压气机初始设计中端区堵塞模型的建立和数值验证  

Foundation and Numerical Verification of an Endwall Blockage Model for Initial Design of Compressor

作　　者：刘瀛龙[1] 杨春[1] 李秋实[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2009年第3期15-18,共4页Aeroengine

摘　　要：根据扩张管道边界层理论,从边界层动量积分关系式出发,提出了用于轴流压气机初始设计的端壁区堵塞发展模型。应用该模型,可以在初始设计阶段方便地预测压气机端壁区堵塞的发展。通过对轴流压气机扩压叶栅的数值模拟,将模型预测值与数值模拟结果进行对比分析,验证了该模型的准确性和适用性。A development endwall blockage model for the initial design of axial compressor was proposed which was based on the boundary layer theory of diffuser and the momeutum integral equation of boundary layer. It was very convenient to use this model to predict the compressor endwall blockage in the initial design. The numerical simulation results of the axial compressor diffusion cascade compared with the results perdicted by the new model. The results show that the model has good accuracy and applicability in the prediction of the endwall blockage.

关 键 词：轴流压气机 端壁区 初始设计 堵塞模型 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] TQ021.5[化学工程]