1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet
1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet
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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![Q3) A turbojet engine is operates at altitude where temperature and pressure are 216K, 60kPa
respectively. The air craft speed is 250m/s and the engine data is given below. Assume that,
properties of the combustion gas same as those of air and no stagnation pressure losses in
the inlet diffuser.
Combustion
• The stagnation temperature at the turbine
chamber
3
inlet=1500K
Toa Pea
Tes Paa
Temperature drop at the turbine= 205 C
• Calorific valve of the fuel= 42MJ/ Kg
Turbine efficiency= 0.9
• Compressor efficiency 0.8
• Combustion efficiency= 0.95
Exhaust Nozzle efficiency =0.93
Stagnation pressure at the turbine entry:
(Po3) = 0.97 x Po2
Air
Compressor
Turbine
Nozzie
Exhaust
TA
T. Pe
Intet
difuser
Tor. Por
Toe Pos
Calculate:
1- Air to fuel ratio
2- Exhaust nozzle pressure
3- The velocity of the exhaust jet
4- Thrust force develops if the inlet diffuser area is 0.5m2
5- Propulsive efficiency, specific thrust](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fe54f423b-acdf-4577-b6e9-57b1f63079c4%2Fdbfe654d-5b4d-42bb-9b27-f26f8dbc027b%2F1dc8kz4_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Q3) A turbojet engine is operates at altitude where temperature and pressure are 216K, 60kPa
respectively. The air craft speed is 250m/s and the engine data is given below. Assume that,
properties of the combustion gas same as those of air and no stagnation pressure losses in
the inlet diffuser.
Combustion
• The stagnation temperature at the turbine
chamber
3
inlet=1500K
Toa Pea
Tes Paa
Temperature drop at the turbine= 205 C
• Calorific valve of the fuel= 42MJ/ Kg
Turbine efficiency= 0.9
• Compressor efficiency 0.8
• Combustion efficiency= 0.95
Exhaust Nozzle efficiency =0.93
Stagnation pressure at the turbine entry:
(Po3) = 0.97 x Po2
Air
Compressor
Turbine
Nozzie
Exhaust
TA
T. Pe
Intet
difuser
Tor. Por
Toe Pos
Calculate:
1- Air to fuel ratio
2- Exhaust nozzle pressure
3- The velocity of the exhaust jet
4- Thrust force develops if the inlet diffuser area is 0.5m2
5- Propulsive efficiency, specific thrust
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