2. A double-spool turbofan engine is used to power an aircraft flying at speed of 250...
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2. A double-spool turbofan engine is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m, where ambient temperature is -50°C and pressure is 22.7 kPa. As shown below, the low-pressure turbine drives the fan and low-pressure compressor, while the high- pressure turbine drives the high-pressure compressor. Inlet and outlet temperature and velocity of engine are plotted beside the engine layout. The engine has the following data: Bypass ratio P = 8. • Total ingested air flow rate ma = 180 kg/s. • Overall pressure ratio Pos/Poa = 35. • Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; ПHPC = 4πLPC. •⚫ Fuel heating value QR = 43 MJ/kg. (10 250 m/s T -50°C 306m/s -40°C Core stream 543.2 m/s 306m/s -40°C 250 m/s -50°C 592°C Assuming all processes are ideal. Also assume the flow capture area is the same as the engine inlet area and the bypass and core nozzle areas are the same as the respective capture areas. Find, a) Whether the nozzles are choked or not b) Pressure ratios πf, πLPC, and πнРC c) Turbine inlet temperature T06 and fuel to air ratio f d) The thrust force e) TSFC [unit in mg/(N s)] [30 Marks] 2. A double-spool turbofan engine is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m, where ambient temperature is -50°C and pressure is 22.7 kPa. As shown below, the low-pressure turbine drives the fan and low-pressure compressor, while the high- pressure turbine drives the high-pressure compressor. Inlet and outlet temperature and velocity of engine are plotted beside the engine layout. The engine has the following data: Bypass ratio P = 8. • Total ingested air flow rate ma = 180 kg/s. • Overall pressure ratio Pos/Poa = 35. • Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; ПHPC = 4πLPC. •⚫ Fuel heating value QR = 43 MJ/kg. (10 250 m/s T -50°C 306m/s -40°C Core stream 543.2 m/s 306m/s -40°C 250 m/s -50°C 592°C Assuming all processes are ideal. Also assume the flow capture area is the same as the engine inlet area and the bypass and core nozzle areas are the same as the respective capture areas. Find, a) Whether the nozzles are choked or not b) Pressure ratios πf, πLPC, and πнРC c) Turbine inlet temperature T06 and fuel to air ratio f d) The thrust force e) TSFC [unit in mg/(N s)] [30 Marks]
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A doublespool turbofan engine as shown in Figure 1 powers an aircraft flying at a speed of 250 ms at an altitude of 11000 m The engine has the following data Bypass ratio 8 Total ingested air flow rat... View the full answer
Related Book For
Thermodynamics An Engineering Approach
ISBN: 978-0073398174
8th edition
Authors: Yunus A. Cengel, Michael A. Boles
Posted Date:
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