# Applied Thermodynamics for Marine Systems Prof. P. K. Das Department of Mechanical Engineering Indian Institute of Technology, Kharagpur

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1 Applied Thermodynamics for Marine Systems Prof. P. K. Das Department of Mechanical Engineering Indian Institute of Technology, Kharagpur Lecture - 12 Steam Turbine - Impulse Good afternoon. We were studying the analysis of impulse turbine in our last class and I like to do a little bit of recapitulation of that topic. Then we will proceed with the further analysis. In an impulse turbine there will be two important components, one is a nozzle and another is the impulse blading. (Refer Slide Time: 01:28) If we see a schematic representation of the impulse turbine, it is something like this. There is a nozzle through which the steam is flowing and when the steam flows through this nozzle, there will be a drop in the pressure and there will be increase in velocity. Then, this steam will pass through the blade passages of the impulse turbine. I have shown two rows. This is the row for the nozzle and this is the row for the impulse blading. This is a stationary row where a number of nozzles will be there. This is a row of moving blades where a very large number of blades will be there and that will be rotating as they are mounted over the turbine drum or turbine disk. 1

4 the direction of rotation. Joining these two, we will get the absolute velocity at the exit that is V 2. This is beta 1 and this angle is beta 2. One is blade inlet angle and another is blade outlet angle. We have got another representation of different components of steam velocity, when it enters the blade and when it goes out of the blade. This is basically a triangular representation. The top triangle is known as an inlet velocity triangle and the triangle at the bottom is known as the exit velocity triangle or outlet velocity triangle. These two triangles can be superimposed over one another because they have got a common component that is V b. If we do that, then, other analysis will follow from that combined velocity diagram. The combined velocity diagram can be drawn like this. First, let us draw the common velocity component V b. We will have the inlet velocity triangle like this. This is our V 1, this is our V r1 and this is V b. We will have beta 1 and this is alpha. Again, let me repeat. Beta 1 is the inlet velocity angle and alpha is known as the nozzle angle. We can see from the geometry alpha is smaller compared to beta 1. We can draw the other velocity triangle that means the exit velocity triangle. We will have something like this. This is V r2, the relative velocity at the exit. This angle is beta 2, this is V b and this is V 2 absolute velocity at the exit. Another angle has to be defined. So, let us say this angle and let us give a name delta. Now, we can define a few more things, let us do that. If I project the vertical lines from the apex of these two velocity triangles and join them, the quantity which I get is denoted as V omega. This is known as?... component of velocity. Again, this can be divided into two parts. Maybe if I use another colour, it will be better. This I can call as V omega1 and then this I can call as V omega 2. Similarly, I can have V a2 and V a1. So V a2 or V a in general, is axial velocity or axial component of velocity. V a1 is the axial component of velocity at the inlet and V a2 is the axial component of velocity at the outlet or exit. If we imagine the steam turbine, there is a turbine shaft. The shaft axis is the axial direction and this component of velocity is in the direction of the axis of the shaft and the. component of the velocity that is tangential to the shaft or to the shaft axis. If we try to imagine the turbine, then these are the physical directions of these two components of velocity that is. component of velocity and axial component of velocity. The geometry is basically there are two triangles. We can use the basic laws of geometry and can get the relationship between different components of velocity. We can do this in a minute. Let us see what type of relationship we will get. 4

5 In this diagram, I would like to make a small change. Generally this is a difference. We want to put this as delta V w or the difference between V omega1 and V omega2. Let us see how we get these quantities. (Refer Slide Time: 17:34) Let us see V omega1. What is V omega1? If we see this, V omega1 is nothing but If we see V 1 and project it on this plane then we get V omega1 and this angle is alpha. So, V omega1 will be V 1 cos of alpha. Now, let us determine V omega2. 5

6 (Refer Slide Time: 17:52) What is V omega2? If we see this is V 2. This angle let us call it any name, let us say it is Z. If we take V 2 cos Z then we get V omega 2. V 2 cos Z, if we write this is V 2 cos of Z. (Refer Slide Time: 18:19) We can write V 2 cos of, from this relationship, 180 degree minus delta, cos 180 degree minus delta. So, what we will get? We will get minus V 2 cos of delta. The magnitude of V omega2 will be V 2 cos delta. And then what can we get? We can get delta V omega is equal to V omega1 plus, 6

7 magnitude wise it will be plus, V omega2 and then we can write it will be V 1 cos of alpha, then minus of minus V 2 cos of alpha. According to this diagram, which I have drawn it is like this. Basically we can put V 1 cos of alpha plus V 2 cos of delta. (Refer Slide Time: 20:31) Here, I like to tell you, that we have drawn a particular diagram where delta is an obtuse angle. It need not be an obtuse angle always. Delta need not be an obtuse angle always. The value of delta depends on the value of the relative velocity, the blade velocity and the blade angle, outlet blade angle. In some cases, it can be an acute angle or in some cases, it can be 90 degree also. But, this relationship we can use always; irrespective of the magnitude of delta you can use this relationship always. 7

8 (Refer Slide Time: 21:10) Basically, delta V omega is equal to V 1 cos alpha plus V 2 cos delta; the way I have drawn the delta. If we draw or if we denote delta in the same manner then we can use this relationship. We can determine also the inlet blade angle. (Refer Slide Time: 21:55) The inlet blade angle if we see, the inlet blade the angle is given by beta 1. We can get a relationship like this - tan beta 1 is equal to How we can get? This is V 1 sin alpha is this one 8

10 In other words, the relative velocity here V r1 will be equal to V r2 if there is no friction in the blade passage or the blade passage is smooth. If there is friction in the blade passage, then V r1 is not equal to V r2. In general, there can be some friction. So, that is why we defined a factor K b, which is V r2 divided by V r1. If this is 1, then there is no friction and inlet relative velocity is equal to the relative velocity at the exit. If there is friction then the relative velocity at the inlet and exit are different. From here, we can also determine what the frictional dissipation is. The frictional dissipation, the kinetic energy which will be lost due to friction, that is equal to 1/2 V r1 square minus V r2 square. This is per unit mass flow of steam. Let me write loss in kinetic energy due to friction. Due to friction, this will be the loss in kinetic energy. (Refer Slide Time: 29:42) Once we have introduced this K b we can write delta V omega - this is a vector quantity, it has got a direction. This quantity can be written like this: V 1 cos of alpha minus V b. All are vector quantities, these velocities, 1 plus K b. Now, this needs a little bit of derivation but that derivation is easy and I am leaving this derivation to you. If you try with the combined velocity triangle diagram, what one has to do is this V 1 one has to change it to V r1 and V 2 to V r2. Then one can introduce the relationship between V r1 and V r2, bringing this K b. Then one can get this relationship. This I am leaving to you. This derivation you can do easily. 10

11 Then comes the important parameters. Next, we want to determine what the tangential thrust is. The tangential thrust this is generally thrust. It is nothing but a momentum and it is denoted by P; as it is in the tangential direction we call it P t and this P t is change of momentum in tangential direction. A change of momentum in the tangential direction means, again, let us go back to this basic diagram. Here, steam is entering with a velocity V 1. It will have a component in the tangential direction. This is the tangential direction; so, V 1 into cos of alpha in this direction. Similarly, when it goes out it will have a component in the tangential direction and if we take the difference between them then we will see what the change in velocity along the tangential direction is. That multiplied by the mass flow will give you the momentum or change of momentum in the tangential direction. We will have P t that is omega s into delta V omega. This is a vector quantity. Omega s is the steam flow rate. This is the thrust which is responsible for doing the work. From the turbine, we get the mechanical work or we get the external work. This thrust, the tangential thrust, is responsible for that. This thrust is responsible for the movement of the turbine. That is why this is very important and we can determine it. We have to determine delta V w or V omega. V omega, I have given two formulae; this formula and initially I have given another formula in terms of V 1 and V 2. So, either of these we can use and can determine the tangential thrust. Then comes the axial thrust. Axial thrust again in the direction of the axis, if we see what the change of velocity is, we can determine it. In the inlet we have got Va1 that is in the direction of axis and in the exit, we have got V a2. We can write P axial is equal to omega s delta V a. Delta V a is equal to V a1 minus V a2. Again V a1 we can write V 1 sin of alpha. V 1 sin of alpha, we can write minus this is V 2 sin of z that means sin of 180 degree minus delta, that is, V 2 sin delta. This is how we can get the axial thrust. Now, axial thrust does not do the useful work. Rather, it is not desirable to have a very large axial thrust. Though we cannot avoid it, there will be some amount of axial thrust and that is taken care of by bearings in a turbine shaft. This is the axial thrust. So tangential and axial thrust we could determine. 11

12 (Refer Slide Time: 36:53) Next, we can determine the blading work or diagram work. This blading work or diagram work, we know that the useful component of force which is doing the work, that is, P t. So P t due to this force there is a movement in the direction of V b or there is a rotation of the blade; rotation of the blade and in the same direction we have got the tangential velocity V b. Using these two we can determine the blading work, let us say we call it W D diagram work, that is why it is called W D; that is equal to P t into V b. That means we will have this is the steam flow rate into delta V omega into V b. This will be the blading work or diagram work. This is the amount of energy which is coming out as external work or as the useful work out of a turbine. What is the energy being supplied to the turbine? The energy that is being supplied to the turbine, if we do not consider the nozzle, but if we consider only the blade, then energy going to the blade passage that will be equal to let us say E blade, that is equal to half into omega s into V 1 square. That is the kinetic energy. With this, we can define the blade efficiency or stage efficiency or sometimes it is called diagram efficiency. Let us go to another page. 12

13 (Refer Slide Time: 39:58) One can define the efficiency of energy conversion, eta D. Again sometimes, it is called diagram efficiency. That is why I have denoted it as eta D. So, what will it be? We will have omega s, delta V omega to V b divided by 1/2 omega s V 1 square. Omega s can be cancelled from both the sides. So, basically we will get twice delta V omega V b divided by V 1 square. We see if we go back to the initial diagram which we have drawn or maybe we can go to the first diagram. (Refer Slide Time: 41:45) 13

14 What we can see in this diagram is that steam is supplied at certain pressure, at a certain enthalpy and there is a nozzle and there is a blade. In the nozzle, there is a change in pressure. There is a loss in pressure or drop in pressure and velocity is increasing. When the steam is passing through the blade passage, then there is a drop in velocity. Basically, there are a number of conversions and how much will be the inlet velocity and outlet velocity that depends on nozzle design and blade design. At this point, I mean a very logical question will arise: Are these values arbitrary? Can we choose these values arbitrarily? Or is there some sort of a guideline we should follow to get the maximum out of this design? If we go to the next diagram, we can see how the different components of velocities are changing from inlet to outlet. (Refer Slide Time: 43:19) You see quite a few things can be selected. One can select the nozzle angle; one can select the tangential component of velocity for the blade which is V b. How? Because we know that, it is a function of rotational speed RPM and the diameter of the turbine, one can select that; or if we see from the other perspective, let us say that the power generated is torque into RPM. We have some sort of independence of selecting torque and RPM separately, so that we get a product that is torque into RPM or power. So, if power also remains constant, one has some independence of selecting torque and RPM. 14

15 The question is how these design parameters can be selected so that we get maximum efficiency out of our design turbine. Probably at this point, we are in a position to decide that at least partially. (Refer Slide Time: 45:02) Here you see that we are getting two velocity components, one is V 1 and another is V b. Apparently these two can be selected independently but let us see whether there is some sort of a relationship or not. What we can do is, let us define a ratio rho that is V b by V 1. Again, here we have to remember that V 1 that is the velocity at the nozzle outlet and that depends how much enthalpy drop we are going to allow in a nozzle. Let us see how V b depends on V 1. If I define this as rho and we call it velocity ratio then one can show eta D is equal to twice rho square cos of alpha by rho minus 1 into 1 plus K b. K b that friction ratio or blade friction factor we already have. One can do a little bit analysis like d eta D by d rho that should be equal to 0 for maximum efficiency. For maximum efficiency, this quantity should be made equal to 0. 15

16 (Refer Slide Time: 47:30) Let me write it once again, eta D is equal to twice rho square cos of alpha by rho minus 1 and this is 1 plus K b. d eta D by d rho that is equal to how much will be this quantity? If we break it 1 plus K b, that will be a constant term. Then rho will cancel, so we will have 2 rho cos of alpha minus 2 rho square. This is equal to 1 plus K b and 2 cos alpha minus 4 rho and for maximum efficiency this is equal to 0. For maximum efficiency, for eta D max, we will have twice cos of alpha is equal to 4 rho or rho is equal to cos of alpha by 2. We can see we have defined rho as or V b by V 1 is equal to cos of alpha by 2. We can see that if we want to run the turbine at maximum efficiency then we cannot arbitrarily select V b. I said that V 1 comes from how much enthalpy drop we are going to allow in the nozzle; from their V 1 comes. So if V 1 we select arbitrarily or V 1 is selected independently, then V b bears a relationship with it for maximum efficiency and this is the relationship. 16

17 (Refer Slide Time: 50:17) If we put that we will get eta D is equal to, rho is equal to cos alpha by 2. So, twice cos square alpha by 4, then cos of alpha; this is cos alpha by 2, cos of alpha by 2 means this is 2 minus 1 and 1 plus K b. We will get cos alpha, cos alpha will cancel 2 minus 1 is 1 and here it is cos square alpha by 2, 1 plus K b. If the blade is assumed to be more or less smooth, then K b is equal to 1; K b is 1 for smooth blade. In that case eta D is equal to cos square alpha. This will be the efficiency of the blade passage or optimum efficiency of the blade passage. Let us go back to the diagram. (Refer Slide Time: 51:53) 17

18 We see that efficiency of the blade passage depends on the nozzle angle. That is what I said at the beginning that there are number of parameters. At the beginning it appears that they are independent of each other. We can select them bit arbitrarily but it is not so. We can see that the blade angle determines what the efficiency of the turbine will be. From here again it is interesting to see that eta D will have a high value, if cos alpha is high. Now, if cos alpha value has to be high, then this angle has to be very small, but we cannot make it very small due to the mechanical construction. We cannot make it very small, it will slant then and the blade passage will be very obscured, so we cannot do it. There are some limitations. Generally, this angle is kept 12 degrees, 14 degrees, like that. We generally do not go to a smaller angle than this, may be 12 degrees or 14 degrees or 16 degrees like this. These are the typical values of the nozzle for the impulse turbine. This analysis is the basic analysis and it is applicable for impulse staging. We will see what the different ways of compounding impulse turbine are and that we will do in the next class. 18

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