This paper presents the engineering design method of tip clearance in a civil aero-engine com-pressor.Firstly,the initial cold-state clearance is computed based on the design point requirements.Sub-sequently,the clearance at other assessment points is assessed considering the deformation calculation of strength analysis,manufacturing tolerance,fit relationship,steady-state unbalanced response and engine operation.Through a series of iterations,a safe clearance is determined.Ultimately,the final cold-state clearance is obtained according to the experimental data correction.Taking the seventh stage rotor of a high-load compressor as an example,the blade tip clearance design is carried out.The feasibility and ra-tionality of the proposed method are substantiated by comparing the results with experimental verification.The design results of safe and reliable blade tip clearance has been obtained by this method.
维普
万方数据