Abstract: For the high pressure compressor of an aero-engine, on the comprehensive consideration of aerodynamic loading, centrifugal loading, temperature loading, the radial clearance computational model for high pressure compressor was established. Characteristics of flow field and distribution of deformation and stress of blades were obtained under the three typical working states. And regularity of radial blade tip clearance of high pressure compressor and scope of blade tip clearance were achieved by the simulation method. For diagonal compressor, the computational results show that under the state of design point and the state of the greatest rotating speed, the blade tip will rub on the casing. The results are coincident with the aero-engines test results which testify the effectiveness of the calculating method and also provide the research idea of building logically and effectively analytical method of radial clearance for compressor. 

Key words: Axial compressor； Diagonal compressor； Radial clearance；Numerical simulation CLC number:V231.1Document code:AArticle number:1001-4055(2013)03-0339-08

摘要： 针对航空发动机高压压气机,综合考虑气动载荷、离心力载荷、温度载荷耦合作用,建立了压气机径向间隙分析模型,获得了3个典型工况下的流场特征以及叶片的变形、应力分布,高压压气机转子叶尖径向间隙沿轴向变化的分布规律以及轴流压气机转子与机匣的间隙范围。计算结果显示在设计点和转速最高点,斜流压气机转子叶尖与机匣发生碰磨,与试验结果一致,验证了计算方法的正确性,也为建立合理有效的压气机径向间隙分析方法提供了思路。 