Welcome to the World Summit on the Information Society 2016 in Geneva, Switzerland. I'm joined by Betty Bonadelle Azarelli, who works with the satellite operators on trying to bridge the digital divide. And I understand that you will be a speaker at a workshop this afternoon on exactly that topic. Yeah, that's right. The workshop is looking at a variety of issues that have to be taken into account to bring all these remote communities everywhere around the world, the underserved and the unserved, and make sure that they get access to broadband connectivity and they are included into the internet evolution. What sort of challenges are there then in bringing them into this internet evolution? First of all, I think there is a geographical issue that needs to be bridged. These rural communities sometimes are hard to link through to these real means. And satellite technology can bring an added value in order to ensure that the connectivity is brought to these people. This is mainly for women, I have to say, that tend to be in the remote places and get access to the internet. Why is it so hard for women to have access to the internet? I think it's a group of issues that they have to face. If you look at the statistics you will find out that they don't necessarily have access to the devices as easily as men. This may be also linked to the fact that many more women live in rural places and it's also linked that probably statistics say that education is not always as easy for girls as it is for boys. Therefore, bringing the internet and connectivity to remote places and villages will be a good opportunity to bridge that gap. Once women have got access to this sort of connectivity, what sort of things are they going to be able to do? They are going to be able to learn one of the things which is important. Then from there maybe access to health support, get access to an eco-community or an economic ecosystem that will allow them to maybe sustain their community and the village and contribute to the well-being of their community. What do you hope might come out of the workshop this afternoon? What concretely can we see as a way forward to promoting this inclusion of women? I hope that this afternoon reaffirms the importance of bridging this digital divide and brings sustainable solutions for that, including funding schemes to allow this to happen and promote ICT in the broad range of communities. Betty Barnadel Azarelli from the AB5 Consulting Group, thank you very much for joining us and please do also tune in to the video interviews that we're doing all week at the WISIS Forum which you'll find on the ITU YouTube channel.


Hello and welcome to lecture number 3 of this lecture series on turbo machinery aerodynamics. In the last lecture that was lecture number 2, we had discussed about some simplified aero thermo analysis of compression systems and where we discussed about the significance of such an analysis method. We will also we had also discussed about how we can construct a velocity triangle and use that in our preliminary design analysis and how we can use the simplified analysis to help our detailed design analysis which will be taken up after the simple aero thermo dynamic analysis. In today's class, we will continue with discussion on some of these topics. To begin with, we will be talking about how we can calculate the pressure of the work required for a certain compression to be carried out and how we can estimate the pressure ratio based on the work requirements for the compression process. So, we will basically be deriving an expression for the pressure ratio expressed in terms of the temperature rise and the efficiency. So, that is one of the first things that we will be doing today. Subsequently, we will discuss about some of the design parameters which are used in the initial design of a compression system. We will be talking about the various parameters like the flow coefficient and the stage loading coefficient, the degree of reaction and the diffusion factor. So, we will discuss about all of these parameters in detail and the significance of these parameters. And then we will take up discussion on what is known as a cascade aerodynamics. We will be discussing about the aerodynamics of a cascade. We will first take up what we mean by a cascade and what a cascade wind tunnel looks like and what is the significance of a cascade in the design process. So, these are some of the topics that we will be discussing in today's lecture. So, we will start our discussion with the calculation of work for a compression process. We will then take up the design parameters and then we will do we will carry out a two dimensional analysis of what is meant by a cascade and the aerodynamics of cascade flows. So, in the previous lecture, if you remember we had drawn a velocity triangle across a stage of a compressor where we also expressed all the velocity components, the absolute velocity, the relative velocity, the blade speed. Then the tangential components as well as the axial component of velocities. So, using the discussion that we had in the last class, let us now carry out some analysis of the flow across a stage and how we can estimate the pressure ratio as the flow passes through a stage. So, we will begin this analysis with an assumption that the axial velocity remains the same. So, if you recall the velocity triangle which we had seen in the last class, we will assume if we assume the axial velocity to remain same that is C a should be equal to C a 1 is equal to C a 2. What we see is that from the velocity triangle we get the ratio u by C a that is where u is the blade speed C a is the axial velocity. This should be equal to tan alpha 1 plus tan beta 1. Similarly, u by C a this is at the what you see here is at the leading edge of the rotor or the inlet of the rotor. Similarly, at the exit of the rotor you have u by C a is equal to tan alpha 2 plus tan beta 2. And so of course, if you take a relook at the velocity triangle this is very simple you will see that this directly follows from the velocity triangle if this assumption of axial velocity being the same is true. Now, if you consider the change in angular momentum of the air as it passes through the rotor you have seen that at the inlet of the rotor the whirl component or the tangential component of velocity of the absolute velocity C w 1 and the exit of the rotor it is C w 2. So, what is the net change in tangential component or of velocity across the rotor it is basically the difference between C w 2 and C w 1 which we had expressed as delta C w. If you remember in the last class we had expressed difference between C w 2 and C w 1 as delta C w. So, this multiplied by the blade speed will tell us what is the net change in angular momentum as the flow passes through the rotor. So, the net work done for driving this rotor should be equal to this net change in momentum which is why we have now written w which is the work required for this compression process as equal to the product of u and the net change in the angular velocity. So, u multiplied by delta C w is that is u multiplied by C w 2 minus C w 1 gives us what is the net change in angular momentum as it passes through the rotor and this is basically equal to the work required or work done on the flow per unit mass. Here C w 1 represents the tangential component of velocity before the rotor or at the inlet of the rotor and C w 2 is the tangential component of velocity at the exit of the rotor. Now, so from the velocity triangle we can also write or express these velocity components that is C w 2 and C w 1 in terms of the axial velocities. So, C w 2 should also be equal to C a times tan alpha 2 and C w 1 is C a tan alpha 1. So, u times C a multiplied by tan alpha 2 minus tan alpha 1. So, this is also equal to the net work done. Now, if you remember from the velocity triangle we can also write the difference between tan alpha 1 and tan alpha 2 that is tan alpha 2 minus tan alpha 1 is also equal to tan beta 1 minus tan beta 2. Therefore, we have the work done as u into axial velocity C a tan beta 1 minus tan beta 2 and which is also basically equal to u times delta C w. So, what we have here is that we can express the net work done which is a function of the blade speed as well as the change in the tangential velocity delta C w. So, the product of the blade speed and delta C w will give us what is the or we will tell as what is the amount of work required or that is amount of work that is done on the flow by the rotor blades. So, and this energy that is added on the flow will basically reveal itself in the form of an increase in stagnation temperature of the air. Therefore, the work done as indicated here as equal to u times delta C w will be also be equal to the net change in stagnation enthalpy in the stage. Because you are adding work on the flow there through the rotor which obviously leads to an increase in stagnation enthalpy that is something we have seen in the last class that from the inlet of the rotor to the exit of the rotor there is an increase in stagnation enthalpy across the stator there is no change in stagnation enthalpy. So, the net change in stagnation enthalpy taking place in the stage is basically as a result of the work done by the rotor on the flow. So, what we can do is that we can equate delta h across the rotor that is h 0 2 minus h 0 1 should be equal to the work done on the flow that is u times delta C w. Now, here we will express now the enthalpy in terms of the temperature the stagnation enthalpy difference is also equal to stagnation temperature difference multiplied by C p. So, that is T 0 2 minus T 0 1 is equal to del u times delta C w by C p which is also equal to delta T naught by T 0 1 which is u delta C w by C p into T 0 1. Now, since the flow is adiabatic as that is some one of the basic things that we have seen in the last class since it is adiabatic there is no work done as the flow passes through the stator and therefore, T 0 3 should be equal to T 0 2. So, what we will do now is to define what is known as the stage efficiency. If you remember in the last class we had expressed the compression in a stage in terms of temperature and entropy diagram and I had specifically mentioned that deviation of the process from an isentropic behavior is expressed in terms of what is known as an isentropic efficiency. Now, for a stage what we will do is that we will express this as what is known as the stage efficiency which is basically the difference between the enthalpy at the exit of the stage for an isentropic process minus the inlet enthalpy thus divided by the actual enthalpy at the stage exit minus the inlet enthalpy. So, we will define stage efficiency as equal to H 0 3 S or H 0 3 prime that is the stagnation enthalpy at the exit of the stage minus H 0 1 which is the stagnation enthalpy at the inlet divided by H 0 3 minus H 0 1. We can express this further as T 0 3 S or T 0 3 prime which is the isentropic stagnation temperature at the exit of the stage divided by T 0 1. This is equal to 1 plus the stage efficiency multiplied by delta T naught divided by T 0 1. So, here we have expressed the stagnation temperature ratio in terms of the stage efficiency and delta T naught and the inlet stagnation temperature. So, here in this expression that we have written just now delta T naught represents the net change in stagnation temperature across the stage which is basically the actual stagnation temperature rise T 0 3 minus T 0 1. Now, we will express this expression that is T 0 3 S by T 0 1 is the stagnation temperature ratio for an isentropic process. This is related to the pressure ratio through the isentropic relation. So, T 0 3 S by T 0 1 is equal to P 0 3 S by P 0 1 raise to gamma minus 1 by gamma. Therefore, we have pressure ratio P 0 3 by P 0 1 is 1 plus the stage efficiency into delta T naught divided by T 0 1 the whole raise to gamma by gamma minus 1. So, this we will combine with the previous expression which we have written here for delta T naught by T 1 in terms of the components from the velocity triangle that is u times delta C w. What we get here is P 0 3 by P 0 1 is 1 plus the stage efficiency multiplied by u times delta C w by C P T 0 1 raise to gamma by gamma minus 1. So, we have now here an expression for the pressure ratio across a compressor expressed in terms of a certain parameters which for example, u times delta C w is something you can find from the velocity triangle itself. The inlet stagnation temperature is known the stage efficiency if known then the pressure ratio across the stage of a compressor can be quite easily determined. So, we have now derived an expression which can basically tell us the amount of pressure ratio that you can get from a stage if one can estimate the if of course, the blade speed is known and the change in the tangential velocity across the rotor is known one can estimate the pressure ratio per stage. So, this is one way of estimating the amount of pressure ratio that one can express for that one can expect from a stage of a compression process or the other way round to look at it is if this there is a certain pressure ratio requirement what is the kind of work that will be required for generating this amount of pressure ratio per stage. So, we have expressed the pressure ratio that can be developed per stage in terms of some of the parameters which can be obtained quite easily from the velocity triangle. And therefore, the pressure ratio that one can achieve per stage of compression can be directly expressed in terms of some of these parameters. Now, if you take a closer look at the expression that you have just derived we can see that the per stage temperature rise that is which basically the equation which relates this temperature rise to the pressure ratio. We see that to obtain a high temperature ratio for an overall pressure ratio there are two possibilities here which can lead to minimum number of stages one is that you can increase the blade speed that is if you increase the blade speed here as shown here because the pressure ratio is directly a function of the blade speed. And the other is of course, to increase the axial velocity because that is something which would come up here. Now, or change the fluid deflection that is you have a higher fluid deflection which means that the difference between the inlet and exit blade angles that is beta 1 minus beta 2 would be quite high. Now, all the three obviously have certain limitations that is high blade speed of is in one sense limited by the blade stresses and high axial velocity or fluid deflection is limited in terms of the aerodynamic performance penalties that one may have to be and also the adverse pressure gradients which might lead to that is if the fluid deflection is very high the fluid is forced to take up an increased turn which means that it leads to increased pressure gradients adverse pressure gradients and that the performance of the blade of the compressor would be drastically affected. But of course, one can see that from this pressure ratio relation with the temperature rise or the blade speed one can at least estimate the parameters on which the increase in pressure ratio can be achieved. So, what we have discussed now is from simple thermodynamics how we can estimate the pressure ratio that one can achieve per stage using some of the parameters like the temperature and the inlet conditions as well as some of the parameters coming in from the velocity triangles you can estimate what is the kind of pressure ratio that one can expect from a certain stage of an axial compressor. Now, having understood this what we will do next is to try and understand the different design parameters which are usually used in the initial design stages. So, let us try to understand what are those parameters which are used in the design exercise and what is the significance of each of these design parameters. So, we will see that there are primarily four types of design parameters that we need to look at. And these are parameters which are usually used in a parametric analysis of axial compressor. Now, one of the important parameters is what is known as the flow coefficient. Flow coefficient is usually expressed in terms of phi and flow coefficient is the ratio of axial velocity to the blade speed u. So, C a by u tells us what is meant by the flow coefficient. And you can see here that the numerator of this flow coefficient is the axial velocity. Significance of this parameter is in the fact that flow coefficient is in some sense non-dimensional form of a mass flow rate that is primarily because for a given blade speed as flow coefficient changes it also tells us that there is a change in mass flow rate because mass flow rate is directly a function of the axial velocity. And therefore, we will see little later in some of the later lectures that the performance characteristics of typically a single stage of axial compressor is expressed in terms of one of the parameters using which one would express the performance parameter characteristic is the flow coefficient because it is an indication of the mass flow rate. The other parameter that we shall be interested in is known as the stage loading coefficient usually denoted by psi. And this is equal to delta H naught by u square that is delta H naught represents the change in stagnation enthalpy across the stage divided by u square. This is also equal to delta C w by u because delta H naught is u times delta C w. Therefore, you have delta C w by u which is usually denoted as the stage loading coefficient. And so these are two parameters to begin with which we shall be interested in and we will be using these parameters in great detail when we take up the performance characteristics of single stage and subsequently multi stage axial compressors. Now, there are two other parameters which are of interest one is known as the degree of reaction will denote by symbol r subscript x and the diffusion factor which will denote by d star. So, we will discuss these two parameters in little more detail as to what is meant by a degree of reaction and what is meant by a diffusion factor and how we can calculate these parameters. Now, let us take a look at what is meant by degree of reaction. Now, in a axial compressor stage as we have seen diffusion is or the compression is shared by both the rotor as well as the rotor as well as the stator that is part of the diffusion takes place in the rotor and part of the diffusion takes place in the stator. So, the degree of reaction is basically telling as what is the extent to which the rotor takes part in the entire diffusion process as compared to the entire stage. So, degree of reaction tells us what is the fraction of the diffusion that has taken place in the rotor as compared to the diffusion across the whole stage itself. So, we will be expressing diffusion factor in terms of pressure static pressure as well as enthalpy shortly. Now, static pressure rise takes place as we have seen it takes place both in the rotor as well as the stator and degree of reaction gives us some measure of the extent to which the rotor contributes to the overall pressure rise in the stage. Now, to express this in terms of the enthalpy or the rotor or the static pressure degree of reaction by definition is the ratio of static enthalpy rise in the state in the rotor divided by the stagnation enthalpy rise in the stage that is H 2 minus H 1 which is the static enthalpy rise in the rotor divided by H 0 3 minus H 0 1 which is the stagnation enthalpy rise taking place in the stage. This is equivalent to H 2 minus H 1 divided by H 0 2 minus H 0 1 because H 0 2 is equal to H 0 3 there is no stagnation enthalpy change in the stator. Now, for a an incompressible flow we can express enthalpy can be equated to the change in static pressures divided by density that is H 2 minus H 1 can be expressed in terms of P 2 minus P 1 divided by delta by rho. So, for a rotor we can see that H 2 minus H 1 can be expressed in terms of P 2 minus P 1 divided by rho. Similarly for the stage H 0 3 minus H 0 1 is equal to P 0 3 minus P 0 1 divided by rho. Therefore, this degree of reaction is which was expressed in terms of enthalpy is that is H 2 minus H 1 divided by H 2 H 0 2 minus H 0 1 is equivalent to P 2 minus P 1 divided by P 0 2 minus P 0 1. So, that is following from this previous expression that I just mentioned. So, we can express the degree of reaction in terms of these static pressure rise in the rotor divided by the stagnation pressure rise in the rotor. Now, we will further simplify this expression and express that in terms of velocities and angles which one can determine easily from the velocity triangle. The intent here is that we can express the degree of reaction in terms of parameters that can be derived from a velocity triangle. So, from the velocity triangle one can one should be in a position to estimate the degree of reaction for a particular rotor stator combination. Now, from the classical thermodynamics that I assume you would have undergone the steady flow energy equation which you might have studied in your thermodynamics course tells us that the sum of enthalpy plus the kinetic energy is conserved. So, H 1 plus V 1 square by 2 should be equal to H 2 plus V 2 square by 2 for a flow through a compressor or a turbine. Therefore, we have degree of reaction which was expressed in terms of H 2 minus H 1 divided by H 0 3 minus H 0 1. We will now express that in terms of the velocities. So, on the numerator we have this difference H 2 minus H 1 as V 1 square minus V 2 square divided by on the denominator it is stagnation enthalpy change in the in the stage. This is equal to U times delta C w. So, we have the denominator 2 U into C w 2 minus C w 1. So, if we assume that axial velocity is a constant in a stage then V 1 square minus V 2 square can be equated to V w 1 square minus V w 2 square and we also know that V w 1 minus V w 2 is also equal to C w 1 minus C w 2 assuming that axial velocity remains the same in the stage. So, if we substitute for all this in the degree of reaction expression we get degree of reaction as 1 by 2 that 0.5 minus C a by 2 U into tan alpha 1 minus tan beta 2 or C a by 2 U into tan beta 1 plus tan beta 2. So, this of course, comes from the velocity triangle directly. So, what we have done now is to express the degree of reaction in terms of parameters which one can easily determine from the velocity triangle. So, here we have axial velocity degree of reaction is now a function of axial velocity and the blade angles tan beta 1 plus tan beta 2 and denominator we have the blade speed. All these parameters can be quite easily estimated from the velocity triangle and therefore, if one can construct a velocity triangle for a certain rotor stator combination one can estimate the degree of reaction simply by developing the velocity triangle based on the flow conditions. So, degree of reaction is something that you can estimate from the velocity triangle and the significance of the degree of reaction is the fact that it basically tells us how much does the rotor contribute to the overall pressure rise or the diffusion taking place in the compressor. So, this is one of the parameters that will be of significance when we carry out detailed design exercise one would be looking at what is the degree of reaction in a typical compressor stage. So, what we will do is now we will now take a look at some of the special cases of degree of reaction which are likely to which one might likely one might encounter when we carry out the design exercise what happens to the different values of degree of reaction. For example, if what if degree of reaction is 0 and what if degree of reaction is equal to 1 or 0.5. Now, let us take a look at a few special cases of degree of reaction when degree of reaction is 0 what happens and degree of reaction is 0 it means that the blade angles beta 2 will be equal to minus beta 1. When degree of reaction is 0 it basically means that there is no change or there is no contribution of the rotor to the overall pressure rise because degree of reaction is 0 it tells us what is the contribution of rotor to the overall pressure rise. So, when 0 degree of reaction is 0 and if you substitute degree of reaction r x equal to 0 here what you will see is that beta 1 beta 2 is equal to minus beta 1. There is no pressure rise in the rotor the entire pressure rise is basically taking place in the stator and the rotor merely deflects the incoming flow and this basically represents an impulse blading. So, we will probably discuss little more details of these in later lectures that is in this particular configuration if degree of reaction is 0 the rotor primarily does not do any work on the flow it simply deflects the flow entire pressure rise takes place in the stator. Now, the second possibility is if degree of reaction is equal to 0.5. So, if you substitute r x is equal to 0.5 here what you will observe is that you will get alpha 1 is equal to beta 2 and alpha 2 is equal to beta 1 and if you recall the velocity triangles which also I will show in the next slide. In such a situation what you will observe is the velocity triangles are symmetric and since degree of reaction is equal to 0.5 it also means that there is an equal pressure rise taking place in the rotor and this stator and the third extreme case is if degree of reaction is equal to 1 and degree of reaction is equal to 1 alpha 2 is equal to minus alpha 1 entire pressure rise takes place in the rotor the stator has no contribution to the pressure rise taking place in the rotor. So, these are three different special cases of degree of reaction where one might encounter natural design you are likely to encounter values in which are in between 0 and 1. So, if you now look at the velocity triangles corresponding to each of these three cases one can see what is the difference between the velocity triangle as we change the degree of reaction from 0 all the way to 1. So, for a degree of reaction of 0 beta 1 was equal to minus beta 2. So, here we have velocity triangle for this particular case we have beta 1 and this is beta 2. So, beta 1 is equal to minus beta 2. So, you can see the change in velocity triangle you can see what happens to the velocity triangle in this case. So, this first one corresponds to the velocity triangle at the rotor inlet and this corresponds to the velocity triangle at the rotor exit and in such a configuration the rotor does not basically contribute to any pressure rise it simply deflects the flow which is also true here as you can see v 1 is in magnitude equal to v 2. So, that is there is no change in relative velocity as it passes through the rotor and since there is no change in relative velocity as it passes through the rotor there is no diffusion taking place in the rotor the entire diffusion takes place in the stator. The absolute velocity on the other hand of course increases there is a tremendous increase in absolute velocity from C 1 to C 2. When degree of reaction is 0.5 we have alpha 1 is equal to beta 2 and alpha 2 is equal to beta 1. We get a velocity set of velocity triangles which are symmetrical or velocity triangle at the inlet and exit of the rotor are mirror images of one another. So, one would have C 1 is equal to v 2 and C 2 is equal to v 1 because alpha 1 is equal to beta 2 and alpha 2 is equal to beta 1 and in this case both the rotor and stator contribute equally to the pressure rise. And the third case is when degree of reaction is 1 we have alpha 2 is equal to minus alpha 1 and here the entire diffusion takes place in the rotor which is because you can see that there is a tremendous change in the relative velocity from v 1 to v 2. So, the entire diffusion is restricted to the rotor in this case. So, these are three different cases of degree of reaction possible values which the degree of reaction can take play of can take during a particular design exercise. Now, let us move on to the next parameter that is of interest to us which is known as the diffusion factor. We will now look at what we mean by diffusion factor and how we can calculate diffusion factor for a certain design of a rotor a combination. Now, diffusion factor is basically looking at as the name such as diffusion itself in the blade we have seen that the fluid deflection that is the difference between beta 2 and beta 1 is a very important parameter which affects the stage pressure rise. So, it means that as we increase this deflection as we increase beta 2 minus beta 1 we can get a substantially high amount of diffusion at the same time we are also risking the fact that increasing the diffusion can also lead to increased pressure gradients adverse pressure gradients eventually it might lead to the blade stall because if you are operating a blade with a substantially high amount of diffusion the fact that the blade might undergo stall is also true rather. So, diffusion factor is a parameter which will now tell us what is the possibility that the blade might stall and what are the kind of numbers that we need to look at to ensure that the blade stalling does not take place. So, diffusion factor is a parameter which basically associates blade stall with deceleration primarily on the suction surface of the airfoil because that is where one would expect the blade to stall to take place under normal incidence angles. So, diffusion factor will tell us what is the what is the relation between the blade stall and deceleration on the blade surface. So, it is basically defined as the difference between V max which is the ideal suction surface velocity at the minimum pressure point and V 2 which is the ideal velocity at the trailing edge divided by V 1 which is the velocity at the leading edge. So, velocity difference between the maximum and the trailing edge velocity to the leading edge velocity. So, let us look at what diffusion factor definition basically means. So, what I have shown here is the distribution of velocity on the suction and pressure surface as a percentage called. So, on the y axis we have velocity the relative velocity and on the x axis we have the percentage called. So, this represents the leading edge of the blade and this represents the trailing edge of the blade. So, as the flow proceeds from the leading edge you can see there is a an acceleration from the leading edge all the way to the minimum pressure point which is where the velocity remains attains its maximum on the suction surface, subsequent to that the flow decelerates. So, you can see that after the minimum pressure point the flow decelerates and then you have a decrease in velocity all the way up to the trailing edge. So, this here represents V 2 which is the trailing edge velocity. So, diffusion factor is basically the difference between this velocity here that is V max minus V 2 as a function of the inlet velocity. So, greater this difference between V max and V 2 the greater is the diffusion, but on the other hand it also indicates the fact that higher the diffusion means greater is the pressure gradient the adverse pressure gradient that is the static pressure at the trailing edge would be much higher than the minimum pressure point here. So, as you increase this difference between V max and V 2 in relation to the inlet velocity the adverse pressure gradient also increases. So, diffusion factor tells us that beyond a certain level a certain parameter or certain level if you try to increase the diffusion even further there are chances that the blade might stall is quite high. So, diffusion factor would in some sense tell us that what are the chances that the blade might stall given a certain value of diffusion factor. So, how do we calculate these maximum and minimum velocity? So, we have in the diffusion the fundamental definition of diffusion factor is in terms of max velocity and the trailing at velocity to the inlet velocity. So, for a long time it was in the earlier days when the significance of this parameter was realized calculating the maximum velocity from experimental data was not quite easy. And therefore, they had to come up with some form of an empirical correlation to estimate the value of diffusion factor from the data that one would get from a internal testing. So, in 1953 way back in 1953 Leiblin proposed an empirical parameter for calculating diffusion factor. Now, the advantage of this is that you can express this diffusion factor entirely in terms of parameters which are measured and also there is a strong dependence of the diffusion factor on the solidity which is the chord to the spacing ratio. And the definition for what the Leiblin's diffusion factor definition is 1 minus v 2 by v 1 plus v w 1 minus v w 2 divided by 2 into c by s into v 1. So, here you can see that besides certain geometric parameters there are also velocity components and the tangential velocity components which are involved here in this definition of the diffusion factor as stated by Leiblin. And over the years from experience it has been found that diffusion factor of around 0.5 is what is considered as a safe diffusion factor. Diffusion factors exceeding 0.5 might lead to the possibility increased threat of blade stall occurs at diffusion factors which are much higher than 0.5. So, 0.5 is kind of considered as a safe diffusion factor in most of the preliminary design analysis. So, we have now looked at four different performance parameters starting with the flow coefficient which was a ratio of axial velocity to the blade speed then the loading coefficient and subsequently we discussed about degree of reaction and the diffusion factor. So, these are four fundamental parameters which form part of the design optimization cycle. There are of course, a few more parameters which we will discuss little later. So, but to begin with these are the four parameters that we need to be familiar with and something that we will be taking up in discussion in detail in subsequent lectures as well. So, now that we have understood the working of a rotor stator combination of a compressor stage and also the different performance parameters. Let us now proceed towards discussion on a concept of what is known as cascade. Cascade is basically forms the fundamental basis for carrying out a two dimensional analysis of compressor blades and so we will discuss about what is meant by a cascade and what constitutes a cascade wind tunnel and what are the different parameters that one can expect from cascade testing. So, let us take a look at what is meant by a cascade and what are the constituents of a cascade? So, a cascade is basically a stationary array of blades and the basic function of a cascade is to measure certain performance parameters which can be used in axial compressor design. So, that is subsequent to a preliminary design of an axial compressor blade one may like to test these blades for its performance and cascade is the simplest form of experiments or performance tests that can be done on a certain type of compressor blades. The compressor blades are simplified and since the blades are stationary detailed measurements are relatively easy on a cascade as compared to a rotational on an actual compressor setup. So, cascade is a simplified form of an experimental test facility where one can do wind tunnel test to estimate the performance of a particular compressor blade compressor or turbine blade designs. Now, cascade wind tunnels usually have porous end walls. So, as to remove boundary layer so that you get a pure two dimensional flow one would not like to have a three dimensional flow in a cascade in a typical conventional cascade tunnel one would like to remove any three dimensional effects and this is also ensured by removing boundary layer from the casing using boundary layer. So, that the bound end walls of a cascade are porous with something I will explain in the next slide and since the flow is now two dimensional radial variations in the velocity field can be neglected because there the flow is purely two dimensional. So, cascade analysis basically relates the fluid turning angles to the geometry and also the losses in stagnation pressure that are likely to be incurred as the flow passes through a cascade blade. Now, typical conventional cascade will consist of a turn table on which all the blades are mounted and so a turn table will enable the enable us to rotate the blades. So, as to change the angle of incidence of the flow and in a cascade the conventional cascade one would like to measure the surface pressure distribution of the blades and also the stagnation pressure loss taking place across the blades. So, measurements in cascade basically consists of pressures velocity and flow angles downstream and upstream of the cascade and the cascade wind tunnels usually will have provision for traversing these different types of probes at the trailing edge for measurement and on the blade surface one would measure the static pressure distribution. So, that one can estimate the C P distribution or the blade loading from the C P distribution that we get from the cascade. So, what you see here is a typical open circuit so called open circuit cascade wind tunnel it is called open circuit because it draws air from the ambient and releases air at the other end of the cascade back to the ambient. There are certain wind tunnels which are also known as closed circuit wind tunnels where it is the same air which is circulated again and again within the cascade. So, that is a closed circuit wind tunnel and this is called a linear cascade because all the blades as you can see here are arranged in a linear fashion. There are also cascade tunnels which are annular in nature where the blades are arranged in an annulus. So, those are annular wind tunnels cascade tunnels. So, cascade tunnel as you can see consists of various components and if you have seen a wind tunnel cascade tunnel is very similar to that of a conventional wind tunnel it has all those components. There is a driving drive section here where a fan drives the flow through a series of screens and wire mesh screens to ensure that the flow that reaches the test section is uniform and free of high levels of turbulence. Then there is a contraction section just before the test section to accelerate the flow and further reduce the turbulence levels. Now, upstream of the cascade you can see these slots. These slots are basically meant for removing the boundary layer to ensure two dimensionality of the flow as it reaches the blades and this is the cascade that you can see. You can notice a series of blades which are arranged in a linear fashion. So, all these blades together constitute a cascade and at the trailing edge you can see an axis shown here which is basically a line of traverse that is where one would traverse the probes and take measurements at the trailing edge of the blades. If I take a closer look at the same the test section the cascade section would look like this. These blades either compressor or turbine blades are arranged in a linear fashion and that is what is mounted on a turn table that is the entire section can be actually rotated. So, that one can change the incidence angle of the flow entering the cascade. So, as you rotate the cascade axis one can change the incidence angle. Now, that I mentioned about incidence angle let us also look at the cascade nomenclature. So, there are certain angles and geometric parameters that one needs to be familiar with when we are dealing with cascades. So, what is shown here is the different parameters in terms of the different geometric parameters associated with the cascade. The most fundamental parameter being the chord of the blade which is indicated here by symbol C. So, C represents the chord of the blade and the distance between two blades is represented as by symbol S it is known as the spacing or the pitch of the blades and here T represents the thickness of the blades and the angle subtended by tangent at the leading as well as the trailing edge is known as the camber which is indicated by symbol theta. So, theta tells us the camber of the blade. So, higher the camber the higher would be the turning across the blade and theta is measured by tangent the angle subtended between tangent at the leading edge and tangent the trailing edge of the blade. Now, psi here denotes the denotes what is known as a stagger or the setting angle it is basically the angle between the chord of the blade and the cascade axis. This angle that you see here represents the stagger or this angle angular setting of the blade incidence angle i denotes the angle between the incoming velocity which is shown here as C 1 and the blade angle at the leading edge. So, the angle between the blade and the velocity vector is known as the incidence angle. So, the difference between these two gives us the incidence angle. Similarly, at the trailing edge the difference between the velocity vector and the trailing edge tangent to the trailing edge gives us the deflection angle. So, incidence angle represents the angle between the velocity vector and the leading edge and deflection angle gives us the angle between the velocity vector leaving the trailing edge and the tangent at the trailing edge. In most of the designs the one of the criteria would be to try and minimize the incidence and deflection angles. One would like to keep by design the incidence and deflection angles as low as possible because as the angle incoming velocity vector deviates from the design angles or for higher and higher incidence angles the chances of deterioration in performance of the cascade is also higher. So, in or for a compressor one would like to minimize the deviation or at the trailing edge or incidence at the trailing edge to as low as value as possible. So, as to minimize the performance penalties associated with deviation of the incidence angle or the deflection angle from what it is been designed for. So, in a typical cascade one can adjust all these parameters in terms of the for a given test section the chord is fixed one and the spacing for the given solidity is fixed. But one can change the incidence angles one can change the stagger or setting angles and see how all these parameters influence the performance of this particular cascade which has been or the blade which has been designed. So, in a in a modern day cascade one would like to take lot of measurements because cascade facilitates detail measurements on compressor blades primarily because of the fact that the blades are stationary and because the blades are stationary one can take very detail measurements which probably are quite difficult to take in rotating machinery and therefore, cascade testing forms is still a part of modern day design exercise where one could carry out quite detailed measurements on compressor blades. In fact there is substantial amount of literature available on series of different types of compressor blades which are used and all this data has been generated primarily from cascade testing. Now, in cascades one would normally use different types of measurement devices measuring probes for measuring total pressure losses and static pressure on the blade surface flow angles etcetera. So, one might use different types of probes which could be nulling probes or non nulling probes either cylindrical type of probes or cobra probes these are different types of probes that one might like to use to carry out measurements in a cascade and infer data from the cascade testing. So, what we have discussed in relation to cascade is the fact that cascade allows us cascade testing allows us to carry out detail measurements in much more simplified geometry without the complexities of rotation which are present in an actual compressor. So, let me now quickly recap our discussion in today's lecture we started our discussion today with the compression process taking place in an axial compressor stage how we can estimate the pressure ratio and how we can relate pressure ratio to the temperature rise in a stage of an axial compressor. And what is it that the pressure ratio depends upon that is increase in pressure ratio would require that we either have increase in axial velocity or blade speed or a deflection each of them obviously as we discussed have certain limitations. We then discussed about different performance parameters or design parameters which are used in design of axial compressors to begin with we discussed about flow coefficient and then we have the loading coefficient. And subsequently we also discussed about two other parameters the degree of reaction which tells us what is the amount of static pressure rise that is generated in a rotor as compared to that of a stator. And in subsequently we also discussed about what is what is meant by the diffusion factor diffusion factor basically tells us the amount of diffusion that one can achieve in a rotor without the risk of flow separation that is likely to take place or diffusion factor indicates the chances of flow separation due to adverse pressure gradients which might occur with increasing deflection across a rotor blade. We then spend a few minutes on discussion on cascades what is meant by cascade and what is the significance of a cascade. And subsequently we also discussed about what is meant by a cascade tunnel and how we can carry out testing of two dimensional blades in a cascade. And what are the kind of measurements that one can take in a cascade we also had some quick discussion on the nomenclature which is used in a cascade what are the different geometric parameters like this the chord the spacing the camber the stagger and incidence and deflection angles. In the next class we are going to continue discussion on cascades and two dimensional analysis. We will now extend the discussion to losses different types of two dimensional losses that we can associate to a cascade and how we can estimate some of these two dimensional losses in a typical axial compressor stage. So, we are going to discuss about the losses associated with 2 D flow which is basically a cascade flow and how we can estimate these losses in an axial compressor. So, these are some of the topics that we will be discussing in our next lecture.


Hello and welcome to this session. This is Professor Farhad and this session we would look at taxable estate and specifically we're gonna be looking at expenses, losses and deductions. This topic is covered in a corporate income tax course, the CPA exam regulation section, enrolled agent exam. As always, I would like to remind you to connect with me on LinkedIn if you haven't done so. YouTube is where you would need to subscribe. I have 1,600 plus accounting, auditing, tax and finance lectures. If you like my lectures, please like them. It doesn't cost you anything to share them. Put them in playlist. If they benefit you, it means that they may benefit other people, so share the wealth and please connect with me on Instagram. On my website, you will find additional resources such as multiple choice, true, false, CPA questions, CPA exercises that are quasi-CPA simulations. So if you're studying for your CPA exam or you want additional resources, I strongly suggest you check out my website. Let's start by reviewing the estate tax formula, which starts with the fair market value of gross estate. And this is what we talked about in the prior session. You can check the description, which is what we call the slime one. Then we deduct from line one, we're gonna call line two and it's not really one line, it's multiple lines, but on these lines, we're gonna have expenses, losses and deductions. And in this session, we're gonna be focusing on this line, line two, the deductions, the losses, the expenses. Then line one minus line two will give us line three, which is the taxable estate. Then we add any taxable gift, which we already talked about, gifts and taxable gift. You could also look in the prior session, equal to the estate tax basis. Now we're gonna figure out what's our tax liability, deduct any taxes that we paid prior and prior years, post-1976 tax, deduct the unified tax credit, deduct any other tax credit, then if the answer is still positive, we have a tax due on estate tax. And basically, eventually we're gonna work all this formula, all this formula, but the two most important line are line one and line two and the rest are computation. And you will see later when we work and exercise that once you figure out line one and line two, the rest kind of they fill in from prior knowledge or from other sources. Or you need to know how to compute the tax liability, which we'll talk about this. Now when it comes to deductions, we're gonna focus a little bit more on the marital deductions, but the first we wanna look at losses and expenses. What are some of expenses, losses and charity that can be deducted after the person passes away? This is what we're gonna be looking at. So it's a list of things, a list of laundry list. So for example, for your exam at the university, you would need to know what that list is, what's included, what's not. For the CPA exam, the same exact concept, you wanna know what's included, what's not. Maybe you're better off knowing what's not included in those expenses because it's a list of you wanna know, because usually they ask you what's not. For example, funeral expenses, generally speaking, are included. Expenses incurred in administering the property. Once you pass away, that's included as an expense. Claims against the estate, like any unpaid mortgage, well, you can't deduct this. Expenses incurred in administrating community property. Community property means you and the other individual own it, only deductible to the portion of the deceased's spouse interest in the community. That include what? That include commissions to the executor, the person that's gonna be in charge of the estate, attorney fees, accountant fees, court costs, certain selling expenses. When you wanna sell the property, you're gonna incur expenses. Those are deductible. Deductible. Also, property taxes accrued before the decedents that, so if you owe any property before you passed away, then that's gonna be deductible. Unpaid income taxes on income received by the decedent before they passed away. Same concept. Unpaid gift taxes, so simply put, if you owe taxes before you passed away, you can deduct those taxes. The decedent's unpaid pledge or subscription in favor of public, charitable, religious, or educational organization is deductible to the extended. It would have constituted in allowable deduction had it been made a bequest. So simply put, if the individual that passed away made a pledge, then that pledge is deductible as long as it would have been deductible if the person deductible under taxes of the person basically either was alive or they passed away. Also, if there's any casualty or theft incurred during the period when the estate is being settled. Now here, we're talking about casualty and theft losses, but remember, the rules are a little bit different. What does that mean? It means we don't have the floor or the $100 deduction. So it's just so that casualty and theft losses are deductible if those happen during the settlement when the estate being settled. Charity, shareable contribution if designated in the decedent's will. If the decedents in their will said, I would like to contribute $5 million to a charity. As long as that's included in the will, that's deductible. Now of the executor who'd like, he or she would like to contribute this. That's not up to them. It's not deductible. They can, if they are allowed, but they cannot deduct it from gross estate. So simply put, what I just did showed you what are some of the expenses and losses that are allowed from the gross estate. Okay, because the more you want to deduct, the better off you are because you'll pay less taxes. Now we need to talk about the marital deduction because that's an important deduction. So simply put, the marital deduction, the purpose of it, the Congress says when someone passed away, if they're married, we really don't want to get involved between the husband and the wife. What's gonna happen is we're gonna allow what's called the marital deduction. So this way, the assets goes from the husband to the wife or from the wife to the husband with no tax consequences, with no tax consequences. So the marital deduction allows spouses to arrange their financial affair without federal gift or state gift consequences. So when you transfer assets, money, whatever you have left in your gross estate to your spouse, there's no, really, there's no effect on your federal gift tax or estate tax, okay? So asset can pass between them without any immediate gift or estate tax liability. And that's the purpose, to make the life of the person that passed away a little bit more easier, whether deduction allowed to offset otherwise a taxable gift or an estate. So what you do is you will include it, then you will deduct it. What's called, it's called the marital deduction. Obviously, if you pass away, your asset goes from you to your spouse. Well, it's gonna be included in your gross estate in line one, then in line two, you will deduct it. So it will be offset. So let's take a look at an example. At the time of his death in the current year, T owed an insurance owned an insurance policy on his own life. The face amount is half a million with Ella, his wife as a designated beneficiary. So if something happened to him, the half a million goes to his wife. T and Ella also owned real estate worth 600,000, as standard by entirety. It means when one of them passes away, the other individual gets the property. T had furnished all the purchase price. It doesn't matter if they are married, it's 50-50. As to these transfer, 500, the insurance proceeds, as well as the half of the asset, the insurance proceeds, as well as half of the asset is included in the gross estate of T. So if this is T, if this is Teo, the, let me just kind of write here this way we can see what's going on. If this is, we're gonna assume this is Teo, let me change the color so you can see. This is Teo and this is Ella. Okay, so the asset's gonna go 800,000. Why 800,000? The insurance policy and half of his real estate, okay? Goes to Ella and basically it's gonna be included in line one that then deducted in line two. So 800,000 plus 800,000 minus. Now, marital deduction when the property interest passing to the surviving staff is subject to a mortgage when there's a mortgage against that property. So the asset is passed, but there's a mortgage. We're gonna only count the net value of the interest after reduction by the amount of the debt qualified for the marital deduction. Simply put, if you transfer an asset and it has a loan, what's really transferred is the net value of this asset. In his will, Jacob leaves real estate for the fair market value of half a million to Rachel, his wife, if the real estate, the subject to a mortgage of half of 100,000, upon which Jacob is responsible, the marital deduction is limited to 400,000. So why 400,000? The fair market value of the property minus the loan. The 100,000 mortgage is deductible as an obligation of the decedent. So the 100 remember, if you owed any money, remember you can deduct that as well. That it's not a marital deduction, what really transfer is the net. Then we have something called Q-TIP or Qualified Turnable Interest Property. And we just wanna kind of know what Q-TIP is. When you think of Q-TIP, think of this individual. It doesn't mean think of this individual. This is Mr. Hafner, if you don't know who he is, he's the founder of the Playboy and he had multiple wives. So basically what happened is this. I'm not saying that he used the Q-TIP, I'm just saying when you have more than one marriage, what happened is this.   Now, over the second marriage, your new spouse maybe she has two, three kids. Now, when you pass away, what you want to do is you want to keep some assets to your kids from the previous marriage.  So you can do, individuals can set up a Q-TIP, which is a trust. And what they would do, they would allow the recent spouse, the second spouse, to enjoy the asset, to enjoy the asset in a sense be able to use the asset. But once they pass away, the asset goes to your kids. So simply put, if you pass it, so you have picture, I'm just gonna try to do this real quick. So you have this individual, that's their first spouse. Okay, that's their first spouse and they have three kids. Now they get divorced, now he's married to a second spouse. Really lousy. Okay, now this is his second spouse. Now, what you would do is, you would pass the asset to your second spouse on the condition that once she passes away, the asset goes to the three kids from the first spouse. So this way, rather than paying the taxes now, you would defer the taxes for later. And this way, you also protect your second spouse that she can live off the asset, but there's nothing she can do with it or he can do with it until they passes away, then it goes to what you wanted to do. So basically, it's kind of deferring the tax until the, in a sense, second spouse. It doesn't have to be a second spouse situation. The reason I'm trying to explain this in a second spouse situation to make it easy for you to understand. And that's why I use Mr. Hafner as an example because he is a well-known figure and his divorce case lasted several years. And I don't know if it's done or not, but that's the whole point of it. So property that passes from one spouse to another by gift or at death and for which the transferee spouse has a qualifying income interest for life. So basically the asset goes from Mr. Hafner to his second spouse, let's assume that's the case, and the spouse has a qualifying interest income for life. So if they have stocks and bonds, the spouse can get the stocks, can get the interest, can get the dividend and live off that, okay? So the person is entitled for life to all the income from the property, payable at an annual or more frequent interval, whatever the arrangement is. No person has the power to appoint any part of the property to any person other than the surviving spouse during his or her life. So basically that's the deal. No person has the power to appoint the property other than the spouse. Once you make this election as a revocable, if the election is made, okay, a transfer tax is imposed on the Q-tip, on the trust when the surviving spouse dispose of it by gift. So let's assume the second spouse decided to give it a gift to the designated transferee today, to the kids from the first marriage or upon death, okay? And under those circumstances, if the later transfer occurred during the survivor, spouse's life, which is a gift, a gift tax apply, measure that fair market value, and if the spouse kept the asset until she passes away, it's part of her estate, part of her estate. So this is basically what's a Q-tip, qualified, turnable interest property, okay? An example with Clyde dies and provides in his will that certain asset fair market value of 2.1 million are to be transferred to a trust under which Lily, his wife, to receive income of the trust for her life.  So what's happening here, Clyde doesn't want to transfer the asset to the kids now because it will have to be included in his estate. That's one thing. And maybe he also wants to protect his wife in a sense that he wants the property to be under her control until she passes away. Presuming that all the preceding requirements are satisfied and Clyde's executor so-elects the estate, receive a marital deduction of 2.1 million. So Lily dies when the trust assets are worth 6.4, the amount is included in her gross estate, then it goes to the kids as Clyde wished before he died. So basically there's like a two, what you do is you're deferring, the deferring the taxes for later. And let's take a look at a marital deduction, kind of a good example, work an example to kind of illustrate the concept. Hank and Wendy are married. Hank purchased survivor annuity. Wendy is a beneficiary, the fair market value is half a million. Hank and Wendy jointly own property with a fair market value of 600,000, jointly means 50, 50. Hank owns a property by himself for 100,000.  Hank dies. Let's assume Hank passes his solely owned property to his children, which is only the 100,000. And let's assume he passes everything to Wendy, passes his solely property to Wendy. So let's see how it works, how the marital deduction works. So here we go. What's included in the gross estate of Hank? Well, the annuity he purchased himself, that's his, that gets included. Then the jointly owned property, the 600,000, what's gonna happen with that? It's gonna be split, 50, 50. It's a joint property, 300,000 and 300,000. The 100,000 will be included in the gross estate of Hank and the life insurance, it's because it's his life insurance, Wendy's the beneficiary, but it's his, therefore it's included in his estate. So his gross estate is 1.3 million.  So less the marital deduction. The annuity, 500,000, it's included here. Then it's deducted and transferred to Wendy. The 300,000 is included in the gross estate, then it's transferred to Wendy. It's deducted and transferred to Wendy. This asset he owned solely, he wants to keep for his kids directly. That's not marital deduction. It's gonna be included in his gross estate and the life insurance, the same thing. It's included, then deducted and it goes to Wendy. What's gonna happen is the taxable estate for Hank is only 100,000, which is nothing. It's that don't have to worry about anything. Now, the total gross estate for Wendy after this transfer is 1.5, one point, what's transferred to her, in total, now it's under her estate, 1.5 million. Now let's assume B, Hank transferred his solely property to Wendy, then his estate will be zero and Wendy will have 1.6 million, 1.6 million. We'll work another example when I do the CPA simulations, but this is basically an illustration of the marital deduction. Also what we can include deduct is estate taxes at debt. Now, certain states and certain counties, they impose a debt tax, basically, if you're passing not all states. That's why it's, I have Astrid because it's not all of them. These taxes can be assessed at a marginal of almost 20%. So if you pay the taxes, what can you do? You are allowed a deduction, a deduction against your taxable estate and inheritance taxes. So you pay them for the state or for the county, then you'll get a deduction. So the deduction is not to pay taxes twice, basically deduction for taxes paid to the estate at the debt mitigate the effect of subjecting property to multiple taxes, payable at debt. So you pay the taxes for the state, you will get a deduction. So that's another deduction. So basically, this is the formula that we started with. At this point, at this point, we've covered line one in the prior session. You could look at the description. In this session, we look at line two. Then the remainder of this is basically, it's a computation and we'll work a CPA simulation in the next session illustrating this concept. So in the next session, I'll work a few exercises, kind of CPA simulation to illustrate what we learned and reinforce and understand. Again, this topic often time is not properly taught in college or if it's taught in college, students don't pay attention. Then when they get to the CPA exam, well, you suffer and this is why I can help you. So what I suggest you do, if you like my videos, please like them. If you wanna visit my website for additional resources, don't hesitate to do so. You study for your CPA once, you wanna use all your resources to succeed. This is 20 to 30 year investment.  I'm here to help you and study hard.


Your mind is like a mirror it is reflecting all this You can see this one and this one, but you cannot see this one because this one is behind the mirror You must do one simple thing within a few days. You will be on the other side of the mirror. I would like to ask you If you could relate an experience of divinity within yourself It's like this the reason Why it is not coming to everybody's experiences because everybody believes something The only thing that I have done with myself is I have remained uneducated Just the way I was when I was an infant the same way I am in my mind Nothing in the sense Remaining uneducated is not easy Because from the first day you're born Your parents your teachers every adult Pandit Muller priests everybody is trying to teach you something That's not worked in their life. Yes It's very simple to check whether it's worked in their life or not Suppose you have a child in your house three four five years of age Between you and the child who is more joyful Who should be a consultant for life Miserable ones or joyful ones so if you look at Those people who are giving you all kinds of advises and teachings First look at their face. Don't listen to their words If they're really blissed out you must listen to them we must know how they got so blissful If they're miserable It doesn't matter what big things they are saying the goddamn things have not worked for them So the only thing I did with myself is Remained uneducated that means Not getting identified with your parentage With your family with your religion with your culture with the philosophies floating around With the politics with stuff happening around you You can be involved, but you're not identified Once you're not identified it is natural for human intelligence To turn inward and find this naturally But because we have ready made conclusions We know where God is of course. We know his name. We know his wife's name We know how many children he has we know his birthday. We know what he likes for his birthday. This is a serious problem But you don't know a damn thing about yourself As I already told you the only and only thing that you can experience is this life is What happens within you? You cannot experience what happens here. You can only experience what happens here If you see this You know this only the way it's projected in your mind, isn't it? There is no other way to know it but Belief gives you an outlet from this If you understand if you don't believe anything if you don't just disbelieve anything Naturally every human being would have turned inward Because they believe they're looking heavenward if you don't make these conclusions The nature of human intelligence is It will naturally understand the seat of your experiences within you If you right now the way you're seeing the world is Your mind is like a mirror. It is reflecting all this You're not seeing it here. You're seeing it within So this mirror is showing you everything Don't believe it is a plain mirror Many distortions, but still it is showing things But it never shows you Who you are You can see this one and this one and that one and that one and that one But you cannot see this one because this one is behind the mirror You must do one simple thing I don't know if you will attempt this but you try this If you pay attention right now you're sitting You know sitting for two hours already This is happening when you stand up a Certain pleasantness spreads through you not the relief of the muscles Something deeper if you notice a certain pleasantness happens or you've been standing for a long time You sit down a certain pleasantness happens or let's say you've been thirsty You drink a glass of water Not the coolness of water not the thirst going away much deeper down a pleasantness happens You lie down in your bed after a full day You will see a certain pleasantness spreads through you. You wake up in the morning Certains pleasantness spreads through you because you're in a constant state As I said mental diarrhea You don't notice anything.   Just wait for two minutes. Just look at the food wait Then slowly eat when the food goes into you You will see the entire body response in a certain way certain pleasantness spreads through you You keep paying attention to this right now.  Let's say 12 to 15 seconds Within a few days you will be on the other side of the mirror and you will not ask me this question You will know what it means to live with the divine Right now you're living on the wrong side of the mirror Seeing multiple images a kaleidoscope happening, but you can never see yourself or the nature of your existence The processes of ecstasy were never written down It is only in the presence of a certain being those things happen The yogis have many ways of doing it certain Nadi's in the system That if you activate them You will be ecstatic if this humanity overflows Then divinity will come in search of you


There's so much about what I'm trying to do here comes down to the complexities of being simple. The goal of a meaningful life, having a meaningful life myself, helping others to work together towards this goal, it really is a very simple thing I believe. I don't believe we need to do anything particularly elaborate, and it's quite possible to have a meaningful life without even considering things in the way that I think about things and without any kind of analysis really of any kind. Meaning can come from many different ways, many different sources. There's many different ways to have this meaningful life, and yet as different as they are, I don't think any of them are very complicated. If there's anything that you feel is a very complicated goal, a very complicated requirement that you have, I would bet that it can probably be simplified, reduced to something much less complicated. Some kind of complicated plan in fact feeds into a simple objective. The idea of this meaningful life, it tends to really come down to love and some kind of meaningful work and a sense of alignment, aligning our lives with a higher value. And all these things are very simple. So why do I keep talking about it? Why does it take up all this space? Because it seems like the work is really focused on the distractions, the hindrances, the obstacles, the interference. All of these are all the things that get in the way of the very simple objective. And that's where things get complicated. The obstacles to the simple life are anything but simple. The obstacles themselves and the work of clearing those obstacles. That work just seems to multiply in complexity. The more complex these distractions are, it seems like they multiply beyond just their number. It's like they multiply by their combinations, by their exponential growth. So if you have three things, they have three connections. And if you have four things, they have 12 connections. Maybe someone can check my math on that. But the idea is that with every extra thing you add, every extra detail, every extra point you add to a system, it multiplies the complexity. Not just plus one to the complexity, but multiplying it through its connections with everything else. So I felt this to a small degree today, just taking one more step on clearing out my possessions, trying to sort everything down to a simple, minimal selection so that I can have clear space, clear open space, free of cluttering obstacles. And it takes a lot of work. It takes a lot of time to sort through things. And the decision fatigue of deciding with each object one after another how this will fit in, or if it is decided to pass it on, how will it be passed on. And finding a place for it, finding a category for it, finding, determining its fate as one of my possessions. So this work is, this is complex work. It is busy work. And I've realized today that I need to dedicate more time to this. And I'm looking at this as being something that will be a good weekend activity, a good focus for my weekends, for any free time I have on weekends to work on this, pairing down and clearing out and organizing and simplifying. Because the results are very satisfying. For all the efforts of starting this process, once it starts going, each step forward leaves me with a more clear space so that the feeling of clutter and distractions and interference in my life is just a little bit replaced by that feeling of open space and fresh air to breathe. So this work is in so many ways at the heart of what I think is important. Clearing the physical distractions is what I was working on today. But of course, all the mental, emotional and habitual clutter is, I believe really, the main thing that is blocking us from living that simple, meaningful life. So one day, one step, one less piece of baggage and one more breath of fresh air.


The future, I think it's about first discovering the future before you can own the future. Discovery is an important process. You know, the thing that I find most with my clients, which are companies from all over the world in all kinds of sectors, is that they are so busy doing what they do now, so they have no time to discover what's next. And imagine using technology, we can travel so much faster.  But we're looking in the rear-view mirror the whole time. I mean, we're going faster all the time, we're getting ready to really take off and go into warp drive, but we're looking backwards and saying, oh yeah, this is 10 years ago, this is what worked. Well, you know what's going to happen there is we have terrible accidents. Nokia. Blackberry. Anybody remember Blackberry? You know those? Yeah? Okay. So accidents, right? So not to say that those guys did the wrong thing, it's just, you know, the speed of things is just mind-boggling.


There's an extraordinary amount of errors that occur every single day in healthcare. We also know that there are extraordinary people that come to work every single day to do a good job. Our goal is to do work that actually moves patient safety forward. As we know change is never easy and so it was a very strong collaborative effort. What the ARB program has really done is brought all the disciplines closer together and talking a little bit more than they used to for a common goal and that's improve patient care. Whether the number is 200,000 or 400,000 or one, it's one too many. It starts with us. We have to be the ones to decide we're going to lead us out of that tyranny of happening. With your help we can continue to transform the healthcare system. Because if we're really going to get to zero, we're going to need everyone's help. Do whatever you have to do to get enough partners to make the number zero.


What do you got all right How has will looked and what do you think his readiness is for potentially playing Sunday? Ryan will start and we'll be the third quarter bet What when you see these guys taking these position group pictures and kind of doing some of these wrap-up things? What goes through your mind for this group as they get ready to finish the season? I didn't see any pictures, so I don't know what that that is by my focus is on finishing strong finishing with a win finishing with class and and making this thing Right, you know on Sunday that that's what the focus is and I know that You know, there'll be a lot of different moving parts and But I appreciate, you know the way that they've tried to approach This week here this final week, and you know, it's a great opportunity every time we go out there to do something amazing Individually and then obviously as a team Again, it would be about the team it wouldn't be about one particular player I think that's what the focus is is trying to You know again play these games that give us a chance to To win you know to where? You convert some third downs extend the drive Hit some plays it you know moves change field position finish drive with points and then also, you know get some stops defensively and Use the special teams make all those things that we talk about and so Ryan will be a large part of that of making that happen And helping us Beginning of May Any kind of sentimental feelings as your head is a last game know what to raise the last practice I don't get to walk through tomorrow, but what kind of goes through a coach's mind when you know this is your last run with these guys I think it's just about You know again the the one message of focus on this week and not focus it on things that Coder could not happen in the future, you know, it's just literally focusing on Getting guys ready continue to clean up the details that are gonna be so critical and you know get them as healthy as they can And get them ready to go out and have confidence in what they're doing like that's what this comes down to and then You know at that point in time You know we'll have we'll have meetings and going Different directions, how do you feel like the guys have handled keeping that focus? I think they have handled it well Well as possible. It's not something that you prepare for or get used to you try to You know stay as consistent and possible as the messaging and what you're showing them and you know what you're Trying to get them ready to do and do that all the way up until game time Obviously, we've seen the leadership from Ryan many times before but how has he set the tone for that focus you wanted going into? I think it's been it's been really good Try to obviously command the huddle. I mean that's not never an issue with Ryan and you know coaching these guys up And a fine line and get them the speed and the throws he needs to to feel sharp and to feel ready and to be accurate and decisive Let the ball go What is Ryan's professionalism meant not just this week, but just throughout the season Considering not being a starter and not getting this chance. Well, I boy, we've talked on it. It's a tough spot Biggest thing that he's handled it with with class and you know you can be disappointed but also still be Supportive and be about the team. I think those things can can still happen, right? There's a lot of emotions that they'd go on with each individual player Their role on the football team and how that changes throughout the year But I do appreciate Ryan's professionalism like you mentioned throughout Caleb Farley TK McClendon Anthony Kendall and Colton down In incentive in the contract or you may be eyeballing a couple of those heading into this last game trying to make some extra money I'm just trying to go out and win a game That's that's my objective to go in go out strong Yeah It's tough obviously but Going out being a good team like Jacksonville will obviously make things better And just you know trying to play a complete game trying to you know continue You know where we left off from Miami We felt like you know we did some good things but obviously we didn't continue it So I was just trying to go out and play a complete game. It's it's our focus right now Obviously wishes in the playoffs, but how do you maybe would you describe your year here? I would say it was it was decent, you know, I hope myself to a high regard So, you know, I feel like anytime I'm out there on the field Whatever ball come my way. I should catch or whatever block I should make I should make So, you know, I feel like it was decent wasn't bad, but um, you know, I knew the kind of offense I was coming into run for his offense and you know, I was wanting to come out and try to help these guys win You know, I knew I wouldn't be you know Targeted like, you know, some number one receivers are targeted on certain teams 15 or however so much times a game, but you know for me to have a thousand yards You know, if you play a lot of football, you know, that's hard to do Especially in a run for his office Yeah, never really spent time in Nashville, but I'm from South Carolina. So I would say it's similar just You know more restaurants more people Similar vibes. It's good people though. I love the city. You know, Nashville is treated Treated me, you know, like family welcome me with open arms. You know, and I got here They said, you know, people people don't take pictures with you know, famous people But I found out that's not true Because everybody asked for pictures, but it's a good thing man. I appreciate I appreciate the city No, for me personally, I like challenges like that I've never wanted to take the easy road and just go do what everybody else think I should do or what everyone else should do So for me, I loved it. I love having that challenge of You know us interacting, you know bumping heads having good times bad times You know, but I know will has a lot of football to play in this league and to be part of that starting off I think is special You know, he's gonna play longer than I will You know, so just being able to be someone that he can ask questions to and you know Just give him an honest opinion. I think it's gonna go a long way for his career How competitive he is been around a lot of quarterbacks, he's he's in my top He's in the top three of competitive quarterbacks. I'll play with I'm sorry if you can't shoot something similar already Excited about the prospects of next year When the roster is likely to look a lot different I can just focus on this year Paul in this game Oh, yeah, of course, but you know, I'm focusing on This game and when you ask me one of my you know looking forward to next week Monday, it'll probably be Spending time with my kids, you know in our season. So, you know, I doubt I can give you a PSA of Management questions and an answer Coastal give me Coastal is that I'm trying to get me to start or just what have you seen with him this week? And how do you think you got something to connect out there on Sunday? We seen, you know We've been on ten a hill. So we seen we seen him all year and we know he can do You know, he's he's hungry just like we ought to go out and get a win So I think everybody's gonna, you know, give it their all this Sunday It's not a it's not a game where was going out and and looking at our record like, you know, we're this but You know, I think you're gonna see a team that's gonna compete Sunday How important is it for you guys to end it on a high note? I think it's important for for everyone in here just morale going into the off-season You know a lot of people might not be here some people might be here So, you know, some people are playing not just for this team, but the teams as well Nice paper view


To the backcountry wilderness half marathon in Highlands Ranch, 2 weeks ago, ran the Blue Sky Marathon in Fort Collins, did well, especially the first 22 miles, let it for 22 miles, hit a little bit of a wall and my leg flared up, but so I was not expecting to race again this quickly, 2 weeks later, but you know, the aerobic fitness is there, I just got to do it. I just got to do it. So we're off. It's like 2 seconds away from our house. We would just say we slept in the 720 today. Yeah, it's a 9 AM start. Like that never happens. I love it. Never happens. So, going there. It's my favorite so far. It's my favorite race. I know. We feel good. We got the cowbell. We are ready to rock and roll and I think I'm going to do a little more filming today. Oh. Who knows? We'll see. We're on the journey. So stay tuned. So we're on our way. We're about 15 minutes away. True love's research in the starting line. Is this it? Can we find it? That's okay, pumpkin. Right there. That's Marathon. I was impressed by 5 minutes. Let's hear it. You're overcooking my grits just a little bit. A great event overall. A great event. Great t-shirts with a hoodie. Love it. Amazing. Finisher metal right here. Amazing. And a great like post race party at the finish line and a great starting line environment with good music. But what about out on the course? What about out on the course? I was a little livid after the race. I've calmed down now just a little bit. All I'm saying is where I got lost with 2.5 miles to go, I was in first place by, I would say 90 seconds to 2 minutes roughly. A half mile before I got lost there was an intersection with 6 to 8 volunteers cheering and I think there to help people that were hurt, which is fine, it was like mile 4 and then also mile 10 and a half. And I'm like, please, next year, next year, send one volunteer down that trail to that hard right that in my opinion was not marked well and thankfully I did meet another runner after the race who got lost as well. So I didn't, I was not the only one that got lost at that intersection. Now being in first place at that point, I wasn't following anybody. I wasn't following a lead bike and that is a tip of the day. Whoever the race director is, if you watch this, please have a lead bike throughout the entire race preferably but at least in a couple tough sections where if you've never run those trails before, you're going to get lost. I love you. It was a fun race. I love you all. It was a really fun race. A very smart race. I, two weeks ago at the Blue Sky Marathon, I led for 22 miles and then dropped back to fifth place those last four miles because of my leg and because I hit the wall. Today in the half marathon, I was in fifth place for about seven and a half miles and then crushed it to the, let's see, 10 and a half mile, no, 10, yeah, 10 and a half mile mark. I was in first place for like three and a half, four miles there, just like rolling it into the finish ready for the W. Oh yeah, another thing that hurts is that there was some cash prize money involved in this race today and I was hoping to win it so that I could use that money to register for more races in 2018. What am I going to do now? I don't know. It was 80 bucks, 80 bucks to run this race today. That's not cheap and all I'm saying is you just made a lot of money race director and Hyland's Ranch racing series. Please put more volunteers out on the course at the tough intersections. Please. All right, got that off my chest. Thank you YouTube for listening. Love you. Seek beauty, work hard at not getting lost and love each other. See you tomorrow.


Welcome to submitting your Angling Guide report video for Angling Guide reporting in the province of BC. In this short video, we will review the process of submitting your Excel report to our SharePoint reporting site. Prior to logging into the Angling Guide reporting site, you will need an active BCE ID account and access approval to the site. If you are a new user who has never logged into the site before, please watch our first time users video prior to viewing this recording. Our first time users video will show you how to register for a BCE ID account and how to request access to our site. Logging into our reporting site begins with a link in the confirmation email that you received from our team upon requesting access to the site. You can also access it by clicking on the link provided on FrontCounterBC's website at www.frontcounterbc.gov.bc.ca forward slash guides forward slash fish dash wildlife forward slash angling dash guide forward slash overview. The link to our reporting site is found under section 6, links here. Clicking on the links hyperlink will open up a selection of links for you. Please select the first link entitled Angling Guide reporting website here. Doing so will trigger the Windows security login box in the middle of your browser screen. Enter your BCE ID username using the BCE ID backslash before your username as shown in our example here. Enter your password and click the OK button. If your BCE ID account is active and you have entered your username and password correctly, scroll down to step 1, open and complete an annual submission form. Click on the hyperlink. You will now see the reporting site home page. A new project form will open for you as seen in our example here. Please take your time filling in the required fields on this form. The first field is your Angling Guide license number. Please note that Assistant Angling Guides must report under the license number for the Angling Guide that they guided for. Your Angling Guide license number will begin with the letters AG and then the region code letters for the region to which you are licensed in that year. The last two digits of the Angling Guide license number signify the licensing year. In our example, we have an Angling Guide licensed in the Skeena region in the 2016-2017 license year. It is critical to complete all the fields on the project form that are marked with the red asterisks. SharePoint will not let you leave the form until all required fields, those marked with the red asterisks, are filled in. Proceed slowly and deliberately through the form to complete all required fields. The final few fields at the bottom of the project form are for our team's administrative use. Please do not fill in these fields. Click the Save button at the very bottom of the form once you are done. If you missed one of the required fields, as we did in our example here, you will see the form again after hitting the Save button. You will need to scroll through the form to see which field is highlighted in red and still requires a response. Proceed to the field that is missing its mandatory response and complete the field or fields as appropriate. Click on the Save button at the bottom. Once all the mandatory fields are completed, you will see the information in a tabular format. Scrolling over the Angling Guide license number field will pop out a drop-down arrow. Click on this arrow to reveal the drop-down menu of choices. Select Edit Form. Selecting Edit Form takes you back into the project form for this Angling Guide report submission. Click on Attach File at the top of the form. Click Open to populate the file into the Uploading Tool. Click OK. You will be returned back to the project form. Scroll to the bottom of this form. You will now see the file that you selected at the very bottom of the screen. It is ready to be attached to this project form. Click Save. If the file has been successfully uploaded, you will be returned to the tabular view of your report submission, as seen in this example. You will see a paperclip here. This is your evidence that the file has successfully uploaded. Please note that we are able to accept completed guide reports in both the PC-friendly MSXL and MAC-friendly Numbers spreadsheet formats. Our preference is MSXL. The MAC Numbers program offers users the ability to export to MSXL format as well. You will find this option under the File menu. Export to Dialog Box. Congratulations! You are done with your report submission. If you are still unsuccessful at logging into the site at this point, please contact us via email at anglingguidereporting.gov.bc.ca, providing your name and contact phone number to reach you. Describing your logging in issue and any steps you have already taken to resolve this issue will assist us in helping you better.