Other Gas Power System Applications A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser at 12 lbf/ in.2, 460°R, with a volumetric flow rate of 30,000 ft3/min and a velocity of 520 ft/s. In the diffuser, the air decelerates isentropically to negligible velocity. The compressor pressure ratio is 9, and the turbine inlet temperature is 2100°R. The turbine exit pressure is 25 lbf/in.2, and the air expands to 12 lbf/in.2 through a nozzle. The compressor and turbine each has an isentropic efficiency of 87%, and the nozzle has an isentropic efficiency of 95%. Using an air-standard analysis, determine
(a) the power delivered to the propeller, in hp.
(b) the velocity at the nozzle exit, in ft/s.
Neglect kinetic energy except at the diffuser inlet and the nozzle exit.
We need at least 10 more requests to produce the solution.
0 / 10 have requested this problem solution
The more requests, the faster the answer.