Optimization of gas turbines for sustainable turbojet propulsion

Abstract Gas-turbines are widely used to power aero planes because they are light, compact with a high power-to-weight ratio. In the turbo jet engine, the main operating variables are: compressor pressure ratio r p and turbine inlet temperature ( TIT ). These variables affect the specific thrust and specific fuel consumption ( SFC ), which represent the main performance parameters. In addition to the analytical work, a computer program of the General Algebraic Modeling System (GAMS) was used for analysis and optimization. The analysis shows that the specific thrust strongly depends on turbine inlet temperature ( TIT ), where a 10% decrease in TIT results in 6.7% decrease in specific thrust and 6.8% decrease in SFC . Furthermore, the value of optimum pressure ratio r f for maximum specific thrust increases with TIT . A 10% decrease from design TIT results in 11.43% decrease in r f . The value of optimum pressure ratio for the turbojet engine operating at Ma =0.8 and altitude Alt =13000 m, and TIT =1700 K was found to be 14.

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