发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究

孙添一; 李志刚; 李军

doi:10.7652/xjtuxb202201014

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发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究

更新时间：2025-05-08

- 发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究
- Investigation on the Flow Structure of Turbine Vane Endwall under Effects of Effusion Cooling and Leading Edge Slot Jet
- 西安交通大学学报 2022年56卷第1期页码：120-129
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
  
  李军（通信作者），男，教授，博士生导师。
- 基金信息：
  
  : 2021-06-25。作者简介: 孙添一(1998—),男,硕士生;李军(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(51936008,51776151)
- DOI：10.7652/xjtuxb202201014
  中图分类号： TK474.7
- 网络首发：2022-01-10，
  
  纸质出版：2022
- 稿件说明：
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孙添一, 李志刚, 李军. 发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究[J]. 西安交通大学学报, 2022,56(1):120-129.

SUN Tianyi, LI Zhigang, LI Jun. Investigation on the Flow Structure of Turbine Vane Endwall under Effects of Effusion Cooling and Leading Edge Slot Jet[J]. 2022, 56(1): 120-129.
孙添一, 李志刚, 李军. 发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究[J]. 西安交通大学学报, 2022,56(1):120-129. DOI： 10.7652/xjtuxb202201014.

SUN Tianyi, LI Zhigang, LI Jun. Investigation on the Flow Structure of Turbine Vane Endwall under Effects of Effusion Cooling and Leading Edge Slot Jet[J]. 2022, 56(1): 120-129. DOI： 10.7652/xjtuxb202201014.

摘要

数值研究了无发散冷却与3种发散冷却气质量流量比下的涡轮静叶端壁附近涡结构、总压损失系数和端壁、叶表绝热冷却有效度以及两种冷却气在端壁上的流动结构。研究表明:发散冷却气质量流量比由5%增加至7%时

进口截面端壁附近的总压峰值升高3.7%

峰值区流体在叶片前缘滞止后向上卷起形成冲击涡; 发散冷却流量增加会增强冲击涡而吸力面角区涡对被削弱。低流量冷却气会使整体总压损失降低

而发散冷却气质量流量比由5%升高至7%时总压损失增加4.5%。发散冷却气注入时

冲击涡会将冷却气携带至叶表

在压力面形成显著的泛冷却效果; 发散冷却气质量流量比增加至7%会使冲击涡纵向伸长并分裂出三次涡。发散冷却贡献占比的计算结果表明

边界层分离线上游端壁由槽缝射流冷却气覆盖

而叶表和下游端壁的冷却由发散冷却主导。静叶端壁流动结构受到上游燃烧室内壁发散冷却的显著影响

并将改变端壁冷却特性。

Abstract

The vortex system near the turbine vane endwall

total pressure loss coefficient

adiabatic cooling effectiveness distribution on the endwall and vane surface

as well as the distribution of two cooling structures

are numerically investigated via the case without effusion cooling and the cases with three kinds of effusion cooling mass flow rates(M). The obtained results show that the peak total pressure near endwall of the inlet is increased by 3.7% when M increases from 5% to 7%. The increase of M can strengthen the impingement vortex and weaken the suction-side corner vortices. The effusion cooling with low mass flow rate can reduce the total pressure loss

however

the total pressure loss is increased by 4.5% when M increases from 5% to 7%. With effusion cooling

coolants are carried to the vane surface by the impingement vortex

thus the phantom cooling effect on the pressure surface is significant. When M is 7%

the impingement vortex may exhibit spanwise extension and a tertiary vortex is split out. The calculation results of the contribution percentage of effusion cooling show that the endwall upstream of the boundary layer separation line is covered mainly by the slot jet flow

while the cooling effectiveness of vane surface and downstream endwall is dominated by effusion cooling. The upstream combustor liner effusion cooling may significantly affect the flow structure near endwall

as well as the aerothermal and cooling performances of turbine vane endwall.

关键词

Keywords

references

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