Numerical simulation on flow field of axial compressor after bleeding

梁东; 弓志强; 陈灿平; 高山

doi:10.13224/j.cnki.jasp.2017.02.024

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Numerical simulation on flow field of axial compressor after bleeding

更新时间：2026-07-07

- Numerical simulation on flow field of axial compressor after bleeding
- Vol. 32, Issue 2, Pages: 446-454(2017)
- 作者机构：
  
  1. 中国航空发动机集团有限公司中国航空发动机研究院,北京,101304
  2. 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：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.02.024
  CLC：
- Published：2017
- 稿件说明：
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梁东, 弓志强, 陈灿平, 高山. 轴流压气机引气后流场的数值模拟[J]. 航空动力学报, 2017, 32(2): 446-454.

doi: 10.13224/j.cnki.jasp.2017.02.024
梁东, 弓志强, 陈灿平, 高山. 轴流压气机引气后流场的数值模拟[J]. 航空动力学报, 2017, 32(2): 446-454. DOI： 10.13224/j.cnki.jasp.2017.02.024.

doi: 10.13224/j.cnki.jasp.2017.02.024 DOI：

摘要

选取了NASA Stage 35作为算例进行压气机引气数值模拟研究.通过对比验证了网格无关性和计算的准确性

应用两种数值实现方法分别进行圆孔和槽引气计算

两种数值方法的结果基本吻合.进行了两种引气方式（即圆孔和槽）的对比.结果表明:槽引气转子出口总压损失小

效果好于圆孔引气.应用NUMECA软件自带引气模块操作简单

容易实现.绘制引气管路网格增加了流道网格绘制的难度和计算边界条件设置的复杂度

但更加符合压气机实际的引气情况.引气后压气机效率流量曲线整体上移

总压比流量曲线下降

失速裕度有较大提升.

Abstract

By analyzing the transonic singlestage compressors NASA Stage 35

the results of numerical simulation and the experimental results were combined

proving the veracity of numerical simulation. The hole and slot bleeding were calculated by two ways

and the same results were got. At last

the results of hole bleeding and the slot were compared. Result showed that

the slot bleeding was better. The bleeding/cooling block of NUMECA software was easy to realize the bleeding

another way increased the difficulty and complexity of numerical simulation

but it agreed with the fact of bleeding on compressor. Before the bleeding

the efficiency improved

and the total pressure ratio declined little. At same time

stall margin was enhanced.

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Related Institution

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

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Aerospace Technology Institute，China Aerodynamics Research and Development Center

School of Aeronautics and Astronautics， Shanghai Jiao Tong University

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