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A turbojet aircraft is travelling at 925 km/h in atmospheric conditions of 0.45 bar and -26oC. The compressor pressure ratio is 8, the air mass flow rate is 45kg/s, and the maximum allowable cycle temperature is 800oC. The compressor, turbine, and jet pipe stagnation isentropic efficiencies are 0.85, 0.89, and 0.9 respectively, the mechanical efficiency of the drive is 0.98, and the combustion efficiency is 0.99. Assuming a convergent propulsion nozzle, a loss of stagnation pressure in the combustion chamber of 0.2 bar, and a fuel of calorific value 43 300kJ/kg, calculate: i) The required nozzle exit are; ii) The net thrust developed; slader For a gases in the turbine & propulsion nozzle take γ = 1.333 & Cp = 1.15kj/kg.k For the combustion process assume an equivalent Cp value of 1.15 kJ

A turbojet aircraft is travelling at 925 km/h in atmospheric conditions of 0.45 bar and -26oC. The compressor pressure ratio is 8, the air mass flow rate is 45kg/s, and the maximum allowable cycle temperature is 800oC. The compressor, turbine, and jet pipe stagnation isentropic efficiencies are 0.85, 0.89, and 0.9 respectively, the mechanical efficiency of the drive is 0.98, and the combustion efficiency is 0.99. Assuming a convergent propulsion nozzle, a loss of stagnation pressure in the combustion chamber of 0.2 bar, and a fuel of calorific value 43 300kJ/kg, calculate: i) The required nozzle exit are; ii) The net thrust developed; slader For a gases in the turbine & propulsion nozzle take γ = 1.333 & Cp = 1.15kj/kg.k For the combustion process assume an equivalent Cp value of 1.15 kJ

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 aircraft is travelling at 925 km/h in atmospheric conditions of 0.45 bar and -26oC. The compressor pressure ratio is 8, the air mass flow rate is 45kg/s, and the maximum allowable cycle temperature is 800oC. The compressor, turbine, and jet pipe stagnation isentropic efficiencies are 0.85, 0.89, and 0.9 respectively, the mechanical efficiency of the drive is 0.98, and the combustion efficiency is 0.99. Assuming a convergent propulsion nozzle, a loss of stagnation pressure in the combustion chamber of 0.2 bar, and a fuel of calorific value 43 300kJ/kg, calculate: i) The required nozzle exit are; ii) The net thrust developed; slader

For a gases in the turbine & propulsion nozzle take γ = 1.333 & Cp = 1.15kj/kg.k

For the combustion process assume an equivalent Cp value of 1.15 kJ/kg.k

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