端壁合成射流激励参数变化对跨声速轴流压气机性能的影响

王广; 楚武利; 张皓光; 郭正涛

doi:10.7652/xjtuxb202105021

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端壁合成射流激励参数变化对跨声速轴流压气机性能的影响

更新时间：2025-07-09

- 端壁合成射流激励参数变化对跨声速轴流压气机性能的影响
- Effects of the Endwall Synthetic Jet Excitation Parameters on Performance of Transonic Axial Flow Compressor
- 西安交通大学学报 2021年55卷第5期页码：193-202
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710129
- 作者简介：
- 基金信息：
  
  : 2020-09-21。作者简介: 王广(1981—),男,博士生;楚武利(通信作者),男,教授,博士生导师。基金项目: 国家科技重大专项资助项目(2017-II-0005-0018)
- DOI：10.7652/xjtuxb202105021
  中图分类号： V231.3
- 网络首发：2021-05-10，
  
  纸质出版：2021
- 稿件说明：
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王广, 楚武利, 张皓光, 等. 端壁合成射流激励参数变化对跨声速轴流压气机性能的影响[J]. 西安交通大学学报, 2021,55(5):193-202.

Effects of the Endwall Synthetic Jet Excitation Parameters on Performance of Transonic Axial Flow Compressor[J]. 2021, 55(5): 193-202.
王广, 楚武利, 张皓光, 等. 端壁合成射流激励参数变化对跨声速轴流压气机性能的影响[J]. 西安交通大学学报, 2021,55(5):193-202. DOI： 10.7652/xjtuxb202105021.

Effects of the Endwall Synthetic Jet Excitation Parameters on Performance of Transonic Axial Flow Compressor[J]. 2021, 55(5): 193-202. DOI： 10.7652/xjtuxb202105021.

摘要

为了提升高负荷轴流压气机的气动性能

提出了一种在端壁上施加合成射流的主动流动控制方法。以跨声速轴流压气机NASA Rotor35为研究对象

在固定端壁激励于叶顶堵塞核心位置的基础上

数值模拟了3个激励频率和3个射流峰值速度对该压气机气动性能的影响

获得了端壁合成射流激励参数的影响规律。计算结果表明:激励频率对压气机的近失速流量影响不大

但对总压比和等熵效率有较大影响

并且存在一个激励频率的阈值

只有当激励频率大于该阈值时

才能使得总压比和等熵效率高于原型压气机。射流峰值速度对压气机性能的影响不如激励频率

在超过激励频率阈值的端壁合成射流作用下

即使射流峰值速度较小

压气机也能获得比原型压气机更高的流量裕度、总压比和等熵效率

而且随着射流峰值速度的增大

压气机的性能还可以进一步提高。

Abstract

To improve the aerodynamic performance of high-load axial compressor

an active flow control method with synthetic jet applied on the endwall was proposed. A transonic axial flow compressor NASA Rotor35 was taken as the research object. On the basis of fixed endwall excitation at the core of blade tip blockage

the influences of three excitation frequencies and three jet peak velocities on the aerodynamic performance of the compressor were numerically simulated

and the influencing rules of the endwall synthetic jet excitation parameters were obtained. The results show that the excitation frequency has little influence on the near stall flow of the compressor

but has great influence on the total pressure ratio and isentropic efficiency. It is also found that there is a threshold of excitation frequency

and only when the excitation frequency is greater than the threshold

can the total pressure ratio and isentropic efficiency be higher than those of the prototype compressor. The effect of jet peak velocity on the performance of compressor is inferior to the excitation frequency. Under the action of the endwall synthetic jet exceeding the excitation frequency threshold

the compressor can obtain higher flow margin

total pressure ratio and isentropic efficiency than the prototype compressor even if the peak velocity of the jet is small

and the performance of the compressor can be further improved with the increase of the jet peak velocity.

关键词

Keywords

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