Hello and welcome to lecture number 35 of this lecture series on turbo machinery aerodynamics. We have been discussing about different types of turbo machines in the last 34 lot lectures that we have had. And in the last class I think I had mentioned that we are going to take up a relatively new topic now from this lecture onwards. And we are going to discuss about a set of turbines which kind of are contrary to the type of turbines that we have discussed earlier on. We have had some detail discussion on axial turbines which had the inflow as well as the exit flow as axial. In today's lecture what we are going to discuss about are a set of turbines which are in some sense very similar to a centrifugal compressor or these are the radial counterparts of turbines and these are known as the radial flow turbines. We are going to have some detail discussion on radial flow turbines. Today's lecture we are going to exclusively set aside for thermodynamics and the aerodynamics of radial flow turbines. We will also have some discussion in a later lecture on some other aspects of the blade shapes and geometries of radial flow turbines. But today's lecture is going to be primarily on the thermodynamics and aerodynamics of radial flow turbines. We will first have some introduction to the different types of radial flow turbines that are available or possible followed by the thermodynamic working of the radial flow turbines and some elementary aerodynamics associated with radial flow turbines. We will also discuss in some detail about the losses in radial flow turbines and the methods of calculating or estimating these losses. So, we are going to discuss these topics in today's lecture. Now, the history of radial flow turbines dates back to about 150 to 200 years now. It is in the mid 1800s or that the radial flow turbines were developed by a French engineer who was known as Farninon. This turbine was basically a radially outward flow turbine and subsequently a few years later in 1850s Francis and his colleague Boydon developed the inward flow turbines wherein the flow enters the turbine in radially and leaves the turbine in the axial direction. And so these are known as inward flow turbines and some of the modern turbines are actually named after the inventors. These are called Francis turbines. You must have heard about reaction turbines which are also known as Francis turbines. So, these are the earliest developments of turbines and were meant exclusively for use in hydraulic applications for power generation and so on. Some of these types are in use even to this date even after about 200 years or more that these have been developed. And so these are the basic types of turbines which were developed in the 1800s and continue some of the versions or modern versions of these continue to be used. And so there are these two distinct types of turbines. The outward flow turbines which were originally developed by the French engineer and subsequently the inward flow turbine which is the more popular version of the turbine which is continued which continues to be used even to this date. And the inward flow turbine has a set of advantages in the sense that they can cover tremendous ranges of power rates of mass flow and rotational speeds. And therefore, they are used in a variety of applications ranging from hydroelectric power plants where these turbines generate hundreds of megawatts of power to micro or small gas turbines where they generate probably a few kilowatts of power. So, you can see that there is a huge range of power spectra which can be covered by these types of turbines. But in if you look at aero engine in specific radial turbines as I think I had mentioned a few times earlier on they are not really used in the sense that the one of the main limitations of why radial turbines are not used is the fact that there are certain limitations on them how much temperature one can use in radial flow turbines when it is applied for a gas turbine application. Unlike an axial turbine which is relatively easier to manage temperatures by applying artificial blade cooling, we have already discussed blade cooling in a lot of detail earlier on. Now, blade cooling is not very easy to implement in a radial flow turbine which means that that puts a very significant limitation on the temperature which these turbines can be operated at. And that is the reason why that is one of the reasons why radial flow turbines are not very commonly used in gas turbine applications. But they are used in smaller aero engines where blade cooling is not really required because temperatures are not very high or of course they are used in hydraulic applications for even huge capacity power plants which generate hundreds of megawatts of power. So, radial turbines have as I said variety of applications and the inward flow turbine is what we are basically looking at because of the fact that these inward flow turbines have inherent advantages which is what I just mentioned. So, when we look at inward flow turbines there are again multiple varieties of inward flow turbines. We will look at two distinct varieties which have been used over the past many years and these are the cantilever type turbines and the 90 degree IFR or inward flow radial turbine. So, these are two distinct types of inward flow radial turbines, the cantilever type turbine and the 90 degree inward flow turbine. Out of this of course, we will spend the rest of the lecture discussing primarily about the 90 degree inward flow radial turbine or IFR turbine. Antilever turbine is in some sense similar to the impulse type turbine we discussed in detail when we were talking about axial compressors which means that there is hardly any change in relative velocity across the rotor and it is aerodynamically very similar to the axial impulse turbine and it is in fact, designed in a manner very similar to how an axial impulse turbine is designed. And so, cantilever type turbines are in some sense similar to the impulse turbine. We have discussed about impulse turbine in detail when we were talking about the axial turbines and these are very similar to that when it comes to the aerodynamics and the design of these turbines. And it is called cantilever because I will show you now that the blades of the turbine are actually suspended from one end and then that resembles a cantilever beam because it supported only at one end which is also true for axial turbine blades because the blades are actually supported only at one end. The other end has to be free for mechanical reasons. So, let us take a look at a schematic of a cantilever turbine. This is how a typical cantilever turbine would look like and so, there are two distinct views of this is the front view of the turbine showing the nozzles and the rotor vanes or rotor blades. So, the nozzle blades actually accelerate the flow and then discharge the flow in through the rotor blades and the flow leaves the turbine axially. So, you can see that it enters the flow radially it moves inward and that is why these are all inward flow turbines and then it exhausts the flow in the axial direction. Let us look at the velocity triangles velocity triangle at the inlet of the rotor or the velocity triangle leaving the stator here. Station 1 is the nozzle entry, station 2 is nozzle exit and rotor entry, station 3 is rotor exit. So, the flow leaves the absolute flow leaves the nozzle at an angle of C 2 and because of the relative velocity the blade speed u 2 the velocity which the rotor sees at its inlet is v 2 that is the relative velocity and the as the flow exits the rotor we have the flow becoming axial flow leaves the blades axially for nominal design condition v 3 is the relative velocity with which the flow leaves the rotor. So, you can see that at the exit of the rotor the blade speed has actually changed you have a different blade speed because of the fact that these two are at two different radial location something we have also discussed for centrifugal compressors u 2 would actually be greater than u 3 because the whole thing is rotating at the same rotational speed because of the difference in radius u 2 should be greater than u 3 and so the flow leaves the blades in the axial direction and v 3 is the relative velocity with which the flow leaves the rotor. So, this is the typical arrangement of one type of inward flow turbine that is the cantilever type turbines and the corresponding velocity triangles very similar to an impulse turbine that you have seen. So, in across the rotor v 3 and v 2 should really be the same it should not change as the flow enters and leaves the rotor the relative velocity does not change which means that the entire static pressure drop has actually occurred in the nozzle the rotor does not really contribute towards the static pressure drop and that is actually taken care of by the stator. Now, the other class of turbines that we are going to spend considerable time in of today's lecture is the 90 degree I F R turbine that is 90 degree inward flow radial turbine I F R stands for inward flow radial turbine and we are saying 90 degree because of flow actually takes a 90 degree turn as it passes through the I F R turbine. Now, these are turbines which are more commonly used for performance reasons that these turbines have much better performance and the design complications are also much more simplified. This is also true for impulse and the reaction turbines which we discussed for axial turbines impulse the reaction turbines can actually have much better efficiencies than the impulse turbine and we have seen even thermodynamically that makes sense. Now, in if you look at a 90 degree I F R turbine if you take a cross section of that this turbine looks exactly similar to that of a centrifugal compressor and so an I F R 90 degree radial flow turbine inward flow radial turbine has a very striking similarity to a centrifugal compressor just the fact that the flow directions and the blade rotation is reversed. In a centrifugal compressor the flow enters the impeller axially leaves the impeller radially and there is a certain direction of rotation whereas, in an I F R turbine the flow and direction flow enters the turbine radially and exits it axial axially and normally the blades are straight radial whereas, in centrifugal compressor we have seen that even it is possible to have backward leaning blades as well. In a turbine well it is possible to have that theoretically, but then the curvature of the blade is going to induce even more stresses and therefore, it is very uncommon to see curved blades for I F R turbines normally they are all straight radial blades and the rotor ends with the with what is known as an x-ducer. In a compressor we have seen that it has an inducer which turns the flow from axial to radial allowing smooth entry into the impeller similarly, in a rotor of an I F R turbine we have what is known as an x-ducer it is like it is exactly like an impeller inducer just that the function is different here it turns the flow from radial to axial direction and usually the flow passing through the rotor also exhausts into a diffuser which recovers part of the kinetic energy because the flow still will exiting the rotor will have a substantial amount of kinetic energy and if it is allowed to pass through a straight duct that kinetic energy is going to get wasted. So, that can be used to increase the overall work done by the turbine and so diffuser helps us in recovering part of this kinetic energy. This is also very commonly used in hydraulic turbines where they have what is known as a draft tube at the exit of the turbine they use a draft tube. So, the overall pressure ratio across the turbine is improved and that leads to an improvement in the overall work done. Let us now take a look at a schematic of a typical 90 degree I F R turbine and also the corresponding velocity triangles. Now, as you can see the first on if I had not written turbines here one would be one would possibly want to take consider this as a centrifugal compressor because it looks exactly like a centrifugal compressor, but of course the rotor rotation is different in a centrifugal compressor the rotor rotation would have been the other way round. In this case the rotation is this way as well as the vanes you can see it is actually the leading edge of the airfoil is towards the radial direction it would have been the other way round in a centrifugal compressor, but otherwise they look very similar to a centrifugal compressor. What are the different components of radial turbine? Radial turbine has a volute or a scroll as it is called in the turbine terminology scroll is like a volute or what we had seen in the case of centrifugal compressor in turbines it is usually called as a scroll. Flow from the volute or scroll passes through the nozzle blades which accelerate the flow and then allow the flow to pass through the rotor wherein the work is done by the flow on the rotor blades flow exiting the rotor passes through a diffuser. And therefore the flow enters the turbine in the radial direction and leaves the turbine in the axial direction it takes exactly 90 degree turn and that is why it is called a 90 degree IFR turbine. If you look at the corresponding velocity triangles now these are the velocity triangles for the radial turbine. Now this C 2 refers to the absolute velocity leaving the nozzle and then it enters the rotor blades at a relative velocity of V 2 and it is radial because the blades are radial and U 2 is the blade speed at the tip of the rotor or impeller. As the flow leaves the exducer here the relative velocity is V 3 and the flow is axial and that is why it is called C A 3 the flow leaves the turbine in the axial direction. The blade speed of course is lower here U 3 is less than U 2 because of the difference in radii between stations 2 and 3. So, this is how a typical radial 90 degree invert flow radial turbine would look like and the corresponding velocity triangles. What we are going to do next is to take up this particular turbine as an example consider the expansion of flow as it passes through this turbine and we will carry out an analysis of the flow as it passes through this turbine. We will also look at the governing equations with reference to a 90 degree IFR turbine of course this is also applicable to other forms of turbine with corresponding variations in the blade speeds and velocities and so on. We will also then look at the losses incurred as the flow passes through such a turbine configuration. So, if you look at a 90 degree IFR turbine the components that constitute this turbine basically include a nozzle, radial bladed rotor and a diffuser. For this analysis we are going to consider complete adiabatic expansion which means that there is no heat transfer across the walls of the turbine and the losses that we are looking at would primarily one of the components of the losses would be frictional losses and therefore, the entropy of course changes in fact increases in all the components. The stagnation temperature or enthalpy does not change across the nozzle or the diffuser because we are firstly considering an adiabatic flow and there is no work done on the system or by the system in the nozzle and the diffuser. So, there is no change in stagnation parameters, stagnation temperature and enthalpy in the nozzle and diffuser. So, let us take a look at the temperature entropy plot as we have been doing for all the other machines we have seen like compressor axial compressors and turbines and centrifugal compressor and we look at thermodynamically what is that is involved as the flow passes through these different components and what happens to the thermodynamic parameters and as the flow passes through these components. So, at a T S diagram for a typical invert flow radial turbine would look like this. Let me explain the different components associated with this particular T S diagram as we have seen before station one is the nozzle entry, station two is nozzle exit, three corresponds to rotor exit and four corresponds to the diffuser exit. So, if you look at the static pressure there should be a continuous drop in static pressure between stations one to two and two to three because as the flow accelerates through the nozzle and then subsequently in the rotor static pressure has to drop. Whereas, in the diffuser there would be a rise in static pressure as the flow passes between stations three and four and in the nozzle there is no change in stagnation enthalpy and temperature that is T 0 1 should be equal to T 0 2. Similarly, in the diffuser T 0 3 should be equal to T 0 4. So, let us take a look at the T S diagram again here T 0 1 is a stagnation pressure available at the nozzle entry. There is a certain amount of total pressure loss taking place in the nozzle due to frictional losses. So, there would be a small amount of pressure loss in the nozzle and then the corresponding static pressures are P 1 and P 2. So, there is a change there is a drop in static pressure. The actual process that is taking place in the turbine is indicated by this bold line between stations one to two and two to three and between three to four. So, between one to two is the nozzle and there is a drop in static pressure as you can see. There is also a drop in stagnation pressure because of the fact that there could be some amount of frictional losses taking place in the nozzle. But, the stagnation temperature does not change you can see T 0 1 should be equal to T 0 2 in the nozzle it does not change irrespective of whether there is frictional losses or not. Between two and three we have the rotor and therefore, there is further drop in static pressure between stations two and three. So, there is a drop in static pressure as you can see as the flow passes through the rotor. Between three and four is the diffuser and the diffuser the flow actually decelerates and therefore, the kinetic energy is partly recovered in the form of rising static pressure. So, there should be a change there should be an increase in static pressure between stations three and four which is why you can see that there is an increase in static pressure between three and four. On the other hand there could be a small drop in stagnation pressure in the diffuser and that is why p 0 3 and p 0 4 do not really coincide and there could be a small drop in the stagnation pressure which is attributed to the frictional losses in the diffuser. Now, but the stagnation temperature as you can see does not change in the diffuser as well t 0 3 and t 0 4 are the same. So, across the turbine there is a drop in stagnation temperature which is attributed to the rotor. So, the stagnation temperature that that you see is different that between t 0 1 and t 0 3 is because of the drop in stagnation temperature in the rotor which is basically the work done by the rotor. So, that is the temperature drop that is the potential which is converted by the turbine to useful work output. So, that is the enthalpy drop which the turbine is able to convert into useful work output and that is what we are basically interested in we are trying to extract work from the flow through this drop in stagnation temperature. So, what we will do now is to analyze the flow as it passes through the turbine and try to derive some equations which we can use to analyze the flow as it passes through the radial flow turbine. So, we will start with the nozzle now across the nozzle we know that there is no change in stagnation enthalpy h 0 1 should be equal to h 0 2. Now, therefore, the static enthalpy drop in the nozzle is h 1 minus h 2 there is a change in static enthalpy as we have seen the enthalpy between stations 1 and 2 there is a static enthalpy drop, but the stagnation enthalpy is the same and this static enthalpy drop is basically equal to the change in the absolute velocities 1 half of c 2 square minus c 1 square. And in a radial flow machine as we have discussed a few times earlier the rothalpy is conserved for an irreversible process, but an adiabatic process. The process could be irreversible which means that frictional losses are permitted, but it is adiabatic and in which case the rothalpy is conserved. And therefore, rothalpy is denoted by i this should be equal to h 0 that is stagnation enthalpy in the relative frame plus half u square which is the blade speed. So, for the if you look at the rotor since rothalpy is conserved between the inlet and exit h 0 2 relative minus half u 2 square should be equal to h 0 3 relative minus half u 3 square. So, this is that the inlet of the rotor the left hand side right hand side is the exit of the rotor. Now, we also know that h naught relative is the static enthalpy plus half v square where v is the relative velocity because this stagnation enthalpy we are defining in the relative frame of reference. Therefore, if you look at the static enthalpy drop in the rotor h 2 minus h 3 it consists of two components. One is because of the change in the blade speed between the inlet and exit and other is an account of the change in the relative velocity as it as the flow passes through the rotor.  So, this is the change in static enthalpy as the flow passes through the rotor. We will now look at the third component that is the diffuser and then see what happens to the flow as it passes through the diffuser. We will then derive an expression for this specific work done in terms of all these different parameters. Subsequently, we will define efficiency associated with such a turbine and then express efficiency in terms of parameters which we can derive from the velocity triangle that is the velocity components and the blade angles. So, what is normally done is that the irreversibilities are basically especially the nozzle irreversibilities are lumped together with frictional losses occurring between the space between the nozzle exit and the rotor entry. So, the irreversibilities are basically lumped together into a single parameter that we have just now seen. Across the diffuser again stagnation enthalpy remains constant therefore, h 0 3 should be equal to h 0 4 and h 4 minus h 3 you can notice that here it is h 4 minus h 3 and like in the nozzle where it was h 1 minus h 2 here it is h 4 minus h 3 because there is a static enthalpy rise this is equal to half of c 3 square minus c 4 square. So, the specific work done by the rotor on the fluid is between stations 1 and 3 that is delta w is h 0 1 minus h 0 3 and since h 0 1 is equal to h 0 2 we have h 0 1 minus h 0 3 as u 2 c w 2 minus u 3 c w 3. So, delta w that is specific work done is equal to we will express this in terms of static enthalpy. So, we have h 2 minus h 3 plus half into c 2 square minus c 3 square this again can be further written down in terms of u and relative velocity.  So, you can see that there are 3 distinct terms associated with specific work done and each of these different terms contribute towards the specific work done and this is true for a specific specifically for an invert flow radial turbine. And you can also see that the axial turbine in fact happens to be a special case of this where u 2 is equal to u 3 and that component becomes 0 and the specific work done is basically because of the other 2 components. So, delta w as we have seen the specific work done by the turbine has 3 components here half u 2 square minus u 3 square then the relative velocity change and the absolute velocity change. Now, for an invert flow turbine a significant contribution comes from this term that is the change in the blade speed and this is basically one of the reasons why invert flow turbines have an advantage over outflow turbines or outward radial flow turbines. Because here this contribution becomes positive in an outflow turbine this actually becomes negative and that is a big disadvantage for an outflow outflow radial flow turbines and that is why they are not being used anymore in practice. In an axial turbine this component becomes 0 and basically work done is on account of the other 2 terms. So, here what we have done is that we have basically derived an expression for the work done in terms of velocity components that one can estimate from the velocity triangle. So, once you know the velocity triangle the one which I had shown earlier could be used as a starting point to estimate these different velocity components and of course, the flow angles which would also be known for the design condition. So, what we are going to do next is to discuss about what is known as the nominal design condition and then subsequently the nominal design efficiency associated with a radial flow turbine. Now, nominal design is usually defined by relative flow of 0 incidence at the rotor inlet that is if the flow enters the rotor with no incidence which basically happens when the relative velocity is actually equal to the absolute velocity in the radial direction V 2 is equal to C R 2 and the other condition that is also satisfied is that the flow exiting the rotor is axial C 3 is equal to C A 3. So, when C 3 is equal to C A 3 then C w 3 becomes 0 that is the tangential component of absolute velocity at the rotor exit becomes 0 and therefore, C w 2 becomes u 2 and so the specific work done for nominal design would now become delta w is equal to u 2 square. So, it basically becomes a function of purely the blade speed at the rotor entry. So, we in an ideal scenario and when the turbine is actually operating in design condition with 0 incidence at the inlet and the flow leaving the rotor without any deviation then one can consider that to be a nominal design and the work done can actually be estimated merely based upon the blade speed at the rotor exit. We will also now look at specific terminology that is sometimes used in the analysis of radial flow turbines and that is basically which also will come up in our efficiency definition little later on and I am bringing up this particular aspect because in later analysis the this particular form of velocity is sometimes used in efficiency calculations as well. So, this is basically known as the spouting velocity and it has primarily been used in the hydraulic turbine context, but sometimes it is also referred to for normal gas turbine applications as well. So, spouting velocity basically refers to the velocity which has an associated kinetic energy equal to the isentropic enthalpy drop across the turbine. Now, depending upon how this is what kind of application it is one can define spouting velocity different ways either for a total condition or for a static condition. Spouting velocity we will denote this by C subscript 0 C naught and so this is basically half C naught square is either defined as H naught minus H naught 3 S S we will come back to this what this means for a total condition and if it is static condition then half C naught square is equal to H naught 1 minus H 3 S S. So, let us take a look at the T S diagram once again that I had plotted earlier now there are two distinct points you can see here which correspond to the isentropic enthalpy drop. So, the kinetic energy associated with this isentropic enthalpy drop is basically denoted by the spouting velocity. So, H naught 1 minus H naught 3 S S in one case and H naught 1 minus H 3 S S in the other case. So, these are the two definitions that one can have. So, the amount of kinetic energy that is involved in this much enthalpy drop between H 0 1 and H 0 3 for the isentropic case similarly, H 0 1 and H 3 S S that is for the static condition. So, this is basically defined depending upon applications whether the diffuser is used or not that is if kinetic energy is recovered then the flow basically reaches a static condition at the exit in which case one would define spouting velocity based on the second definition that is enthalpy drop from H 0 1 isentropic enthalpy drop being placed between H 0 1 to H 3 S and if it is if you do not use a diffuser which means that there is a stagnation enough stagnation enthalpy is still available at the exit of the rotor then one would prefer to use spouting velocity or define that in terms of H 0 1 minus H 0 3 S. So, this is one of the ways of defining kinetic energy and the term which is sometimes used in analysis of these radial flow turbines. Now, that we have discussed about nominal design point and conditions associated with nominal operation remember that the velocity triangles that I had shown for a typical radial flow turbine was corresponding to a nominal operation because there was no incidents at the inlet and no deflection at the exit. So, if you look at nominal design and try to define an efficiency for this particular design we can define efficiency we will define it first in terms of total to static efficiency that eta T S is total to static efficiency and. So, we have H 0 1 minus H 0 3 divided by H 0 1 minus H 3 S this is equal to the numerator is basically the specific work done delta w divided by the denominator we have specific work done plus a few additional components that is half C 3 square plus H 3 minus H 3 S plus H 3 minus H 3 S double S. So, this if you look at the velocity the T S diagram once again we will be able to appreciate that further the numerator is H 0 1 minus the stagnation temperature corresponding to that H 0 3 denominator is H 0 1 minus the corresponding static enthalpy condition and the other components are what have been added up here. So, delta w plus what you see here has been added is basically the difference between H 0 3 the point 0 3 here to the point 3 S S. So, this difference is what constitutes these three other components including half C 3 square the enthalpy difference H 3 minus H 3 S and H 3 minus H 3 double S. We will now define a few loss parameters let us define the passage enthalpy loss we will define that as a fraction of the exit kinetic energy relative to the nozzle and rotor rho this fraction we will denote by zeta zeta subscript r for the passage losses enthalpy losses in the rotor zeta subscript n for the passage losses in the nozzle. So, we will define these enthalpy losses separately for the nozzle as well as for the rotor. So, for the rotor we have H 3 minus H 3 S is equal to half V 3 square into the passage enthalpy loss that is zeta subscript r. Similarly, for the nozzle we have H 3 minus H 3 double S is equal to half C 2 square zeta n into the temperature difference that is T 3 by T 2 where T 3 and T 2 are the static temperatures at the rotor exit and rotor inlet respectively. So, with this definition of the passage enthalpy loss we will substitute these in the previous expression that we have written down that is for the total to static efficiency. And then if you substitute these values here we will get the revised formula definition for the total to static efficiency as 1 plus half C 3 square plus half V 3 square into zeta r plus half C 2 square zeta n into T 3 by T 2 divided by delta W raise to minus 1. So, delta W divided by this. Now, from the velocity triangles that we have seen for typical 90 degree IFR turbine we can also see that the velocities can be related based on two angles. One is the nozzle angle that is alpha 2 and the other angle is the flow exiting the rotor that is beta 3. So, based on these two different angles we can actually calculate the velocity components based on these different angles. So, what we will do is that in the efficiency definition we can substitute for these flow angles in the definition there and arrive at an expression which is primarily in terms of some of these parameters which are associated with the velocity triangle and the temperature ratio T 3 by T 2. So, from the velocity triangles we can actually see that a nozzle exit flow absolute flow that is C 2 is equal to U 2 cosecant alpha 2 and V 3 is equal to U 3 cosecant beta 3. And similarly, C 3 is equal to U 3 cot beta 3 and assuming that delta W is equal to U 2 square because for a nominal design the flow delta C W is basically equal to C W 2.  So, if you substitute all these different values in the efficiency definition here we have the total static efficiency in a very generic form 1 plus half into zeta n the enthalpy loss coefficient for a nozzle T 3 by T 2 into cosecant square alpha 2 plus R 3 by R 2 the whole square multiplied by zeta R cosecant square beta 3 plus cot square beta 3 inverse of this. Looks like a very complicated formula here, but this is a very generic version of the total to static efficiency definition that one can use and lot of approximations and simplifications to this formula is what have been used by the designers at a preliminary level to estimate the total to static efficiency. So, basically this involves a temperature difference between the nozzle between the rotor exit and inlet and the nozzle inlet angle and the rotor exit angle and as well as the enthalpy loss coefficients for the nozzle as well as the rotor. So, this can actually help us in estimating the total to static efficiency for a typical invert flow turbine configuration. So, the generic formula that I had derived is actually used in a variety of simplified versions by a lot of assumptions and one can actually simplify this further by calculating the temperature in terms of the velocity components and the blade speed. So, there is one more step that is involved if you wish to do that you can actually estimate the static temperature ratios T 3 by T 2 and express that in terms of the flow angles and the blade speed. So, that would complicate the formula even more. So, I am not going into that as of now. So, this particular efficiency definition what we will also do is to try and relate that to the total to total efficiency if one wants to use total efficiency as a performance parameter which is sometimes used especially in aero engine applications. Now, the temperature ratio as I was mentioning can be related to the blade speed at station 2 and the radius ratio as well as the flow angles. Now, if you were to relate the total to static efficiency to the spouting velocity we can also relate it in terms of the velocity components that you see here as 1 minus C 3 square plus zeta n C 2 square plus zeta r v 3 square divided by C naught square. So, if one can estimate the spouting velocity then the efficiency definition can be simplified further and now you can see there are three components of this efficiency definition one corresponding to the nozzle zeta n and the velocity zeta r for the rotor and the corresponding absolute velocity C 3 is the velocity leaving the rotor absolute velocity divided by the spouting velocity square. So, this is yet another way of expressing the total to static efficiency. Now, the relation between total to static and total to total we have already seen for an axial turbine. So, the very same relation also holds for radial flow turbine that is 1 by the total to total efficiency is equal to 1 by total to static efficiency minus C 3 square by 2 delta w where delta w is the work done by the rotor. So, this is basically relating total to static and the total to total efficiencies. So, what we have discussed now is about the the definition of total to total and total to static efficiency in a variety of different ways and based on this understanding let us also now take a better look at a closer look at the different losses and the sources of losses associated with the radial flow turbine. Now, there are different ways of representing losses which have been used by different researchers over the years we will look at two distinct groups one set of loss parameters associated with the nozzle another set of loss parameters associated with the rotor and then we will also look at the sources of these different losses in a general format. So, look at the nozzle loss coefficients there are different ways of expressing loss coefficients we have seen one of them that is the enthalpy loss coefficient that is zeta n which is basically defined as h 2 minus h 2 s divided by half C 2 square in some of the literature you might also come across what are known what is known as velocity coefficient phi subscript n this is defined in terms of absolute velocities C 2 divided by C 2 s and of course, the standard stagnation pressure loss coefficient which is denoted by omega n P 0 1 minus P 0 2 by P 0 2 minus P 2. So, these are three distinct coefficients or loss parameters which one would define for a particular nozzle configuration and you can actually relate some of these different loss parameters the stagnation pressure loss coefficient is approximately related to the enthalpy loss coefficient through the Mach number. So, omega n is approximately equal to zeta n into 1 plus gamma by 2 into m 2 square where m 2 is the absolute Mach number at the rotor entry which is basically related to C 2 and the temperature at the rotor entry. Now, we know that h 0 1 is basically h 2 plus half C 2 square where or this is also equal to h 0 2 and therefore, it is h 2 plus half C 2 square this is in turn equal to h 2 s plus half C 2 square s. Therefore, h 2 minus h 2 s is half C 2 s square minus C 2 square. So, we can actually relate these two different components that is velocity coefficient and the enthalpy loss coefficient through zeta n is equal to 1 by phi n square minus 1. So, the velocity coefficient can be related to the enthalpy loss coefficient associated with the nozzle and it has been observed that for a well designed set of nozzle blades during nominal operation the typical value ranges between 0.9 to 0.97 for phi n. So, the velocity coefficient ranges between 0.9 to 0.97 for a well designed nozzle row which is operating under nominal operation condition. We now look at the rotor loss coefficient we will define them exactly the same way enthalpy loss coefficient is zeta r h 3 minus h 3 s by half v 3 square velocity coefficient v 3 by v 3 s and this is related to zeta r the same way as we have done for nozzle zeta r is equal to half phi r square minus 1. In the case of rotor we have seen that it is notice that phi r ranges between 0.7 to 0.85. So, this is the typical range for the velocity coefficient for a nozzle and for a rotor. So, for a rotor you can see it is much lower it is in the range of 0.7 to 0.85 on the other hand for a nozzle it can be quite high between 0.9 to 0.97. So, these are some of the methods of estimating some simplistic loss parameters for nozzle as well as for rotor. There are other complex loss parameters which look at the sources of these losses which is what we will discuss little later now which also involves the 3 D loss sources like the leakage flows and secondary flows and so on. These are the parameters we just discussed are overall loss parameters which kind of puts all the other individual components of or sources of losses into a single parameter. So, in general if you look at the different sources of losses let us be specific for an inward flow radial turbine. Then the various sources of losses can basically be the nozzle blade row boundary layers, the rotor passage boundary layers then you could have tip leakage or tip clearance effects at the rotor exit. The disc windage that is the rotor surface itself can lead to certain amount of windage losses and the kinetic energy loss at the exit. So, these are the different sources of losses and the loss coefficients of parameters we just defined do not really look at these individual sources of losses and they are combining the various sources of losses into a single parameter for easiness of analysis. And there are of course, very complicated loss models which can estimate these different sources of losses and of course, that is out of scope of this particular syllabus that we are trying to cover here. So, we will not going to details of these individual loss models we just trying to take an overview of the different sources of losses. So, the knowledge of these different sources of losses are obviously, very significant in obtaining an optimum configuration for a particular design that is being attempted. One there is one more source of loss that I would like to highlight upon before I close this session here that is to do with the incidence effects. And when the turbine is operating at under off design conditions whether it is at a different mass flow rate or it is at a different rotational speed than what it has been designed for all of these constitute the off design condition. So, under off design condition there are an additional source of loss that comes into picture which is associated with higher level of incidence than the nominal incidence itself. So, at off design condition the flow is likely to enter the rotor at a relative flow angle which is different from the optimum angle. And this leads to an additional loss component due to incidence. And this is often defined as equal to the kinetic energy corresponding to the component of velocity normal to the rotor when at the inlet. So, what this basically does is that it leads to a corresponding increase in entropy and a corresponding drop in enthalpy due to incidence. So, enthalpy drop will directly correspond to a drop in work done by the turbine and increase in entropy leads to any drop in efficiency for the turbine. So, there are multiple effects here one is that it leads to a drop in the work output of the turbine. At the same time it also affects the efficiency which in thermodynamic sense is because of an increase in entropy. So, let us take a typical example of why this happens in a normal turbine. So, let us look at the T s diagram that we had discussed earlier. Now, at the entry to the rotor let us say the rotor has been designed for an angle of beta 2 which is the optimized beta 2 for a velocity which is V 2 relative velocity. And as the flow approaches the rotor because it is operating under off design condition the approach angle itself could be slightly different from what it has been designed and optimized for. So, the velocity approach velocity is at V 2 prime which is slightly different from V 2. And this leads to a certain amount of mismatch between the flow as it approaches the rotor and as it enters the rotor. So, there is a slight difference between the flow as it enters the rotor leading to a certain amount of incidence. And therefore, the flow enters the rotor at a slightly higher angle than what it was intended for leading to multiple effects in terms of loss in enthalpy and an increase in entropy and therefore, a drop in efficiency. So, this is usually termed as an incidence loss associated with an incidence angle which is greater than what it has been primarily designed for. So, let me quickly now wind up this lecture with a recap of what we had discussed in today's class. So, today's lecture was an introductory lecture on axial on a radial flow turbines. We discussed the fact that radial flow turbines were of course, developed in the early 1800s primarily for hydraulic applications for power generation from hydraulic applications. And of course, subsequently they were they have evolved and they have been used also for other applications like gas turbine engines and so on. And so, we have seen that there are two different classes of radial flow turbines either the outward flow turbines or the inward flow turbines. Inward flow turbines are have inherent advantages which is why they are used over a wide spectrum of power output ranges like they are used in hydraulic power plants where they develop something like a few 100 megawatts of power all the way to very small gas turbine engines where radial turbines are used which generate a few kilowatts of power. So, they have a very wide spectrum of applications. In the inward flow turbine we have seen there are again two classes of turbines one is like the impulse flow turbine these are also called cantilever flow turbines and the other is the 90 degree inward flow turbine which is what we had spent lot of time discussing about that basically a reaction turbine and where there is contribution from the nozzle and the rotor in terms of static pressure drop and work output of the turbine. We then discussed in detail the governing equations of flow as it passes through these different components from the nozzle through the rotor and the diffuser and how we can estimate the work output based on the flow these this analysis. We also discussed about the efficiency definition in quite some detail and expressed it in different forms including the spouting velocity definition. We also discussed in little bit detail about the various loss mechanisms and how one can estimate the loss in a very general sense losses associated with the nozzle and loss parameters associated with the rotor. So, we covered these different aspects of radial flow turbines in today's lecture starting from an introductory part towards the thermodynamic analysis and also the different sources of loss and the components of losses in radial flow turbines. So, we will continue with some more aspects of radial flow turbines in subsequent lectures as well.


The opponents the Tampa Bay Buccaneers on their way to town Titans trying to get to four and four with a second straight win Let's take a look at Mike Vrabel's keys to success and we began with Past defense they're throwing the football. They're throwing for almost 300 yards a game You know, we have to continue to you know combine the pressure with the coverage They've given up 25 sacks. You know, we have to continue that trend. We have to affect the quarterback. We have to get on Evans, you know, we have to hit plan for these guys. These guys are elite receivers Godwin very productive guys. I think they both each have 51 target each That's a lot of targets through six games red zone. Obviously going to be a factor in this one for both the Titans offense and defense Yeah, it's somewhere, you know, hopefully we can take advantage of it. They've been giving up some points right now That hasn't been something That's been a strength of theirs. We have to try to continue where we left off last week in the red zone three for three And again, they're they're scoring points, you know, they're scoring a bunch of points are almost scoring 30 points a game So we're gonna have to be great down there in the red zone on both sides of the football Finally Tampa the number one run defense in the league Titans still have to be able to run the football Yeah, I mean, you have to you have to stay balanced and it's gonna be a huge challenge and a great test for us To be able to try to run the football to create some balance to create some opportunities to to throw the football and off also, you know, that's that's the way we get our guys involved and They're really good at stopping the run and that's gonna be something that we're gonna have to practice hard at Tampa's defensive coordinator Todd Bowles outstanding. Very good football coach understands defense and Historically, he's he's given a lot of offenses some problems. Let's get another win on Sunday. Okay All right, let's see those Titans fans there at Nissan Stadium reminder tickets available at Titans online comm slash tickets If you can't be there make sure and listen on Titans radio Titans countdown is on the air at 11 a.m. And again, it is a noon kickoff the Titans in the box the last Sunday in October at Nissan Stadium from Mike Vrabel Mike Keith says good night, everybody


Okay, welcome back to SiliconANGLE and Wikibon's exclusive coverage of Sapphire Now. I'm John Furrier. I'm General David Floyd, the co-founder and CTO of wikibon.org. And we are here at SAP Sapphire, their annual event. Sapphire Now is the hashtag. Tweet us if you have any questions at Furrier. I'm happy to answer them for you. We are on the ground in the Global Communication Center in Orlando where all the action's happening. Press conferences, we're talking to the CEOs of SAP. A lot of their executives, customers, partners, and developers. We got them all here covered here at theCUBE. This is our flagship program. We go out to the event, extract the signal from the noise. Here with David Floyd. And we're going to view a deep dive here, David. David, you've been following research for the folks who don't know. David Floyd is the CTO, co-founder of Wikibon. Leads the research agenda on all our deep analysis on pricing, economic models, what's going on in the industry. More importantly, he's been leading the efforts with our software-led infrastructure research agenda. David, welcome to the segment. Thank you. We are going to go into a deep dive here on the virtualization aspect of consolidation. Obviously, consolidation's been a big part of the world. So just go in and give us an overview of what we're going to present here. And then we'll just dive right in. What's the background to this? Yes. Well, what's of great interest these days is the whole of software-led infrastructure and consolidation and virtualization. So what we looked at previously, the consolidation of Oracle. We wanted to take that one stage further and look at the value of consolidation, not only of Oracle, but of the application on top of Oracle, in this case SAP, very appropriately as we're here at Sapphire today. So while we're looking at, and we talk to a number of customers, or SAP customers, and looked at how they have gone about the issue of consolidation and virtualization of SAP. So what we looked at is the business reasons why they're looking at it and the technology foundation that they use to consolidate everything. The interesting thing is that the business reasons were the real reasons why people were doing this. We talk today, for example, we talk to West. And the infrastructure people were given their orders to make sure that they got this done in six months. The value of doing the business side of it was so high that they really pushed IT to get this implemented in record time. We talked to SAP at EMC today, what they were doing. And they were doing the same thing and a consolidation for business reasons. In this particular case, they took them 27 months. But that's still a very, very accelerated. And not only did they do the change, the IT change, they also did the business changes as well. So what they were trying to do with SAP is go towards a global single instance, a single version of SAP for all of the, in some cases, it was divisions. In other cases, it was the different countries. And in the case of EMC, it's both countries and divisions. And they were putting on to them a single version of the financial environment and the operating environment that SAP is giving them. That single version, the whole objective then is that they can have very quickly, for example, a single version of the backlog or the single version of the financial situations. And then you be far more effective in using that data and far less people, less movement of data from one system to another system. So that was the business reasons behind most of these migrations. The second piece is how they chose to integrate it, the platform they chose to integrate it. And all these examples chose to integrate it onto an Intel platform, the foundation, and to virtualize it, both the applications and the database and the SAP itself, virtualizing all of this to create a far more flexible version of the infrastructure. David, I've got to ask you, what was the reasoning for the research? Was it to really kind of understand the alternatives to Oracle, because you mentioned Oracle. Obviously Oracle, there's a lot of customers who are looking at moving off of Oracle or staying onto Oracle. I know you're doing some work there. But SAP's business model is a bit more broader with cloud. We've heard from EMC and VBlock and other folks there. A lot of different moving parts. So how do you frame the research? And who is it applied for? What group use case in particular? Well, it's applied for our members, the Wikibon members. So we are looking at ways that we can help them look at, first of all, the reasons why you would want to create a single platform. And secondly, what are the technology implications of doing that? What is best practice? What is the best design of system towards that? And sharing that with our members, sharing that with the people who are doing this. So that's the fundamental reason why we're doing this research and the fundamental reason why we're doing all of this type of research. Is there an environment for a customer environment that makes more sense here? I'll say it's SAP. But is there a specific configuration, infrastructure, scenarios, and some of those variables? What are those key variables? Well, the key here was consolidating SAP itself into a single global instance, or reducing the number of these very significantly, as well as consolidating it on a modern virtualized infrastructure. So those were the two parameters that we had in selecting who we talked to. And that's what we believed was fundamentally best practice, anyway, were those two environments. So that's essentially what we chose. And for a single instance of a very small SAP environment, probably the value of making the change is not that high. But for most SAP environments, have grown slowly over time. There are multiple instances. For example, in one customer, we had one version working on HP 3000 and another piece working on IBM i-series, all over the place, all these different versions. And bringing those together, consolidating them, made both IT sense and it made business sense. And the reason why these get out of control over time is you put these different instances in, you have a whole lot of applications moving data from one place to another. Most of the applications are not with end users, but they're moving data, transforming data from one place to another. Band-aids, if you like, on this complexity that's behind the scenes. What we heard from EMC, for example, is that they reduced the number of those applications from 500 down to just over 100, a fourfold reduction in the number of those applications. And that leads to simplification of the environment. It leads to higher availability. It leads to much faster ability to make change, agility to make change in the future. What are some of the cost numbers that we look at? Can you just walk through some of the savings? Sure. Well, what I've done is to break those down into three. One of which is, what's the IT value? And the second is, what is a low end of the IT and business value? And the third is a sort of more normal, a higher end of the business value. So if we look at slide one on the system, then what we've got here is the first column is the current and I've normalized that to a hundred. The second column is the IT costs of the system once it's been virtualized and centralized. And the third column is the savings. So what we can see in the elements that we're looking at. Just walk through the colors and what the legend is in case they can't see it on the screen. The first column is the operations cost, that's the people cost, that's the purple color. The green color is the cost of the SAP software and the orange color is the cost of the Oracle licenses and the blue is the cost of the infrastructure. So what you can see here is that the biggest single cost is the Oracle license cost. And by going towards a virtualized infrastructure, you can optimize your environment for this optimize it and virtualize it. You can reduce the hardware costs, you can reduce the Oracle costs. The SAP cost doesn't, it's a very slight reduction in that but not very much at all. And you can reduce the infrastructure, the infrastructure cost, the hardware cost and the people cost. So all of those reduce and you can see the savings. As you said, the SAP savings are very small. The Oracle savings are the biggest and the operational savings are the biggest. So that's a very clear saving. You obviously have to put effort into that saving. So the return would be about two years probably if this was done for IT reasons. Return or payback? The return, the payback period would be two years. So essentially SAP gets a little bit of savings but because of their business model but Oracle really takes the big hit. Oracle takes the hit and the operations people take the hit. Those are the two big. So that's the innovation and opportunity. Yes, yes. The hardware cost, you save something but that's not really what you should be focusing on. It should be the Oracle savings and the hard. Well, it's inherent hardware cost with savings with the virtualization but also there's some growth too, right? They can eat, but they don't have to replace all their servers. No, no, no. This works focusing on the servers for SAP. Got it. Which often have the latest hardware anyway because it's large database. Great. So if we go to slide two, we see the same set of numbers in one and two but this time we're looking at the savings from the lowest level of saving which would be, for example, the saving of financial analysts to analyze the data. It's the low level savings for the business. What is that, the orange? That's the orange piece over here under the savings piece and you can see already, it's about the same size as the IDT. But it starts out as zero? Well, the first one was just saying just IT. Okay, got it. And this one is saying, okay, now let's add on the business benefits and the business benefits here are simple. They are just the business benefits for the simple savings of lower number of people, financial analysts, for example, at the end of the month because you have a single instance, you don't need somebody from each of the countries to be doing that, for example, and rolling it up and sending it off. So operational efficiency in the business side? In the business side, on the business side. That's net new savings that's kind of incremental. Exactly, but that's a sort of minimum, that's not really a game where the savings are. Got it, yeah. So if you go to the third one, you're looking at now the true benefit of that and the customer today said that their objective of doing this whole exercise was to increase their revenue by from 1.4 billion to 1.2 billion to 1.4 billion while keeping their people costs constant. So they wanted to grow that. And if you look at that growth as a percentage of IT spend, that's about five times the total IT spend, and if you look at the proportion that's dedicated to the ERP systems, that's probably 10% of that. So you're talking about some really high multiply here of 25 to one on the investment that you're making. Okay, so pretend for a minute that I don't know what I'm, that I don't understand the charts. The blue piece.  I am, but no, I know all seriousness. So that number is significant. That new blue chart is a maximum. Explain that piece. So that piece there is the business benefit of a reasonable investment to the business, the value of this investment. Which includes new revenue. Which includes making, for example, the people that you save in the business as a whole. Because you're able to run the business on a fastest turnover cycle, the EMC guy today, Bill Reed, he was talking about, for example, knowing exactly the financial state. Knowing exactly any business that was in progress at month end so that they could apply that business or not to decide about it. So it's execution efficiency as well. Execution efficiency, more revenue from the people because they can direct them more effectively. Not having a meeting to figure out what's going on, just kind of that lag that goes on from the... Absolutely. So both EMC and the guy from West were talking about very significant increases. Now these don't happen on day one. So this is the end point of where they're going to get to. But the point is that those are very, very big numbers indeed with very high return on investments. So for example, it makes every sense to try and get this in as fast as possible. If you remember when we were talking to the West people, they wanted that in in six months. Why? That's the reason. That's huge. It's one of those things where, as we always talk to customers and people talk about new solutions, it's always like, oh yeah, we can save you on the hard costs. But then there's the untangible business benefits that you're talking about. It's always like the customers know. They get a feel that it's the blue sky. We know when it's not raining. We know when the sun's out and things are happening in a good way. That's really what you're reflecting in here, right? That kind of value where it's obviously been a project. The business value delivered in terms of increased revenue, reduced risk, reduced costs. So let's tie that together with Sapphire because obviously this is very relevant here at Sapphire. The reason why we wanted to go through this was whenever we talk to the executives at SAP, we always ask them questions about speeds and feeds and technology, how can I do this and this can do that. And they automatically, it's like a script. They go right to business benefits. So talk about what you see here at Sapphire, hearing some of the CEO's talk about some of those business benefits. We hear mobility, we hear agility, analytics. So how can you tie this to some of the specific points that they're making here? Well, one good example is the points they make about HANA and why it's important. They are emphasizing that HANA enables them to make decisions in real time. They're analytical decisions on the SAP data, being able to get that up into HANA and decide things in 20 seconds instead of two days or 20 days, which was one of the examples given today. So you asked that great question.  And he said, was it 25 seconds from 25 days? Yeah, 25 days to run a report to 25 seconds. I mean, it's earth-shattering. So the point is that it goes from looking at it a month later and being a long-term project. Well, we asked Wes Pharmaceuticals, who came on theCUBE, a customer of SAP, came on and we asked him some of those things and he goes, he literally said, quote, people aren't standing around. Standing around is reflected in that number. That's right, because they're doing something more productive and they're going out and we can direct them. And they get the normal savings, check the boxes on, okay, we knocked down a few servers, we've got some operational efficiency. So Oracle License, we've heard that one, kind of the old model to the new modern era of, hey. We can make those savings, yes. Those are legit, those are legit. Those are legitimate savings. But the real reason that you're doing it is not for savings, it is because you're virtualizing it, you can bring up new instances quicker, you can put in a production system more quicker. You don't have to go through all the testing of a new version against everything else, the regression testing, that's all done as far as a converged infrastructure. It's all of those things that's around. Is that why we're hearing EMC talk about this co-innovation with some of their partners? We've heard from CSC, we've also heard from some of their customers about this integration testing center of exit. Is that why they're doing that? Absolutely, because you and I know from our previous lives that life in an operations room, when a new version goes in, is difficult. You have to test everything. You have to test the network if it's changed. You have to test the servers of the new version of it. A microcode goes in. There is often a long testing process which can take three months at least before a new version can go in, just to make sure it's working correctly. If you reduce the number of working parts and if you then can look at the fewer number of working parts and work with SAP or Oracle, you can have a much, much smoother and faster introduction of the changes that matter. This is amazing research. David Floyer from wikibon.org, really laying out what is essentially data around why people are so excited about the business value conversation. And I think just my observation and I want to ask you a specific question around this is this is why we're seeing a lot of investment in IT right now. We're seeing a lot of investment saying, hey, the cost to run the business as Dave Vellante always says is 70%, 30%. They want to shift that number down. So yeah, operational costs can drop down but this is really around investing in the business. That's why there's mobile apps. That's why analytics are hot. CIOs and CEOs and lines of business know the business value of using technology. So that's clearly this is a key part that speaks to that in my opinion. So my question to you is you talked to a lot of companies out there in your research. What are you hearing about them? Given the context of what I just said, what are some of the conversations that you're hearing around that blue area, that new savings? Well, there's two answers to that question. The one is that they want to reduce the complexity of their IT systems. And one of the areas which is hidden, people are not seeing it. But one of the enablers of this type of consolidation, remember you're taking 20 different systems and putting them essentially onto one system is that things like flash are a key component of doing that. Because otherwise the IO, the slow IO would actually cripple your ability to do that. So the modern systems, we talk to the VCE, for example, but the modern systems have large amounts of flash in them to do this. So that's something under the covers which meant that it was difficult to do before. But the second thing is they do want to reduce the complexity of their infrastructure and remove the applications which aren't adding value, get rid of those, replace those. The third thing they're looking to do, and this is coming from a number of people, is looking for ways that they can put stuff out into the cloud. Use Amazon, for example, use CSC, use any of these people to push some of their stuff out into the cloud. It makes more sense for a lot of stuff, for example, especially if it's coming from the internet and you're analyzing the internet, social data and things like that. Providing that as a cloud service makes every benefit. So on the technology side, there's a trend towards abstraction, abstracted databases, creates some simplicity around the platforms to enable, as Dave Vellante says, the API, the data center is now the API and developers are now hot. That's kind of the technology, kind of under the covers as you explained. The DevOps are now hot, yeah. The DevOps, right? So that's kind of going on. But above that, why do you think the CIOs are now running hard to get to those savings? What do you personally think is the real catalyst as accelerating the investment and accelerating the mindset of saying, hey, we're not going to be afraid? I think that's slowly happening and I think it's going to accelerate extremely quickly. And the reason is that if you have an infrastructure which can change faster and can deal with a single instance of the truth that you like about an organization and can analyze far, far greater amounts of data, if you have that sort of environment, you are able to improve the value that you can deliver to the business from IT and improve it very significantly. What we did some time ago was look in detail of what happened when a small distributor of electrical stuff went through this process and took their ERP system and made it totally integrated on a single database. The result of that was around a 20% improvement in productivity for the company as a whole. And they ascribed about 10% of that to IT itself. That is an enormous increase in value to that organization from being able to run the system, run the company faster, being more agile, being working together. That was over a 12 month period, 18 month period. That's an enormous return. And I think companies are starting to see that hyperscale, flash, software-led infrastructure, all of those major trends are starting something very big off, which is the ability to fundamentally improve by 20, 30% the productivity of a company and the ability to go after new ways of doing business, new ways that they can do things. We had today, didn't we, about a public transport system that was now making money from selling advertisements to the riders on that system. That's innovative. That's disruptive. That is essentially taking a product that was built for something else and turning it into a new opportunity. A new revenue stream coming into them, and they are the people that are driving it. Well, I think, you know, I'm sure you didn't think about that when you did your analysis, but if you add that into the mix. Absolutely. Your chart explodes. Explodes, that's right. That's even more nebulous to get your arms around. So, you know, I think it's still understated. Great research. David Floyd are actually quantifying and putting a framework around what is the top conversation at Sapphire here is the business value equation. And that's obviously two parts. Technology, simplicity around technology and deployment, integration. And then the second big part is show me the money. And now, ultimately, the business benefits is what drives a lot of these big companies. And SAP certainly is doing very well with that. For more information, always look at this video on youtube.com and let us look at an angle and go to wikibond.org and search for the research. It's going to be out there. It's all free. We're proud to present it here at Sapphire with our exclusive coverage here at Sapphire, presenting the latest research and numbers in quantifying the business benefits around virtualizing SAP. And it's amazing. So, David, thank you very much for presenting that. We'll be back here live from Orlando in the Global Communications Center at Sapphire now, right after this short break.


What is going on guys welcome back to the channel critical overlord here So we kind of now have an understanding of how the staff franchise will factor into the upcoming screen 5 I know a lot of you guys have speculated and wondered how will they use the staff franchise in his upcoming new entry I've talked about it talked about this in the past Maybe we get a stab film based on the events of screen 4 that doesn't appear to be happening Doesn't mean it's not going to actually happen Just no word yet on that we do now know that the staff franchise will at least get mentioned or make some sort of Appearance thanks to a recent interview with AV club that Heather Graham had you know Heather Graham She was the on-screen Casey Becker that we saw in stab 2 or not stab 2 in scream 2 in the opening when Marine and Her boyfriend were getting killed at the stab pre screening She had a recent interview where she talked about her time on set and she stated that it's funny because they just sent Me that clip because they're using it in the new screen and I had to I guess approve it or allow them to use it So I just rewatched it and I'm wearing that wig kind of what Drew Barrymore here was like and I'm like cute wig I want that wig now So before that they were just talking to her about how she about her time in the film And if that was just like a quick thing for her to do and she was going on and on about how she was very Honored to be a part of it and just it was a good opportunity to work with a lot of famous people like West Craving yada yada yada But then that last bit of course is what we're gonna talk about she mentioned that the stab film is gonna make some sort of appearance a Clip regarding her anyway is gonna make an appearance in the screen fire We're gonna get in 2022 from spyglass media from the directors of ready or not and paramount pictures, so That's all we really know as far as like how the staff franchise will factor into it We know that we're gonna at least get that clip now Honestly as far as like how that clip is going to be used That clip is probably going to be used at a party similar to What we saw in the past With other with the with the first scream how they were watching horror movies at a party There's probably gonna be a party and then one of them will probably be watching this stab film And that's when we'll see Heather Graham's Casey on screen again So at least it's good to know that the staff franchise is not completely dead in this new entry I know that was another concern. I saw people speculating about one of the staff franchises never even it's not even mentioned What if it's just ignored? Honestly, I know a lot of you actually we're getting sick of the staff films Particularly with screen for screen for his opening. I I think it's clever But like at one point it became like okay when it was a when it was a fake opening For the first time I was like, okay, then when she stabbed her in the stomach and it was another I'm like, okay And then now okay now we're actually getting the opening like okay. Thank you honestly the opening with The the opening in the stab film from the in screen for with Lucy Hale and I can't think of her name But she was in the grassy I can't think of the actresses name at the moment but she played Darcy in the grassy the opening with Lucy Hale And the actress from the grassy that was a better overall opening when they were both They both got killed and Lucy ran out the house got her throat slit. That was a better opening than what we actually got With the actual opening from screen for I wish that had been the full-fledged opening and that that was the actual opening for the film because what happened afterwards I thought just was very like lukewarm and kind of like meh but yeah, the staff franchise will appear and Ultimately, it's just gonna be this clip of hella grams Casey in some capacity once again Now whether or not they will do anything else with the staff franchise in this upcoming entry We do not know we'll have to wait and see I do believe that this will be the only mention of the staff franchise that we get outside of You know just them Possibly bringing it up, you know that we'll probably have our film geeks and our film nerds and our horror buffs from the group of The new actors and actresses that we have on board who love the staff franchise and they'll talk about it and Then they'll watch the first film at a party later on in the movie That's honestly how I see this how I see this clip being factored in and if this is the only mention we get of the staff franchise I'm fine with it because I thought honestly scream to scream to okay That was a nice clever little introduction to this stab series scream 3 Again, they kind of took it overboard a bit in screen 3. I thought honestly that The whole the whole stab thing while it was a nice touch certain elements of it were just Like overkill like okay, we know we have this universe that's based off of a film series that we're actually watching that in itself is fictional, but The way it just kept getting brought up with each seat each sequel now's gonna get brought up again I'm glad it's I hope it's a more toned down Mention of the of the franchise honestly because it's screen 4 overkill. We got those two fake-out openings We got stab a thong.  So and I've even speculated about stab fanatics being the killers in this film I don't even want to see that anymore. I just feel like after recently we watch rewatching the scream series. I Love it to death, but I feel like with the stab franchise That was one of the things that they kind of just they took it a bit too far It was it was nice and clever in screen 2 screen 3 it was kind of just like okay Why I get it it factored into what was going on with Marine Prescott But then it's just like with each subsequent sequel after screen 2 with 3 and 4 The exposure of that franchise was just becoming more and more like woven into the fabric of this of this universe And I could live without the stem stab franchise being such a crucial part of this because it's it's not It's it's not to us because that's not that's not the actual thing that we're watching We're watching what we believe to be relevance Per what's happening on our TV screens, and they're watching their franchise.  I don't care about stab So if they're just gonna have this one clip with Heather Graham at a party or something I'm cool with that But if they mentioned the stab franchise and if we get you know Some mention of them doing a reboot or something about canceled sequels that have come and gone and they've never They've never come to fruition and like the slight little nod to a lot of other franchise that have been in limbo other horror Franchise that are currently in limbo in our current reality. I'll live with that but The overexposure and you know the going on set of one of the productions of a stab film I can live without that. I can live without it. I talked about it in previous videos I know but the more I think about it I I can live without the stab talk in this movie So whatever happens and however this clip gets factored in again I am not stating that that's officially how it will be utilized because she did not say that in the interview herself I don't know what they'll do with it. I expect it to just be a clip that'll be shown at a party So I know that a lot of you were looking forward to seeing how the stab franchise will be utilized This is so far all we know But let me know what you guys think about all this down the comment section below If you haven't already of course, you can go ahead and make sure you subscribe Turn on post notification at never miss a video in the description I have links on my social media accounts on my Facebook Twitter and Instagram you can message me there of course Let me know is any movies news or views you like me to cover in the future thought into mine guys I will see you in the next video


Welcome to English in a minute. From home. Nuts are a healthy, tasty food. So why is it bad to drive someone to them? Jonathan, do you have time today to help me with some bread? Anna, I can't hear you. What is that noise in the background? It's a leaf blower. My neighbor uses it every day and it drives me nuts.  What? In this case, nuts means a little crazy and drive means to make.  We mostly use this expression for not so serious things. And that's English in a minute.