An Optimization Method for Non-augmented Supersonic Cruise Performance of Turbofan Engine

被引：0
|
作者：
Ma, Xin-yue [1 ]
Gou, Lin-feng [1 ]
Tan, Tian [1 ]
机构：
[1] Northwestern Polytech Univ, Sch Power & Energy, Xian 710072, Peoples R China
来源：
2019 IEEE 10TH INTERNATIONAL CONFERENCE ON MECHANICAL AND AEROSPACE ENGINEERING (ICMAE 2019) | 2019年
关键词：
turbofan engine; non-augmented supersonic cruise; velocity characteristics; tail nozzle throat area adjustment;
D O I：
10.1109/icmae.2019.8880993
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Based on the component maps based gas turbine engine simulation model, the engine steady-state performance calculation model is established. Based on the model, the non-augmented supersonic cruise performance of the fourth-generation engine is studied. The effect of different rotational speed of the high-pressure rotor design values and different throttle ratios on engine velocity characteristics is analyzed. The effect of adjusting the throat area of the tail nozzle on the engine velocity characteristics is analyzed. Finally, the non-augmented supersonic cruise performance of the fourth-generation engine has been optimized.
引用
收藏
页码：122 / 127
页数：6
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