happen in a quiz/exam) after doing the four book problems. A turbojet engine operates at an...
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....