离散气膜孔与间隙冷气掺混作用下燃气透平叶栅端壁气动特性研究

张垲垣; 栗智宇; 白波; 李志刚; 李军

doi:10.7652/xjtuxb202509015

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离散气膜孔与间隙冷气掺混作用下燃气透平叶栅端壁气动特性研究

—————————————————————— | 更新时间：2025-09-11

- 离散气膜孔与间隙冷气掺混作用下燃气透平叶栅端壁气动特性研究
- Study on Aerodynamic Characteristics of Gas Turbine Cascade Endwall Under the Interaction of Discrete Film Cooling Holes and Gap Cooling Air Mixing
- 西安交通大学学报 2025年59卷第9期页码：152-164
- 作者机构：
  
  西安交通大学叶轮机械研究所， 710049，西安
- 作者简介：
  
  张垲垣（1993—），男，助理教授
  李军，男，教授，博士生导师。
- 基金信息：
  
  国家自然科学基金资助项目(52406053);国家科技重大专项资助项目(J2019-II-0010-0030);中国博士后科学基金资助项目(2023M742771)
- DOI：10.7652/xjtuxb202509015
  中图分类号： TK474.7
- 收稿：2025-02-18，
  
  网络首发：2025-06-20，
  
  纸质出版：2025-09-10
- 稿件说明：
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张垲垣, 栗智宇, 白波, 等. 离散气膜孔与间隙冷气掺混作用下燃气透平叶栅端壁气动特性研究[J]. 西安交通大学学报, 2025,59(9):152-164.

ZHANG Kaiyuan, LI Zhiyu, BAI Bo, et al. Study on Aerodynamic Characteristics of Gas Turbine Cascade Endwall Under the Interaction of Discrete Film Cooling Holes and Gap Cooling Air Mixing[J]. Journal of Xi’an Jiaotong University, 2025, 59(9): 152-164.
张垲垣, 栗智宇, 白波, 等. 离散气膜孔与间隙冷气掺混作用下燃气透平叶栅端壁气动特性研究[J]. 西安交通大学学报, 2025,59(9):152-164. DOI： 10.7652/xjtuxb202509015.

ZHANG Kaiyuan, LI Zhiyu, BAI Bo, et al. Study on Aerodynamic Characteristics of Gas Turbine Cascade Endwall Under the Interaction of Discrete Film Cooling Holes and Gap Cooling Air Mixing[J]. Journal of Xi’an Jiaotong University, 2025, 59(9): 152-164. DOI： 10.7652/xjtuxb202509015.

摘要

针对燃气透平端壁多源冷却结构射流相互作用及与端区二次流复杂掺混机理尚不明晰的问题，采用叶栅吹风实验与数值模拟方法研究了3种叶栅出口马赫数（0.2、0.3和0.4）和3种冷气吹风比（1.5、2.0和2.5）条件下离散气膜孔与间隙射流的掺混特性及其对叶栅端壁气动性能的影响。研究结果表明，叶栅气动负荷增加导致间隙冷气向下游迁移及近间隙气膜孔冷气出流趋势有所增强，二次流通过卷吸间隙冷气显著影响通道涡及近端壁区域的冷气聚集及气动损失情况。低马赫数（0.2）下，冷气吹风比的升高增强了间隙上游射流和压力侧马蹄涡的脱离趋势，通道涡损失区域向压力侧及近端壁区扩大，其平均总压损失系数增加0.15%，高吹风比间隙射流会被马蹄涡卷吸并降低叶肩临近区域附着效果。高马赫数（0.3和0.4）下，马蹄涡在压力侧的影响范围更大且脱离位置提前，间隙下游低压区面积显著增加，通道涡区域平均总压损失系数随吹风比增加而增大0.1%~0.16%。靠近间隙的气膜孔冷气覆盖面积较小，设计时应增加与间隙的距离，并调节气膜孔流量避免其在间隙处的脱离。

Abstract

To address the unclear mechanisms of jet interaction and complex mixing between multi-source cooling structures and secondary flows in the endwall region of gas turbines

cascade wind tunnel experiments and numerical simulations are conducted to investigate the mixing characteristics of discrete film cooling holes and gap jets

as well as their impact on the aerodynamic performance of cascade endwalls under three cascade exit Mach numbers (0.2

0.3

and 0.4) and three cooling air blowing ratios (1.5

2.0

and 2.5). The results demonstrate that increasing aerodynamic loading on the cascade leads to a stronger tendency for gap cooling air to migrate downstream and for cooling air from film holes near the gap to flow out. The secondary flow significantly affects the accumulation of cooling air in the passage vortices and near the endwall region

leading to increased aerodynamic losses. At low Mach numbers (0.2)

an increase in the cooling air blowing ratio enhances the tendency for upstream gap jets and pressure-side horseshoe vortices to detach. The passage vortex loss area expands towards the pressure side and the near-endwall region

with an average total pressure loss coefficient increasing by 0.15%. At high blowing ratios

gap jets can be drawn in by the horseshoe vortex

reducing the attachment effect in the area adjacent to the blade shoulder. At high Mach numbers (0.3 and 0.4)

the influence of the horseshoe vortex on the pressure side is more significant

and the detachment point advances

significantly increasing the area of the low-pressure region downstream of the gap. The average total pressure loss coefficient in the passage vortex area increases by 0.1% to 0.16% with the increasing blowing ratio. The coverage area of the cooling air from the film holes near the gap is small

suggesting that the design should increase the distance from the gap and adjust the flow rate of the film holes to prevent detachment in the gap region.

关键词

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references

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