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An aircraft engine has design parameter as shown in table 1 Parameters Mo Pa Ta Compressor Pressure Ratio Turbine Entry Temperature, TET Compressor Efficiency Turbine Efficiency Low Heating Value, LHV of Jet A Combustor Pressure Loss (% of Cdp) Air Mass Flow Cp, cold Y cold Cp,Hot Yhot Value 0 101Kpa 15°C 25 1500K 0.9 0.85 42 800 kJ/Kg 5 150 kJ/s 1000 J/kg/K 1.4 1150 J/Kg/K 1.333 Unless otherwise specified, the turbomachinery efficiency is isentropic. a) Analyze the engine type by sketching a schematic diagram as well as T-s diagram of the engine. b) determine the thrust and Specific Fuel consumption (SFC) of the engine if the engine uses convergent nozzle.

An aircraft engine has design parameter as shown in table 1 Parameters Mo Pa Ta Compressor Pressure Ratio Turbine Entry Temperature, TET Compressor Efficiency Turbine Efficiency Low Heating Value, LHV of Jet A Combustor Pressure Loss (% of Cdp) Air Mass Flow Cp, cold Y cold Cp,Hot Yhot Value 0 101Kpa 15°C 25 1500K 0.9 0.85 42 800 kJ/Kg 5 150 kJ/s 1000 J/kg/K 1.4 1150 J/Kg/K 1.333 Unless otherwise specified, the turbomachinery efficiency is isentropic. a) Analyze the engine type by sketching a schematic diagram as well as T-s diagram of the engine. b) determine the thrust and Specific Fuel consumption (SFC) of the engine if the engine uses convergent nozzle.

Elements Of Electromagnetics
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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An aircraft engine has design parameter as shown in table 1 Parameters Mo Pa Ta Compressor Pressure Ratio Turbine Entry Temperature, TET Compressor Efficiency Turbine Efficiency Low Heating Value, LHV of Jet A Combustor Pressure Loss (% of Cdp) Air Mass Flow Cp, cold Y cold Cp,Hot Yhot Value 0 101Kpa 15°C 25 1500K 0.9 0.85 42 800 kJ/Kg 5 150 kJ/s 1000 J/kg/K 1.4 1150 J/Kg/K 1.333 Unless otherwise specified, the turbomachinery efficiency is isentropic. a) Analyze the engine type by sketching a schematic diagram as well as T-s diagram of the engine. b) determine the thrust and Specific Fuel consumption (SFC) of the engine if the engine uses convergent nozzle.
Transcribed Image Text:An aircraft engine has design parameter as shown in table 1 Parameters Mo Pa Ta Compressor Pressure Ratio Turbine Entry Temperature, TET Compressor Efficiency Turbine Efficiency Low Heating Value, LHV of Jet A Combustor Pressure Loss (% of Cdp) Air Mass Flow Cp, cold Y cold Cp,Hot Yhot Value 0 101Kpa 15°C 25 1500K 0.9 0.85 42 800 kJ/Kg 5 150 kJ/s 1000 J/kg/K 1.4 1150 J/Kg/K 1.333 Unless otherwise specified, the turbomachinery efficiency is isentropic. a) Analyze the engine type by sketching a schematic diagram as well as T-s diagram of the engine. b) determine the thrust and Specific Fuel consumption (SFC) of the engine if the engine uses convergent nozzle.
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