轴流压气机叶尖射流扩稳数值计算模型

基于体积力方法将压气机叶片对气流的作用力和做功简化为源项,对环形无叶片通道求解带源项的Navier-Stokes(N-S)方程,实现了压气机全通道流场的计算,通过在转子上游机匣施加射流建立了轴流压气机叶尖射流扩稳数值模型.模型中的源项根据叶片排进口气流参数进行变化,通过判断施加的人工扰动变化确定压气机失稳边界.采用该模型对某跨声速单级压气机在有、无射流下的性能和稳定性进行了计算分析,无射流下计算的该压气机性能和稳定边界与试验结果都能较好地一致,其中稳定边界流量仅相差0.7％；有射流下射流对压气机具有明显的扩稳效果,将计算结果与国外公开文献的结果进行了对比,验证了模型的可靠性.

Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection

A numerical calculation model for axial compressor stability enhancement by tip injection was developed.The model solved Navier-Stokes equation with source terms for annulus duct without blades.The effect of blades,including the force and energy applied to the flow by the blades,was modeled by the source terms.The current source terms of every iteration step varied according to the inlet parameters.Variation of manual disturbance was introduced to the model to predict the compressor's stall margin.The performance and stall margin of a transonic single stage compressor were calculated by the model with/without tip jet.The performance and stall margin predicted by the model without tip jet agree well with the experiment result,and the difference between the massflow of the stall margin predicted by the model and that got by the experiment is less than 0.7%.The effect of stability enhancement by tip injection is obvious from the results of the model compared with the results in open literature,helping to verify the model.