叶顶喷气对凹槽叶尖气动性能的影响

轩笠铭; 邹正平; 赵强; 黄霖; 杜金霖; 陈云

doi:10.13224/j.cnki.jasp.20210104

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叶顶喷气对凹槽叶尖气动性能的影响

叶轮机械 | 更新时间：2025-04-07

- 叶顶喷气对凹槽叶尖气动性能的影响
- Effect of tip injection on aerodynamic performance of squealer tip
- 航空动力学报 2022年37卷第5期页码：1030-1041
- 作者机构：
  
  1.北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191
  2.北京航空航天大学航空发动机研究院，北京 102206
  3.中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015
- 作者简介：
  
  轩笠铭（1993-），男，博士生，主要从事叶轮机械气动热力学研究。
  邹正平（1970-），男，教授，博士，主要从事高超声速航空发动机、叶轮机气体动力学研究。E⁃mail：zouzhengping@buaa.edu.cn
- 基金信息：
  
  国家自然科学基金(51676005)
- DOI：10.13224/j.cnki.jasp.20210104
  中图分类号：
- 稿件说明：
移动端阅览
轩笠铭, 邹正平, 赵强, 等. 叶顶喷气对凹槽叶尖气动性能的影响[J]. 航空动力学报, 2022,37(5):1030-1041.

Liming XUAN, Zhengping ZOU, Qiang ZHAO, et al. Effect of tip injection on aerodynamic performance of squealer tip[J]. Journal of Aerospace Power, 2022, 37(5): 1030-1041.
轩笠铭, 邹正平, 赵强, 等. 叶顶喷气对凹槽叶尖气动性能的影响[J]. 航空动力学报, 2022,37(5):1030-1041. DOI： 10.13224/j.cnki.jasp.20210104.

Liming XUAN, Zhengping ZOU, Qiang ZHAO, et al. Effect of tip injection on aerodynamic performance of squealer tip[J]. Journal of Aerospace Power, 2022, 37(5): 1030-1041. DOI： 10.13224/j.cnki.jasp.20210104.

摘要

对某型航空发动机高压涡轮转子叶片通过相似变换得到的低速叶型进行研究，探讨叶尖机匣相对运动条件下，叶顶喷气对凹槽叶尖气动性能的影响。结果表明：叶顶喷气对平叶尖的气动性能影响有限，但会降低凹槽叶尖效率；在相同喷气条件下，使用凹槽叶尖相比于使用平叶尖可降低20%的叶尖泄漏损失；泄漏流在凹槽内部的能量耗散主要来自于泄漏流动与凹槽涡和刮削涡的相互作用，在喷气条件下，刮削涡仍然是泄漏流动的主要控制结构。喷气位置对凹槽叶尖性能有显著的的影响；在靠近吸力侧和前缘布置喷气孔，有利于凹槽气动性能的提升；基于以上研究，建立可用于凹槽叶尖的泄漏流动损失模型，新模型相比Denton模型误差降低了31.6%。

Abstract

A low⁃speed blade profile of a certain aero⁃engine high⁃pressure turbine rotor blade obtained by similarity transformation was studied

and the effect of tip injection on the aerodynamic performance of the squealer tip under the condition of relative casing motion was discussed.The results showed that tip injection had limited effect on the aerodynamic performance of the flat tip

but it could reduce the efficiency of the squealer tip.Under the same injection condition

the squealer tip can reduce the tip leakage loss by 20% compared with the flat tip.The energy dissipation of the leakage flow in the cavity mainly came from the interaction of the leakage flow with cavity vortex and scraping vortex.Under the injection condition

scraping vortex was still the dominant flow structure of the leakage flow.The injection position had a significant effect on the performance of the squealer tip; the jet holes near the suction side and leading edge were conducive to the improvement of the aerodynamic performance.Based on the above research

a leakage flow loss model for the squealer tip was established

and the error of new model was reduced by 31.6% compared with the Denton model.

关键词

Keywords

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