Influence of leading edge over tolerance under random machining deviation on aerodynamic performance consistency of compressor cascade

GAO Limin; YANG Guang; WANG Haohao; DAN Yue; TU Panpan

doi:10.7638/kqdlxxb-2024.0083

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Influence of leading edge over tolerance under random machining deviation on aerodynamic performance consistency of compressor cascade

更新时间：2026-05-28

- Influence of leading edge over tolerance under random machining deviation on aerodynamic performance consistency of compressor cascade
- Vol. 42, Issue 10, Pages: 109-118(2024)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,710072
  2. 西北工业大学轻型涡轮动力全国重点实验室,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0083
  CLC： V231.3
- Published：2024
- 稿件说明：
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高丽敏, 杨光, 王浩浩, 等. 随机加工偏差下前缘超差对高亚声速叶栅性能一致性影响[J]. 空气动力学学报, 2024, 42(10): 109−118.

GAO Limin, YANG Guang, WANG Haohao, et al. Influence of leading edge over tolerance under random machining deviation on aerodynamic performance consistency of compressor cascade[J]. 2024, 42(10): 109-118.
高丽敏, 杨光, 王浩浩, 等. 随机加工偏差下前缘超差对高亚声速叶栅性能一致性影响[J]. 空气动力学学报, 2024, 42(10): 109−118. DOI： 10.7638/kqdlxxb-2024.0083

GAO Limin, YANG Guang, WANG Haohao, et al. Influence of leading edge over tolerance under random machining deviation on aerodynamic performance consistency of compressor cascade[J]. 2024, 42(10): 109-118. DOI： 10.7638/kqdlxxb-2024.0083.

摘要

针对叶片实际加工前缘易超差，但叶片其他区域满足加工容差的情况，本文构建了耦合前缘超差的叶型全弧长范围内带有随机轮廓加工偏差的数学模型，并通过基于稀疏网格的非嵌入混沌多项式方法，研究了加工偏差不确定性对高亚声速扩压叶栅气动性能一致性的影响。结果显示，在设计攻角下，叶型损失系数和静压比的一致性最高；在较大正攻角下，叶型性能参数一致性最低。造成性能一致性低的原因为前缘超差导致叶型前缘边界层内流动损失的平均水平和波动程度增大。当以设计叶型损失系数为 ± 5%作为衡量标准时，在设计攻角和较大正攻角下，叶型性能一致性概率分别为99%和79.4%，此时因叶片几何轮廓不符合容差而舍弃叶片会导致较高的误判率。

Abstract

In the actual processing of the cascade blade

the leading edge is prone to exceeding the tolerance

while other parts of the blade are not. The discrepancy in processing tolerance results in a deterioration of the aerodynamic performance consistency of compressor cascades. This paper proposes a mathematical model that incorporates random deliations in blade processing across the entire arc length of the blade profile coupled with the leading-edge over tolerance. This study examines the impact of processing deviation uncertainties on the aerodynamic performance consistency of a high subsonic diffuser cascade. A non-intrusive polynomial chaos expansion method based on sparse grids was employed to achieve this. The results show that the consistency of the blade loss coefficient and static pressure ratio is optimal at the design angle of attack

while it is lowest at large positive angles of attack. The poor performance consistency can be attributsd to the fact that the leading edge deviations result in an increase in the mean and root-mean-square values of flow loss within the boundary layers around the blade leading edge. When using ±5% deviation from the design blade as the criterion to measure the blade loss coefficient

the probability of blade profile performance consistency is 99% at the design angle of attack and 79.4% at large positive angles of attack.

关键词

Keywords

references

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