建立了民用航空发动机压气机叶尖间隙工程设计方法。首先,根据设计点要求进行初始冷态间隙计算,而后基于强度分析得到的变形量、制造公差、配合关系、稳态不平衡响应以及发动机工作状态等因素评估其余考核工况点间隙,经过迭代调整后得到满足安全要求的间隙值，最后根据试验数据修正得到最终冷态间隙值。以某高负荷压气机第7 级转子为例开展了叶尖间隙设计,并与试验验证结果进行对比,证明了所提方法的可行性和合理性,采用该方法获得了安全可靠的叶尖间隙设计结果。

This paper presents the engineering design method of tip clearance in a civil aeroengine compressor. Firstly, the initial coldstate clearance is computed based on the design point requirements. Subsequently, 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 rationality 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.

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