摘要
为了提高多级轴流压气机在非设计条件下的稳定裕度,基于逐排基元叶片方法,应用恰当的损失和落后角模型,建立了预测多级轴流压气机特性工程方法,并将其与复合形优化方法相结合,给出了1种多级轴流压气机多静叶排调节扩稳算法,并应用于NACA 8级轴流压气机,取得了明显扩稳效果,数值计算进一步阐明了不同性能约束对变几何扩稳效果影响规律。结果表明:应用合理的性能约束进行优化,对提高多级轴流压气机非设计条件下稳定裕度有明显效果。
In order to improve the stability margin at off-design conditon of nmhistage axial-flow compressor, the engineering method for calculating multistage axial-flow compressors performances was built based on blade row-by-blade row cascade method and an appropriate loss and deviation models. Combined with complex optimization method, an aerodynamic stability numerical methodology of stator stagger setting of multistage axial-flow compressor was established and applied to NACA eight-stage transonic axial compressor to obtain obvious aerodynamic stability effectiveness. The influence rules of different performance constraints on variable geometry aerodynamic stability effectiveness were clarified further by the numerical calculation. The result show that the multistage axial-flow compressors is optimized by the reasonable performance constraints to improve obviously the stability margin at off-design conditon.
出处
《航空发动机》
2012年第6期11-15,共5页
Aeroengine
关键词
轴流压气机
性能
变几何
气动稳定性
优化
航空发动机
axial-flow compressor
performance
variable geometry
aerodynamic stability
optimization
aeroengine
