叶片破损对压气机性能的影响

王忠义; 赵佳; 张晶; 王萌

doi:10.11990/jheu.202204055

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叶片破损对压气机性能的影响

更新时间：2025-09-01

- 叶片破损对压气机性能的影响
- Effect of blade breakage on compressor performance
- 哈尔滨工程大学学报 2024年45卷第4期页码：722-729
- 作者机构：
  
  1.哈尔滨工程大学动力与能源工程学院, 黑龙江哈尔滨 150001
  2.中船黄埔文冲船舶有限公司, 广东广州 510715
- 作者简介：
  
  [ "王忠义, 男, 教授, 博士生导师" ]
  [ "王萌, 男, 副教授" ]
- 基金信息：
  
  国家自然科学基金项目(52101348);国家科技重大专项(J2019-Ⅲ-0017-0061)
- DOI：10.11990/jheu.202204055
  中图分类号： V232.4
- 收稿：2022-04-22，
  
  网络首发：2024-02-08，
  
  纸质出版：2024-04-05
- 稿件说明：
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王忠义, 赵佳, 张晶, 等. 叶片破损对压气机性能的影响[J]. 哈尔滨工程大学学报, 2024,45(4):722-729.

Zhongyi WANG, Jia ZHAO, Jing ZHANG, et al. Effect of blade breakage on compressor performance[J]. Journal of Harbin Engineering University, 2024, 45(4): 722-729.
王忠义, 赵佳, 张晶, 等. 叶片破损对压气机性能的影响[J]. 哈尔滨工程大学学报, 2024,45(4):722-729. DOI： 10.11990/jheu.202204055.

Zhongyi WANG, Jia ZHAO, Jing ZHANG, et al. Effect of blade breakage on compressor performance[J]. Journal of Harbin Engineering University, 2024, 45(4): 722-729. DOI： 10.11990/jheu.202204055.

摘要

为了研究叶片破损对压气机内部流场的影响机理

本文针对带有破损的跨音速压气机叶片进行气动性能变化规律和机理研究。通过NASA rotor 37实验结果验证了计算方法的准确性

利用数值仿真研究了叶片破损对压气性能的影响规律

并对2种典型工况下叶片破损前后的流场结构进行对比分析

探讨引起性能变化的具体原因。研究表明: 叶片破损会导致压气机的压比降低0.663 1 %、绝热效率降低0.787 7 %

且压气机的稳定裕度降低更为明显。叶尖破损主要对叶顶流场结构产生影响

使叶顶区域泄漏流增强

当其与激波相互作用时

通道内产生了流动堵塞和流动损失。本文研究成果可为实际服役中的航空发动机特性评定提供理论参考。

Abstract

The change rule and mechanism of the aerodynamic performance of transonic compressor blades with damage are studied to investigate the effect of blade damage on compressor performance. The accuracy of the calculation method is verified by the results of the NASA rotor 37 experiment. The influence rule of blade breakage on compressed air performance is investigated through numerical simulation. The flow field structure before and after blade breakage under two typical working conditions is then compared and analyzed to explore the specific causes for performance changes. The results show that the pressure ratio and adiabatic efficiency of the compressor decrease by 0.663 1 % and 0.787 7 %

respectively

and that the stability margin of the compressor decreases more obviously. The tip damage mainly affects the structure of the tip flow field and enhances the leakage flow in the tip area. When it interacts with shock waves

flow blockage and flow loss occur in the channel. The findings of this study can provide a theoretical reference for the performance evaluation of aircraft engines in actual service.

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references

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