6.31 : A double-spool turbofan engine; Fig. (6.66), is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m. As shown in the figure below, the low-pressure turbine drives the fan and low-pressure compressor, while the high-pressure turbine drives the high-pressure compressor. The engine has the following data:Bypass ratio = 8.Total ingested air flow rate = 180 kg/s.Overall pressure ratio OPR = 35.Fan pressure ratio = 1.6.Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; πHPC= 4 πLPC.Turbine inlet temperature = 1650 K.Fuel heating value = 43 MJ/kg.Assuming all processes are ideal and neglecting any pressure drop, it’s required to:Find the thrust, TSFC, and efficiencies of the enginePlot the velocity and temperature distribution over the engine cross section(rear end).

Answered: 6.31 : A double-spool turbofan engine;…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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6.31 : A double-spool turbofan engine; Fig. (6.66), is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m. As shown in the figure below, the low-pressure turbine drives the fan and low-pressure compressor, while the high-pressure turbine drives the high-pressure compressor. The engine has the following data:

Bypass ratio = 8.
Total ingested air flow rate = 180 kg/s.
Overall pressure ratio OPR = 35.
Fan pressure ratio = 1.6.
Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; π_HPC= 4 π_LPC.
Turbine inlet temperature = 1650 K.
Fuel heating value = 43 MJ/kg.