涡扇发动机整机环境下风扇部件气动稳定性评定方法

Aerodynamic stability assessment of fan component running in turbofan engine

将基于部件匹配技术的涡扇发动机非设计点性能计算模型和基于李亚普诺夫稳定性理论的压缩部件气动稳定性评定模型有机的耦合,实现了发动机整机环境下的压缩部件气动稳定性评定,使得该模型成为一种实用的涡扇发动机压缩部件气动稳定性分析模型.以某型涡扇发动机为例,计算比较了均匀进气和畸变进气时发动机整机环境和单独部件评定时风扇部件稳定工作边界的异同,从计算结果可以看到,均匀进气条件下,在发动机环境下和单独部件环境下所得到的风扇部件稳定工作边界变化不大;而畸变进气条件下,同样的进口畸变度,发动机环境下风扇的稳定裕度损失比单独部件下风扇的稳定裕度损失都小,即在发动机环境下评定风扇稳定性时,风扇对进气温度畸变不敏感,而在单独部件环境下评定时,风扇对进气畸变比较敏感.

A new model was presented for predicting of aerodynamic stability limit of compressor in turbofan engine. Firstly, a quasi one-dimensional, time dependent compression system model was used to model the dynamic flow in compressor and the actuator-lagvolume model was adopted to model the stage of compressor. Secondly, Lyapunov stability theory was used to identify the aerodynamic stability of compression component. Finally, this aerodynamic stability numerical model was coupled with steady state thermodynamic cycle model of turbofan for predicting of aerodynamic stability limit of compression component in turbofan engine environment. A turbofan engine with 3 stages fan and 5 stages compressor as an example was simulated. Numerical results show that the model presented in this paper is reasonable and reliable and can be used to predict aerodynamic stability limit of fan and compressor in real turbofan engine environment.