The following data apply to a twin-spool turbofan engine, with the fan driven by the LP turbine and the compressor by the HP turbine. Separate hot and cold nozzles are used: • Compressor pressure ratio: 12.5 • Fan pressure ratio: 1.6 • Bypass ratio: 3.5 • Turbine inlet temperature: 1300 K • Air mass flow: 120 kg/s ● Cph = 1.14 kJ/kg K, %= 1.336 Find the sea-level static thrust and TSFC if the ambient pressure and temperature are 1 bar and 288 K. Heat value of the fuel: 43 MJ/kg
The following data apply to a twin-spool turbofan engine, with the fan driven by the LP turbine and the compressor by the HP turbine. Separate hot and cold nozzles are used: • Compressor pressure ratio: 12.5 • Fan pressure ratio: 1.6 • Bypass ratio: 3.5 • Turbine inlet temperature: 1300 K • Air mass flow: 120 kg/s ● Cph = 1.14 kJ/kg K, %= 1.336 Find the sea-level static thrust and TSFC if the ambient pressure and temperature are 1 bar and 288 K. Heat value of the fuel: 43 MJ/kg
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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![The following data apply to a twin-spool turbofan engine, with the fan driven by the
LP turbine and the compressor by the HP turbine. Separate hot and cold nozzles are
used:
•
Compressor pressure ratio: 12.5
Fan pressure ratio: 1.6
●
●
Bypass ratio: 3.5
●
Turbine inlet temperature: 1300 K
Air mass flow: 120 kg/s
•
Cph = 1.14 kJ/kg K, = 1.336
Find the sea-level static thrust and TSFC if the ambient pressure and temperature are
1 bar and 288 K. Heat value of the fuel: 43 MJ/kg](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fea29d648-0a3a-459b-ae41-2a211d13885c%2Ff6ae2b5b-e169-416a-a559-0894af908c0d%2F332uxxi_processed.jpeg&w=3840&q=75)
Transcribed Image Text:The following data apply to a twin-spool turbofan engine, with the fan driven by the
LP turbine and the compressor by the HP turbine. Separate hot and cold nozzles are
used:
•
Compressor pressure ratio: 12.5
Fan pressure ratio: 1.6
●
●
Bypass ratio: 3.5
●
Turbine inlet temperature: 1300 K
Air mass flow: 120 kg/s
•
Cph = 1.14 kJ/kg K, = 1.336
Find the sea-level static thrust and TSFC if the ambient pressure and temperature are
1 bar and 288 K. Heat value of the fuel: 43 MJ/kg
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