燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究

张垲垣; 栗智宇; 李志刚; 李军

doi:10.7652/xjtuxb202406007

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燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究

—————————————————————— | 更新时间：2025-07-28

- 燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究
- Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance
- 西安交通大学学报 2024年58卷第6期页码：65-76
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
  
  : 2023-08-13。作者简介: 张垲垣(1993—),男,工学博士,助理教授
  李军(通信作者),男,教授,博士生导师。基金项目: 国家科技重大专项资助项目(J2019-Ⅱ-0011-0031)
- 基金信息：
  
  : 2023-08-13。作者简介: 张垲垣(1993—),男,工学博士,助理教授;李军(通信作者),男,教授,博士生导师。基金项目: 国家科技重大专项资助项目(J2019-Ⅱ-0011-0031);国家自然科学基金资助项目(51936008)
- DOI：10.7652/xjtuxb202406007
  中图分类号： TK474.7
- 纸质出版：2024
- 稿件说明：
移动端阅览
张垲垣, 栗智宇, 李志刚, 等. 燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究[J]. 西安交通大学学报, 2024,58(6):65-76.

ZHANG Kaiyuan, LI Zhiyu, LI Zhigang, et al. Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance[J]. 2024, 58(6): 65-76.
张垲垣, 栗智宇, 李志刚, 等. 燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究[J]. 西安交通大学学报, 2024,58(6):65-76. DOI： 10.7652/xjtuxb202406007.

ZHANG Kaiyuan, LI Zhiyu, LI Zhigang, et al. Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance[J]. 2024, 58(6): 65-76. DOI： 10.7652/xjtuxb202406007.

摘要

针对燃烧室与透平冷气掺混导致实际二次流发展及端壁冷却性能偏离设计值的问题

综合考虑燃烧室百叶冷气尾迹与双排孔射流

数值研究了多源冷气射流在燃烧室与透平交界区的掺混机制

分析了其对透平静叶端壁气膜冷却与流动特性的影响规律。研究结果表明:空腔涡卷吸大部分百叶冷气

并跨越双排孔冷气向下游发展

马蹄涡卷吸限制大部分双排孔冷气

并向空腔涡外侧发展; 当双排孔冷气吹风比M

=0.5

1.0较小时

马蹄涡导致冷气形成楔形高冷效区域

空腔涡的附着侧和分离侧分别产生了高、低冷效区

随着百叶冷气吹风比M

的增加

空腔涡强度显著降低

导致位于楔形中心的分离侧冷却效率有所提升; 当双排孔冷气吹风比M

为1.5时

双排孔冷气部分跨越马蹄涡

静叶端壁可实现完全冷气覆盖

此时百叶冷气吹风比M

从0.5增加到1.5

静叶端壁平均冷却效率可从0.4提升到0.63。该研究为考虑燃烧室与透平交界区实际流动掺混情况的静叶端壁冷却结构与布局设计提供理论基础。

Abstract

Aiming at the problem of secondary flow development and cooling effect deviation from the design value caused by the actual mix condition between combustor and turbine coolant jets

comprehensively considering the combustor louver coolant and the turbine double-row hole jets

the coolant mix mechanism at combustor-turbine interface is numerically studied in this paper

and its influence on the cooling and flow characteristics of turbine vane endwall is analyzed too. The results show that the majority of the louver

coolant is entrained by the cavity vortex to develop downstream across the double-row hole jets

and the double-row hole jets are largely entrained by the horseshoe vortex to develop on the outer side of cavity vortex. At low double-row hole blowing ratios(M

=0.5 and 1.0)

the horseshoe vortices lead to a wedge-shaped high cooling effectiveness region

and the attachment and separation side of cavity vortices lead to high and low cooling effectiveness regions

respectively. With the increase of louver blowing ratio

the cavity vortex is weakened

and the cooling effectiveness at wedge-shaped region core increases. At high double-row hole blowing ratio(M

=1.5)

the hole jets can partly flow across the horseshoe vortex

and the vane endwall can be fully covered. With the increase of louver coolant blowing ratio from 0.5 to 1.5

the averaged cooling effectiveness of the vane endwall increases from 0.4 to 0.63. This study can provide a theoretical foundation for the design of turbine vane endwall cooling layout considering the actual flow mixing conditions at the combustor-turbine interface.

关键词

Keywords

references

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