Effects of blade single and coupling errors on axial flow compressor performance

被引：1
作者：
Chu, Wuli [1 ]
He, Xudong [1 ]
Yang, Jibo [2 ]
Liu, Kaiye [1 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi’an
[2] Xi’an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi’an
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 11期
关键词：
coupling error; machining errors; stagger angle error; transonic compressor; uncertainty;
D O I：
10.13224/j.cnki.jasp.20220941
中图分类号：
学科分类号：
摘要：
Due to the limitation of processing technology and other factors，there is always a small error between the theoretical blade profile and the actual blade profile in the actual processing. For transonic compressor Rotor 37，the influences of axial position and stagger angle errors on the uncertainty of compressor aerodynamic performance were studied by numerical simulation and NIPC (non-intrusive polynomial chaos method). The conclusion indicated that，for machining errors with zero mean standard normal distribution of axial position and stagger angle，the sensitivity of rotor aerodynamic performance was approximately the same when they changed singly or in coupling，only individual parameters were different. The correlation between the aerodynamic performance of axial flow compressor and each error was strong or weak，and attention shall be paid to the performance parameters with strong correlation during processing. The influence of blade coupling error on compressor lied in the superposition of the influences of blade axial position error and stagger angle error. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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