Turbomachinery Aerodyanmics

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Turbomachinery Aerodyanmics ( turbomachinery-aerodyanmics )

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So, this can be simplified and you can actually calculate the rotor loss coefficient, given the nozzle loss coefficient in a much simpler, less confusing manner than simply substituting them in the formulae. I picked up this method because if we take up any textbook, you would normally see this kind of method where they would refer to the derivation, which was discussed earlier on what I have done. And, in the problem we just simply substitute, plug in the values and calculate the corresponding efficiency and other terms required. Now, that brings us to the third question. Let us, now proceed towards the third problem that we have for us to solve. And then, we will see how this problem is different from the previous problems. (Refer Slide Time: 36:16) An inward flow turbine with 12 vanes is required to develop 230 Kilowatts at an inlet stagnation temperature of 1,050 kelvin and a flow rate of 1 kilogram per second. Using the optimum efficiency design method and assuming a total-to-static efficiency of 0.81, determine the absolute and relative flow angles at the rotor inlet; part b is the overall pressure ratio, P 0 1 by P 3; part c is the rotor tip speed and the inlet absolute Mach number. So, this is a three part question where we are required to calculate three different part aspects. One is the angles, absolute and relative flow angles and the pressure ratio, and of course, the rotors tip speed and the Mach number. And of course, you can see what is

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