5. Consider a propeller based aircraft with a supercharger. It operates with a revo of 2700 rpm, has 2 piston strokes per revolution of crankshaft, a shaft power of 10 a total engine displacement of 25 L. The supercharger serves to increase the inl to the engine to sea level conditions (P1 = PsL = 101.3 kPa, p1 = Psi = Consider an atmospheric model for air density given by 1.2 %3D h Pa = Psle 3000m

You have been asked to help with the low-pressure compressor (LPC) design for a turbofan engine with a bypass ratio of 8.4. The preliminary cycle design calls for the LPC to produce a pressure ratio of 9.4 with the following operating conditions and constraints. .Inlet Conditions TO2 Poz Core Air Mass Flowrate (kg/s) (K) (kPa) 282 24.6 47.0 Design Constraints Maximum Polytropic Efficiency 94.1% Maximum Stage Pr 1.55 Estimate the minimum number of stages required for this LPC. Then assuming the 1st stage of the LPC operates at the maximum allowable pressure ratio, determine the stagnation temperature exiting the 1st stage, and the stage's adiabatic efficiency. Also determine the power (W) required to operate the full LPC (not just 1st stage). Finally, what would be the percent change in the required power if the polytropic efficiency was only 90.0%.

Engine Aircraft

A single – stage air compressor has a cylinder bore of 0.1m, a stroke of 0.075m and a clearance factor of 0.05. The conditions within the cylinder during suction which are identical to those of the environment are 0.1 Mpa and 300K . The compression and expansion index is 1.3. Calculate; a) The mass delivery rate                                                                                 b) The power required                                                                                      c) The volumetric efficiency                                                                             d) The isothermal efficiency