级间封严引气射流抑制压气机角区分离机理研究

  • 徐文峰 ,
  • 邹世龙 ,
  • 刘永泉 ,
  • 刘振侠 ,
  • 孙丹 ,
  • 任国哲 ,
  • 赵欢
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  • 1. 沈阳航空航天大学
    2. 606所
    3. 西北工业大学
    4. 西北工业大学动力与能源学院

收稿日期: 2025-10-30

  修回日期: 2026-01-13

  网络出版日期: 2026-01-15

基金资助

辽宁省自然科学基金博士研究启动项目;辽宁省教育厅基础研究青年项目;国家自然科学基金

Study on the mechanism of interstage sealing air-entraining jet inhibiting compressor corner separation

  • XU Wen-Feng ,
  • ZOU Shi-Long ,
  • LIU Yong-Quan ,
  • LIU Zhen-Xia ,
  • SUN Dan ,
  • REN Guo-Zhe ,
  • ZHAO Huan
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Received date: 2025-10-30

  Revised date: 2026-01-13

  Online published: 2026-01-15

摘要

本次研究深入探究了不同位置和几何结构的级间封严引气射流结构对压气机叶栅气动性能的影响规律,分析了变攻角条件下级间封严引气射流对压气机叶栅角区涡系结构的作用规律及机理。研究发现,随着射流口向尾缘移动以及射流口宽度、高度的增大,引气射流对叶栅总压损失的抑制效果均是先增大后减小。当射流口位于角区分离起始位置、高度为20%叶高、宽度为8%弦长时改善效果最佳,相较于原型能减小8.5%的总压损失。此外,在不同攻角下布置引气射流结构均会减小通道涡节距方向上的影响范围,但会导致分离涡高度不同程度的增大。随着来流攻角的增大,引气射流结构对节距方向分离涡的抑制先增大后减小,同时中径附近的流动损失的增大效果逐渐减弱。为此,0°攻角下呈现出最佳改善效果,显著提升其高负荷压气机叶栅的气动性能。

本文引用格式

徐文峰 , 邹世龙 , 刘永泉 , 刘振侠 , 孙丹 , 任国哲 , 赵欢 . 级间封严引气射流抑制压气机角区分离机理研究[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.33003

Abstract

In this study, the influence of the interstage sealing air-entraining jet structure at different positions and geometric structures on the aerodynamic performance of the compressor cascade is deeply explored. The effect and mechanism of the interstage sealing air-entraining jet on the vortex structure in the corner region of the compressor cascade under the conditions of variable incidence angle are analyzed. It is found that with the movement of the jet port to the trailing edge and the increase of the width and height of the jet port, the suppression effect of the air-entraining jet on the total pressure loss of the cascade increases first and then decreases. When the jet port is located at the starting of corner separation, the height is 20 % blade height and the width is 8 % chord length, the improvement effect is the best, and the total pressure loss can be reduced by 8.5 % compared with the prototype(ORI). In addition, the arrangement of the air-entraining jet structure under different incidence angle conditions reduces the influence range of the passage vortex pitchwise direction, but leads to the increase of the separation vortex height in different degrees. With the increase of the incidence angle, the suppression of the separation vortex in the pitchwise direction by the air-entraining jet structure increases first and then decreases, and the increase effect of the flow loss near the mid-span gradually weakens. For this reason, the improvement effect of the air-entrining jet structure on the cascade performance is first enhanced and then weakened. The best improvement effect is shown at 0 °, and significantly improve the aerodynamic performance of its high-load compressor cascade.

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