Problem 30 Explore the effects of altitude on the thrust and thrust-specific fuel consumption (TSFC)* for a turbojet eng

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Problem 30 Explore The Effects Of Altitude On The Thrust And Thrust Specific Fuel Consumption Tsfc For A Turbojet Eng 1 (180.31 KiB) Viewed 37 times

Problem 30 Explore the effects of altitude on the thrust and thrust-specific fuel consumption (TSFC)* for a turbojet engine when traveling with an airspeed of 200 m/s. The fuel flow rate is determined and adjusted with altitude so that when burned completely, the turbine operates with an inlet temperature of 1600 K at all times. Refer to table 3.1 for additional operating parameters, and appendix A-16 for atmospheric air properties versus altitude. Use the cold-air standard assumption, and neglect the effect of the diffusor and increase in mass at the engine's exit to complete the following: a) b) c) (10 points) Calculate the thrust produced and thrust-specific fuel consumption at 6000 m, you must show all work to receive credit (12 points) Complete Table 3.2, you do not need to show your work for this part (8 points) Using the results found in part b, plot thrust and TSFC versus altitude on a single smooth line scatter chart. This must be done using a computer (I suggest Excel) and formatted to look professional. * Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine with respect to thrust output. TSFC may also be thought of as the rate of fuel consumption per unit of thrust and is calculated using the following equation: TSFC = m Altitude (m) 2000 3000 4000 5000 6000 7000 8000 9000 10000 F fuel thrust Pressure Ratio Engine Inlet Diameter Compressor Isentropic Efficiency Turbine Isentropic Efficiency Nozzle Isentropic Efficiency Fuel heating Value Combustion Efficiency Table 3.1 Thrust (kN) Table 3.2 10 0.5 m 100% 100% 100% 42.7 MJ/kg 100% TSFC (g/s.kN)