Turbomachinery Aerodyanmics

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Turbomachinery Aerodyanmics ( turbomachinery-aerodyanmics )

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we have seen axial turbines in greater detail, including a tutorial session earlier on. And, this is for just to make a comparison between the work outputs of these two different types of turbine configurations. So, that completes the fourth problem, as well that we have solved today. And, what I have for you are two exercise problems, which I would leave it for you to solve. And, of course I had also left few exercises in between the couple of problems where I had requested that you should try to solve it in a different way. The method I had used to solve is one of the ways of solving the problems. You can also attempt to solve the problem in a different way, for which I had given some hints. So, I suggest that you would also solve those problems using the other alternative approach that I had suggested. (Refer Slide Time: 52:32) So, let us take a look at the first exercise problem that I have: a small inward radial flow gas turbine, comprising a ring of nozzle blades, radial-vaned rotor and an axial diffuser, operates at nominal design point with a total-to-total efficiency of 0.90. At the turbine entry the stagnation pressure and temperature of the gas is 400 kilopascals and 1140 kelvin respectively. The flow leaving the turbine is diffused to a pressure of 100 kilopascals and has negligible final velocity. Given that the flow is just choked at the nozzle exit, determine the impeller peripheral speed and the flow outlet angle from the nozzles.

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