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A turbojet engine is shown in the figure below. The conditions at State 1 are 300K, 100 kPa. The pressure ratio on the compressor is 25. Both the compressor and turbine are adiabatic and reversible. Sufficient heat is added to take Point 3 to 1700 K (constant pressure combustor). In the engine, the turbine produces only enough work to drive the compressor, and no more. This means the pressure at Point 4 is above 100 kPa, and it is | this pressure that is expanded across the nozzle to provide thrust at Point 5. Using air standard assumptions, find the pressure (kPa) and temperature (K) at Point 4. 冊 qlin 3 Combustor Compressor Turbine 5

A turbojet engine is shown in the figure below. The conditions at State 1 are 300K, 100 kPa. The pressure ratio on the compressor is 25. Both the compressor and turbine are adiabatic and reversible. Sufficient heat is added to take Point 3 to 1700 K (constant pressure combustor). In the engine, the turbine produces only enough work to drive the compressor, and no more. This means the pressure at Point 4 is above 100 kPa, and it is | this pressure that is expanded across the nozzle to provide thrust at Point 5. Using air standard assumptions, find the pressure (kPa) and temperature (K) at Point 4. 冊 qlin 3 Combustor Compressor Turbine 5

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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A turbojet engine is shown in the figure below. The conditions at State 1 are 300 K, 100 kPa. The pressure ratio on the compressor is 25. Both the compressor and turbine are adiabatic and reversible. Sufficient heat is added to take Point 3 to 1700 K (constant pressure combustor). In the engine, the turbine produces only enough work to drive the compressor, and no more. This means the pressure at Point 4 is above 100 kPa, and it is this pressure that is expanded across the nozzle to provide thrust at Point 5. Using air standard assumptions, find the pressure (kPa) and temperature (K) at Point 4. 1 qlin 3 Combustor Compressor Turbine 5
Transcribed Image Text:A turbojet engine is shown in the figure below. The conditions at State 1 are 300 K, 100 kPa. The pressure ratio on the compressor is 25. Both the compressor and turbine are adiabatic and reversible. Sufficient heat is added to take Point 3 to 1700 K (constant pressure combustor). In the engine, the turbine produces only enough work to drive the compressor, and no more. This means the pressure at Point 4 is above 100 kPa, and it is this pressure that is expanded across the nozzle to provide thrust at Point 5. Using air standard assumptions, find the pressure (kPa) and temperature (K) at Point 4. 1 qlin 3 Combustor Compressor Turbine 5
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