(Solved): Exercise 2 1. Determine the optimum compressor ratio, specific thrust, and TSFC for an ideal turbo ...

Exercise 2 1. Determine the optimum compressor ratio, specific thrust, and TSFC for an ideal turbojet engine giving the maximum specific thrust at the following conditions: Mo-2.1, To=220K, Tt4-1700K, hPR=42.8 MJ/kg, cp=1.004 kJ/(kg-K), and y=1.4. 2. Compute the specific thrust and the fuel/air ratio of an ideal turbofan engine with ?c=20, ?f=4, T?4=1400K. The engine is meant to be used by an aircraft flying at Mach number of 0.9 at an altitude of 40,000 ft. Use hPR-42.8 MJ/kg, cp=1.004 kJ/(kg-K), and y=1.4. 3. Repeat Problem 2 again but with Tt4-1670K.Compare the results. 4. In the early development of the turbofan engine, GE (yup, that GE), developed a turbofan engine with an aft fan as shown in the figure below. The compressor is driven by the high-pressure turbine, and the aft fan is directly connected to the low-pressure turbine. Consider an ideal case of this turbofan with the aft fan. 0 mF mc TiH TIL Compressor = 2 = High-pressure 13 turbine Combustor =1- 4.5 a. Show that the high-pressure turbine temperature ratio is given by: T?45 Fan T?4 =1- (Tc- -1) T? b. Show that the low-pressure turbine temperature is given by: T?5 ??. --(?,-1) T?4.5 T?TIH 5. Determine the specific thrust and the power specific fuel consumption of an ideal turboprop engine designed for an aircraft flying at Mach number of 0.8 at an altitude of 25,000 ft. To=240K, T4-1700K. The propeller efficiency is 83%. Use hPR=42.8 MJ/kg, cp=1.004 kJ/(kg-K), and y=1.4. 19 Low-pressure turbine Seal between fan stream and low-pressure turbine stream