3) Bypass Turbofan Engine A bypass turbofan engine has a bypass ratio of 5.5 (the mass flow through the bypass in 5.5 times the mass flow through the gas turbine), and propels an aircraft cruising at 250 m/s at an altitude where the atmospheric pressure is 30 kPa and the temperature is 230 K. The mass flow through the gas turbine core is 30 kg/s. Assume air is an ideal gas and the process is reversible. The flow through the bypass experiences a diffuser, fan, and nozzle. The gas turbine process is as follows: compression through an isentropic diffuser isentropic compression, pressure ratio = 13.2 1-2: 2-3: 3-4: isobaric heating in the combustion chamber to 1300 K, 4-5: turbine expansion drive the compressor 5-6: turbine expansion to drive the fan 6-7: isentropic expansion through a nozzle. a. Draw a sketch of the process and the T-s diagram b. Determine the power to drive the fan when the bypass outflow is 420 m/s. c. Determine temperature, pressure, enthalpy and velocity at all points. d. Determine the propulsive power of the engine and its thermal efficiency.