Examine the following open gas turbine process. The temperature of the inlet air is 296 K and pressure is 100 kPa. The polytropic efficiency of the compressor is 81.0 % and pressure ratio 7. The heat flow rate (fuel power) into process is 1.25 MW. The maximum temperature of the process (after combustion chamber) is 1440 K and the polytropic efficiency of the turbine is 87.0 %. The mass flow rate of air is 1.207 kg/s. A constant specific heat cp = 1.15 kJ/kgk can be used for the working fluid. Combustion chamber can be considered as adiabatic. Air in Calculate: C Fuel 10 CH 3 1) Temperature after compressor T₂ 2) Compressor power Pc 3) Temperature after turbine T 4) Turbine power Pt 5) Thermal efficiency of the system nt T Flue gas K (with zero decimal accuracy) MW (with three decimal accuracy) K (with zero decimal accuracy) MW (with three decimal accuracy) % (with one decimal accuracy)

Required information A turbojet is flying with a velocity of 900 ft/s at an altitude of 20,000 ft, where the ambient conditions are 7 psia and 10°F. The pressure ratio across the compressor is 13, and the temperature at the turbine inlet is 2320 R. Assume ideal operation for all components and constant specific heats for air at room temperature. The properties of air at room temperature are Cp = 0.24 Btu/lbm-R and k = 1.4. Determine the propulsive efficiency. The propulsive efficiency is 45.79 %.

Assuming a compression ignition engine having a cut-off ratio of 2 and a compression ratio of 20. Before the compression stroke, air is at 100kPa, 20°C and a volume of 500 cm³. Determine (in kPa) the mean effective pressure of the cycle

Temperature after the heat addition process = K Thermal efficiency =% Mean effective pressure = kpa