Question 3 (2 marks) After combustion a turbojet engine has a turbine inlet stagnation temperature of а 1100 K. Assuming

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Question 3 (2 marks) After combustion a turbojet engine has a turbine inlet stagnation temperature of а 1100 K. Assuming

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Question 3 (2 marks) After combustion a turbojet engine has a turbine inlet stagnation temperature of а 1100 K. Assuming an engine mechanical efficiency of 99% determine the total temperature after exiting the turbine. Assume the total temperature entering and exiting the compressor is 325 K and 572 K respectively. The turbine has an isentropic efficiency of 0.89. Calculate the total pressure at turbine exit. Assume the total pressure at the turbine inlet is 896490 Pa.
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