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So, this question has an additional component, that is, diffuser and it is given that at the exit of the diffuser the flow has negligible velocity. So, we can assume that the flow exits the diffuser with almost 0 velocity, and the flow at the nozzle exit is just choked, which means that Mach number at nozzle exit is 1, velocity there would be equal to square root of gamma r T. And, stagnation temperature is given to us. And, so that should help you in finding out the parameters at the rotor entry. And, since rotor exit conditions are lot of fix. You can also calculate the conditions at the rotor exit using the fact that the diffusion pressure is given and the fact that velocity at the exit is close to 0. So, in this case the tip speed comes out 586 meters per second and the angle alpha 2 is 73.75 degrees. (Refer Slide Time: 54:15) Now, the second question exercise problem is: if the mass flow rate of gas through the turbine given in this problem 1, the previews problem is 3.1 kilogram per second, the ratio of rotor axial width to rotor tip radius is 0. 1 and the nozzle isentropic velocity ratio is 0.96. Assuming that the space between the nozzle exit and nozzle rotor entry is negligible and ignoring the effects of blade blockage, determine the static pressure and static temperature at the nozzle exit; the rotor tip diameter and rotational speed; the power transmitted assuming a mechanical efficiency of 93.5 percentage. So, we need to use part of data which is given in the first question, to be able to solve this question as well. So, answer to part 1 is the pressure static pressure is 205. 80 kilopascal; temperature is 977 kelvin; the rotor tip diameter is 125.44 millimeters andPDF Image | Turbomachinery Aerodyanmics
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