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A turbine engine air intake is at pressure and temperature of air drawn 99 kPa and 29 °C respectively. The maximum pressure and temperature during the cycle is 990 kPa and 888 °C respectively. The adaibatic index as 1.4. After claculations, the pressure ratio of the cycle is compressor exit temperature is K, turbine exit temperature is K, net specific work output from the gas turbine engine is in k thermal efficiency_ is % and work ratio of the cycle is to I decimal place.

A turbine engine air intake is at pressure and temperature of air drawn 99 kPa and 29 °C respectively. The maximum pressure and temperature during the cycle is 990 kPa and 888 °C respectively. The adaibatic index as 1.4. After claculations, the pressure ratio of the cycle is compressor exit temperature is K, turbine exit temperature is K, net specific work output from the gas turbine engine is in k thermal efficiency_ is % and work ratio of the cycle is to I decimal place.

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 turbine engine air intake is at pressure and temperature of air drawn 99 kPa and 29 °C respectively. The maximum pressure and temperature during the cycle is 990 kPa and 888 °C respectively. The adaibatic index as 1.4. After claculations, the pressure ratio of the cycle is compressor exit temperature is K, turbine exit temperature is K, net specific work output from the gas turbine engine is in k thermal efficiency_ is % and work ratio of the cycle is to I decimal place.
Transcribed Image Text:A turbine engine air intake is at pressure and temperature of air drawn 99 kPa and 29 °C respectively. The maximum pressure and temperature during the cycle is 990 kPa and 888 °C respectively. The adaibatic index as 1.4. After claculations, the pressure ratio of the cycle is compressor exit temperature is K, turbine exit temperature is K, net specific work output from the gas turbine engine is in k thermal efficiency_ is % and work ratio of the cycle is to I decimal place.
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