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