End Wall Boundary Layer Suction Method for Performance Enhancement and Flow Field Regulation of Transonic Compressor Cascades

TANG Jie; MENG Fanjie; GONG Chaoxuan; LI Jingyin; GUO Penghua

doi:10.7652/xjtuxb202503008

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End Wall Boundary Layer Suction Method for Performance Enhancement and Flow Field Regulation of Transonic Compressor Cascades

更新时间：2026-01-06

- End Wall Boundary Layer Suction Method for Performance Enhancement and Flow Field Regulation of Transonic Compressor Cascades
- Journal of Xi’an Jiaotong University Vol. 59, Issue 3, Pages: 77-88(2025)
- 作者机构：
  
  西安交通大学能源与动力工程学院， 710049，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202503008
  CLC： TK05
- Received：06 June 2024，
  
  Online First：21 October 2024，
  
  Published：10 March 2025
- 稿件说明：
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TANG Jie, MENG Fanjie, GONG Chaoxuan, et al. End Wall Boundary Layer Suction Method for Performance Enhancement and Flow Field Regulation of Transonic Compressor Cascades[J]. Journal of Xi’an Jiaotong University, 2025, 59(3): 77-88.
DOI：

TANG Jie, MENG Fanjie, GONG Chaoxuan, et al. End Wall Boundary Layer Suction Method for Performance Enhancement and Flow Field Regulation of Transonic Compressor Cascades[J]. Journal of Xi’an Jiaotong University, 2025, 59(3): 77-88. DOI： 10.7652/xjtuxb202503008.

摘要

针对跨声速叶栅吹风试验中叶栅流动与二维流动不一致的问题，以某F级重型燃气轮机的跨声速叶栅为研究对象，提出一种槽宽为5 mm的抽吸槽，采用不同端壁抽吸位置、抽吸流量的附面层抽吸方案，通过数值模拟探究各方案对跨声速叶栅气动性能及流场结构的影响规律，分析比较各方案对角区分离的控制效果。仿真结果表明：端壁抽吸能够有效吸除通道内大量的低能流体，抽吸后叶栅总体的总压损失系数降低、静压比提高、轴向密流比（AVDR，设为

VDR

）被控制在1附近，出口流道内高损耗区（总压损失

0.2）显著减小；角区分离得到有效控制，角涡以及集中脱落涡的影响被削弱，流道通流面积增大，流场品质得到改善；通过对比不同抽吸位置的抽吸方案发现，靠近尾缘，距叶片前缘60%轴向弦长的抽吸槽方案气动性能最佳，抽吸后静压比增大14.4%，流场二维性最好，角区分离最弱；抽吸后，叶栅激波强度在近端壁区增大，尾迹整体范围减小，三维效应被削弱，增压能力得到增强；通过对比不同抽吸流量的抽吸方案发现，当抽吸流量较大时，叶栅的

VDR

能够维持在1附近、静压比较大，而出气角以及总压损失系数变化较小，同时角区分离较弱。因此，在跨声速叶栅中，沿弦向且靠近尾缘的抽吸方案在较大抽吸流量下能够对流场进行调控，叶栅的气动性能提升，角区分离得到控制，叶栅流动与二维流动较为一致。

Abstract

Addressing the inconsistency between the flow in the transonic blade cascade and the two-dimensional flow observed in wind tunnel tests

this study focuses on the transonic cascades of a certain F-class heavy-duty gas turbine. A 5 mm wide suction slot is proposed to investigate the impact of different endwall suction positions and suction flow rates in the attached layer suction scheme on the aerodynamic performance and flow field structure of the transonic cascade through numerical simulation. This study analyzes and compares the control effects of different schemes on the separation in the corner region. Simulation results indicate that endwall suction can effectively remove a large amount of low-energy fluid inside the passage. After suction

the overall total pressure loss coefficient of the cascade decreases

static pressure ratio increases

and the axial velocity density ratio (AVDR

set as

VDR

) is controlled around 1

significantly reducing the high-loss region (

0.2) in the exit passage. The control of corner separation is effective

weakening the effects of corner vortices and concentrated separation vortices

increasing the flow passage area

and improving the flow field quality. By comparing suction schemes at different suction positions

it is observed that the suction slot scheme near the trailing edge

at 60% of the axial chord length from the leading edge

achieves the best aerodynamic performance

with a 14.4% increase in static pressure ratio after suction

the best two-dimensional flow consistency

and the weakest corner separation. After suction

the shock wave intensity near the endwall increases

the overall extent of the wake decreases

three-dimensional effects are reduced

and the boosting capability is enhanced. Comparing suction schemes with different suction flow rates reveals that with higher suction flow rates

the cascade's

VDR

can be maintained around 1

with a higher static pressure ratio

while the change in outlet flow angle and total pressure loss coefficient is minimal

and corner separation is weaker. Therefore

in transonic compressor cascades

the suction scheme along the chord and near the trailing edge can control the flow field under higher suction flow rates

enhance the aerodynamic performance of the cascade

control corner separation

and align the cascade flow with two-dimensional flow patterns.

关键词

Keywords

references

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