重型燃气轮机护环部件的复合冲击冷却特性研究

殷宇阳; 武安; 吴宏; 李雪英; 任静

doi:10.19805/j.cnki.jcspe.2026.250685

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重型燃气轮机护环部件的复合冲击冷却特性研究

更新时间：2026-10-06

- 重型燃气轮机护环部件的复合冲击冷却特性研究
- Study on Compound Impingement Cooling Characteristics of Ring Segment Components in a Heavy-duty Gas Turbine
- 动力工程学报 2026年46卷第3期页码：168-176
- 作者机构：
  
  1. 中国联合重型燃气轮机技术有限公司,北京,100016
  2. 清华大学能源与动力工程系,北京,100084
- 作者简介：
- 基金信息：
- DOI：10.19805/j.cnki.jcspe.2026.250685
  中图分类号：
- 网络首发：2026-03-10，
  
  纸质出版：2026-03-10
- 稿件说明：
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殷宇阳,武安,吴宏,李雪英,任静. 重型燃气轮机护环部件的复合冲击冷却特性研究动力工程学报, 2026, 46(3): 168-176 https://doi.

org/10.19805/j.cnki.jcspe.2026.250685
殷宇阳,武安,吴宏,李雪英,任静. 重型燃气轮机护环部件的复合冲击冷却特性研究动力工程学报, 2026, 46(3): 168-176 https://doi. DOI： 10.19805/j.cnki.jcspe.2026.250685.

org/10.19805/j.cnki.jcspe.2026.250685 DOI：

摘要

随着重型燃气轮机透平进口温度持续升高

传统冲击冷却技术难以满足透平高温部件日益增长的冷却需求。针对透平的护环部件

在传统冲击冷却结构基础上

通过在冲击靶面设置不同扰流结构

设计了4种复合冲击冷却单元

并将其应用于护环部件的冷却方案中

采用半耦合数值模拟方法研究了各方案在F级、G/H级、HL级燃机工况下的综合冷却特性。结果表明:靶面采用离散型扰流结构可使热通量提升13.1%~17.6%

其中圆柱肋加球槽复合靶面结构(PF)构型的冷却性能最优;在H级燃机侧热负荷条件下

采用复合冷却单元护环方案的冷却效果可提升3.3%~9.3%

且高毕渥数条件下(如HL级)冷却效果增幅会进一步扩大

最大增幅为10.1%;复合方案的射流系数降低了1.2%~7.5%

相较于传统方案将其应用在自主下一代燃机产品的透平高温部件中更具优势。

Abstract

With the continual rise in turbine inlet temperatures of heavy-duty gas turbines

conventional impingement cooling techniques are increasingly inadequate to meet the growing cooling demands of high-temperature turbine components. Focusing on turbine ring segment components

four combined impingement cooling unit configurations based on traditional impingement cooling structures by incorporating various turbulence-enhancing structures on the target surface were proposed. And they were applied to cooling scheme for ring segment components. The semi-coupled numerical simulation method was used to study the comprehensive cooling characteristics of each scheme under the operating conditions of F-class

G/H-class

and HL-class gas turbines. The results demonstrate that applying discrete turbulence-enhancing structures on the target surface increases heat flux by 13.1%-17.6%. Among these configurations

the pin-fin with dimpled surface (PF) configuration exhibits the optimal cooling performance. Under the operating conditions of H-class

the cooling effectiveness of the ring segment scheme utilizing combined cooling units is improved by 3.3%-9.3%

with a more pronounced enhancement under high Biot number conditions (e.g.

HL-class)

reaching a maximum improvement of 10.1%. The discharge coefficient of the combined scheme is reduced by 1.2%-7.5%. Compared with traditional approaches

the proposed method has more advantages when applied to the high-temperature components of the turbine in the next-generation autonomous gas turbine products.

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Keywords

references

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