Answer Happy

Question 2 (2 marks) A turbojet single spool axial compressor has a pressure ratio of 6.0. Determine the total temperature and pressure at the outlet of the compressor given that the efficiency of the compressor is 0.8, the inlet stagnation temperature to the compressor is 50 °C and the compressor total inlet pressure is 149415 Pa. Question 3 (2 marks) After combustion a turbojet engine has a turbine inlet stagnation temperature of 1100 K. Assuming an engine mechanical efficiency of 99% determine the total temperature after exiting the turbine. Assume the total temperature entering and exiting the compressor is 325 K and 572 K respectively, The turbine has an isentropic efficiency of 0.89. Calculate the total pressure at turbine exit. Assume the total pressure at the turbine inlet is 896490 Pa.
AVA20004 FORMULA SHEET Gas Turbines Intakes Combustors To-T2 Ti T1 =78= to the end como T3-T; Turbines V = M/YR 96 - 1) RE Y TA' - T: - y 1.33 1.15kl/kg WmCCT-T.) Jet Pipes Yale 14 Cu = 1.005 kl/kg Compressors Wemcc-T) ne T:-T Work Done Wome W P, - A Ya 14 4 - 1.005 kl/kg Choked Flow & Compressible Flow Through Jet Pipes Velocity Choked Flow V = M. YRE M1 Gas Constant mets Cly-1) RE Flow is choked when sentropic Flow) >IS Jet Pipe Nozzle Pressure Ratio P 13