QUESTION 10 5 poir A bypass ratio 4.0 turbofan engine has split core and bypass nozzles. The high pressure turbine drive

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Question 10 5 Poir A Bypass Ratio 4 0 Turbofan Engine Has Split Core And Bypass Nozzles The High Pressure Turbine Drive 1 (396.36 KiB) Viewed 35 times

QUESTION 10 5 poir A bypass ratio 4.0 turbofan engine has split core and bypass nozzles. The high pressure turbine drives the high pressure axial compressor and the low pressure turbine drives the fan. The engine is modelled as a standard air cycle with cold-air-standard assumptions. The air stagnation temperature rise across the fan T03-To2 = 31 °C and the stagnation temperature rise across the high pressure axial compressor To4-To3 = 58 °C. The turbine inlet stagnation temperature To5 = 1286 K. Ignoring bearing losses, estimate the low pressure turbine outlet temperature. State your answer in degrees Kelvin to zero decimal places and enter the numerical value only. Partial credit is awarded for a reasonable approximation to the correct numerical answer. =