Abstract: In order to solve the problem of the Taguchi method when calculated the success rate of an assembly， such as large peak value error， low calculation accuracy and a mountain of calculation amount， an improved Taguchi method is used to calculate compressor assembly success rate of aero engine. First of all， as an influence factor to the orthogonal test of modified Taguchi method， the constitute circles are grouped and used to solve the partial assembly response functions by using the concept of substep orthogonal. The distribution type is determined according to the Pearson theory. The partial assembly response functions are used as the constitute circles to solve the distribution type of the total assembly response function. The response distribution map is obtained and the assembly rate is calculated. Then the influence of each constitute circles size on the assembly response function was analyzed by using the extreme difference method. Finally， on the basis of modified Taguhci method’s theory， an improved Taguchi method was used to calculate the assembly success rate of the aero-engine compressor. The Monte Carlo method and Taguchi method were applied to analyze. The comparison found that the modified Taguhci method’s kurtosis was reduced to 1.39% from 12.46% of Taguchi method which verified the effectiveness of the modified Taguchi method.

Key words: Modified Taguchi method；Compressor；Assembly success rate；Extreme difference analysis；Pearson distribution theory

摘要： 为了解决Taguchi法在计算一次装配成功率时存在峰度值误差大、计算精度低、计算量大等问题，采用一种改进Taguchi法计算航空发动机压气机的装配成功率。将组成环尺寸作为改进Taguchi法封闭环的影响要素，利用分步正交的概念将组成环分组并求解部分装配响应函数，根据Pearson理论判断其分布类型，将部分装配响应函数作为组成环再次正交试验求得总体装配响应函数的分布类型，得到响应分布图并计算其装配率。利用极差法分析组成环各水平因素对于装配响应函数的影响。在改进Taguchi法的理论基础上，以航空发动机压气机级轴向间隙为实例，采用改进Taguchi法计算其装配成功率，应用蒙特卡洛法及Taguchi法进行对比分析，对比发现改进Taguchi法峰度误差由Taguchi法的12.46%降低到1.39%，验证了改进Taguchi法的有效性。

关键词: 改进Taguchi法；压气机；装配成功率；极差法；Pearson分布理论