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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 of multi-stage axial compressor under non-design conditions, an engineering prediction method of multi-stage axial-flow compressor characteristics is established based on the row-by-row primitive blade method with proper loss and backward angle model. Combined with the complex shape optimization method, a multistage turbo-blade regulation and expansion method for a multi-stage axial-flow compressor is presented and applied to a NACA 8-stage axial flow compressor. The results show that the numerical calculation is further improved The influence of different performance constraints on the geometric stabilizing effect is clarified. The results show that the optimization with reasonable performance constraints has obvious effect on improving the stability margin of multi-stage axial compressor in non-design conditions.