Thermodynamic Analysis of a Three-Spool Mixed-Flow Turbofan: An Approach to Improve Burner Performance

A nonlinear model has been developed and implemented in the Simulink environment and This research studies the thermodynamic analysis of a three-spool mixed-flow turbofan engine by examining different parameters, including flight altitude, flight Mach number, fan pressure ratio, high and Intermediate-pressure compressor pressure ratios, bypass ratio, and burner exit temperature. First, the effect of these parameters on the thrust, thrust-specific fuel consumption (TSFC), and engine efficiency was investigated. The exergy analysis resulted in the finding that the lowest exergy efficiency belongs to the combustion chamber, with a value of 85.45%. Therefore, a parametric study was conducted to improve the burner s performance and exergy efficiency. In particular, in the case of a bypass ratio of 2.2 and a fan pressure ratio of 2, the exergy efficiency of the burner is increased by 12.23% compared to the base case. In addition, the sensitivity analysis results show that the burner exit temperature and the high-pressure compressor pressure ratio of 21.81 and 2.2%, respectively, have the most and the least effect on the engine net thrust. Moreover, the burner exit temperature and the flight altitude of 4.57% and 0.11%, respectively, have the most and the least effect on the TSFC.