Effects of specific swirl distortion on performance of transonic compressor

WANG Jiale; CHENG Bangqin; ZHANG Lei

doi:10.13224/j.cnki.jasp.2020.03.010

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Effects of specific swirl distortion on performance of transonic compressor

更新时间：2026-07-07

- Effects of specific swirl distortion on performance of transonic compressor
- Vol. 35, Issue 3, Pages: 540-551(2020)
- 作者机构：
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- DOI：10.13224/j.cnki.jasp.2020.03.010
  CLC：
- Published：2020
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王加乐, 程邦勤, 张磊. 特定涡旋流畸变对跨声速压气机性能的影响[J]. 航空动力学报, 2020, 35(3): 540-551.

doi: 10.13224/j.cnki.jasp.2020.03.010
王加乐, 程邦勤, 张磊. 特定涡旋流畸变对跨声速压气机性能的影响[J]. 航空动力学报, 2020, 35(3): 540-551. DOI： 10.13224/j.cnki.jasp.2020.03.010.

doi: 10.13224/j.cnki.jasp.2020.03.010 DOI：

摘要

为研究S弯进气道出口和翼身融合体(HWB)飞机发动机进口两种特定涡旋流对压气机气动性能和稳定性的影响

将设计的新型叶片式旋流畸变发生器与跨声速压气机Stage 67进行联合数值仿真

获得进口旋流条件下的压气机特性线和流场分布

并与转子进口为均匀来流时进行对比分析。结果表明:在100%换算转速

S弯进气道产生的旋流使得压气机压比和效率在近峰值效率点分别下降0.06%、0.85%

稳定工作流量范围减小5.97%

压气机稳定裕度降低1.13%

压比和效率特性线均向左下方移动。HWB飞机产生的旋流使得压气机在近峰值效率点的压比增大6.61%

效率下降6.25%

稳定工作流量范围减小26.88%

压气机稳定裕度降低2.84%

压比特性线向右上方移动

效率特性线向右下方移动。

Abstract

The StreamVane swirl distortion generator was combined with transonic compressor Stage 67 using numerical simulation to investigate the effect of swirl distortion generated by exit of S-duct inlet and hybrid wing body (HWB) on the performance and stability of compressor. The compressor characteristic map and flow field were obtained by this method and compared with characteristic map and flow field with uniform inflows. There existed a maximum decrease of pressure ratio

efficiency

stability mass flow rate and stability margin by 0.06%

0.85%

5.97% and 1.13%

respectively

with 100% corrected speed under the effect of the S-duct inlet swirl distortion. Both pressure ratio and efficiency characteristic lines moved to the lower left. There existed a maximum decrease of efficiency

stability mass flow rate and stability margin by 6.25%

26.88%

2.84% and a maximum increase pressure ratio by 6.61% respectively with 100% corrected speed under the effect of the HWB swirl distortion. The pressure ratio characteristic lines moved to the upper right

the efficiency characteristic lines moved to the lower right.

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Related Institution

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

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School of Energy Science and Engineering, Harbin Institute of Technology

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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