Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment

WANG Zhuo-qi; LU Li-peng; YUAN Wei; SONG Xi-zhen

doi:10.13224/j.cnki.jasp.2014.12.023

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Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment

更新时间：2026-07-07

- Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment
- Vol. 29, Issue 12, Pages: 2948-2956(2014)
- 作者机构：
  
  1. 北京航空航天大学无人驾驶飞行器设计研究所,北京,100191
  2. 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
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.12.023
  CLC：
- Published：2014
- 稿件说明：
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王卓奇, 陆利蓬, 袁巍, 宋西镇. 驻涡式处理机匣对跨声速压气机扩稳的数值模拟[J]. 航空动力学报, 2014, 29(12): 2948-2956.

doi: 10.13224/j.cnki.jasp.2014.12.023
王卓奇, 陆利蓬, 袁巍, 宋西镇. 驻涡式处理机匣对跨声速压气机扩稳的数值模拟[J]. 航空动力学报, 2014, 29(12): 2948-2956. DOI： 10.13224/j.cnki.jasp.2014.12.023.

doi: 10.13224/j.cnki.jasp.2014.12.023 DOI：

摘要

提出了一种驻涡式处理机匣结构

通过叶片通道前后以及叶片压力面和吸力面共同作用的压差

驱动流体产生回流.将通道后部的附面层流体吸除

然后在叶片前缘注入

增大叶尖泄漏流内的动量

从而达到扩稳的效果.该设计将抽气槽与喷气槽的方向和主流流动方向设计成一致方向

以减少掺混损失.此外

该处理机匣在轴向上完全在转子叶片内部

不需要前伸量

因而可以方便地应用于多级压气机中的任何一级

而不会和静子叶片发生干涉.通过数值模拟对这一设计进行了验证

结果表明该处理机匣可以扩大跨声速压气机转子裕度17.39%

而对效率不会产生明显的影响.

Abstract

A type of trapped vortex casing treatment (CT) was designed

using pressure difference between suction side at front and pressure side at rear of passage to drive fluid flowing back. Boundary flow was sucked into slot at rear of passage

then injected into main flow at front of passage. During this process

momentum of the fluid in the leakage was increased

and then the stall margin of the blade was enhanced. The loss of mixing is decreased by adjusting the direction of suction and injection to the direction of main flow. Also the size of CT in axial direction is inside the blade dimention

which means this CT could be used in each stage of multistage compressors

without overlapping with stators. Numerical simulation was used to evaluate the effectiveness of this CT. Result shows that this CT could increase the stall margin 17.39% of a transonic compressor rotor without compromise on efficiency.

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Related Institution

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

先进航空发动机协同创新中心

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

Collaborative Innovation Center for Advanced Aero-Engine

University of Chinese Academy of Sciences

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