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Problem statement number 2 is: a radial inflow turbine develops 60 kilowatts power when running at 60,000 revolutions per minute. The pressure ratio P 0 1 by P 3 of the turbine is 2.0. The inlet total temperature is 1,200 Kelvin. The rotor has an inlet tip diameter of 12 centimeters and an exit tip diameter of 7.5 centimeters. The hub to tip ratio at the exit is 0. 3. The mass flow rate is 0.35 kilograms per second. The nozzle angle is 70 degrees and the rotor exit blade angle is 40 degrees. If the nozzle loss coefficient is 0.07, determine the total-to-static efficiency of the turbine and the rotor loss coefficient. So, here we can see, of course that the problem involves lot more data than we had for first case. We had the power input or power developed by the turbine is 16 kilowatts, the rotational speed is 60000 revolutions per minute. The pressure ratio is 2. Turbine inlet temperature is 1200. The dimensions of the rotor the tip diameter is 12 centimeter, exit tip diameter of 7.5 centimeter. Hub to tip ratio is 0.3. Mass flow rate and the angles, and additionally, the fact that the nozzle has a loss coefficient of 0.07. We need to find total-to-static efficiency and the rotor loss coefficient. So, this is the problem statement for this second question that we have. As always, we will first start with the velocity triangle. It is exactly the same, as we have seen in the first problem. Nevertheless, let us just quickly look at the velocity triangles and understand, what are the data provided for using this question and what is that we need to find. (Refer Slide Time: 22:13)PDF Image | Turbomachinery Aerodyanmics
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