| Citation: | Liu Kaiye, Chu Wuli, Guo Zhengtao, et al. Uncertainty analysis of compressor aerodynamic performance with impact of global profile errors on blade[J]. Journal of Aerospace Power, 2026, 41（9）：20250135 doi: 10.13224/j.cnki.jasp.20250135
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To investigate the effects of global profile errors on the aerodynamic performance of a transonic compressor, a five-dimensional geometric variability model characterizing blade surface global profile errors was established based on Gaussian process and principal component analysis. Combined with the non-intrusive polynomial chaos expansion based on Gaussian distribution, a surrogate mode of compressor performance was proposed. The effects of the performance were quantified using non-intrusive polynomial chaos methodology, complemented by loss source analysis to investigate the critical flow mechanisms in two extreme-performance blade profiles. Key findings indicated that the performance parameters at peak efficiency condition exhibited slight deviations from normal distributions under the effects of random profile errors, with the performance showing degradation. And the performance was most sensitive to the error at blade tip leading edges. The thinner leading edge can reduce shock intensity and weaken shock-leakage vortex interactions, with the loss decrease.
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