冷却孔结构对燃烧室性能和壁面冷却效果影响的数值模拟研究

杨欢; 郭舒; 詹政德; 文键; 王家瑞

doi:10.7652/xjtuxb202411009

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冷却孔结构对燃烧室性能和壁面冷却效果影响的数值模拟研究

—————————————————————— | 更新时间：2025-07-25

- 冷却孔结构对燃烧室性能和壁面冷却效果影响的数值模拟研究
- Numerical Simulation Research on the Influence of Cooling Hole Structure on Combustor Performance and Liner Wall Cooling Effect
- 西安交通大学学报 2024年58卷第11期页码：98-108
- 作者机构：
  
  1. 西安交通大学能源与动力工程学院,西安,710049
  2. 中国航发沈阳发动机研究所,沈阳,110015
  3. 西安交通大学金禾经济研究中心,西安,710049
  4. 西安交通大学化学工程与技术学院,西安,710049
- 作者简介：
  
  : 2024-05-06。作者简介: 杨欢(1998—),男,博士生
  王家瑞(通信作者),男,副教授,硕士生导师。基金项目: 中国航空发动机集团产学研合作项目(HFZL2022CXY010)
- 基金信息：
  
  : 2024-05-06。作者简介: 杨欢(1998—),男,博士生;王家瑞(通信作者),男,副教授,硕士生导师。基金项目: 中国航空发动机集团产学研合作项目(HFZL2022CXY010);国家自然科学基金资助项目(22308273)。
- DOI：10.7652/xjtuxb202411009
  中图分类号： TK16
- 纸质出版：2024
- 稿件说明：
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杨欢, 郭舒, 詹政德, 等. 冷却孔结构对燃烧室性能和壁面冷却效果影响的数值模拟研究[J]. 西安交通大学学报, 2024,58(11):98-108.

YANG Huan, GUO Shu, ZHAN Zhengde, et al. Numerical Simulation Research on the Influence of Cooling Hole Structure on Combustor Performance and Liner Wall Cooling Effect[J]. 2024, 58(11): 98-108.
杨欢, 郭舒, 詹政德, 等. 冷却孔结构对燃烧室性能和壁面冷却效果影响的数值模拟研究[J]. 西安交通大学学报, 2024,58(11):98-108. DOI： 10.7652/xjtuxb202411009.

YANG Huan, GUO Shu, ZHAN Zhengde, et al. Numerical Simulation Research on the Influence of Cooling Hole Structure on Combustor Performance and Liner Wall Cooling Effect[J]. 2024, 58(11): 98-108. DOI： 10.7652/xjtuxb202411009.

摘要

为提高燃烧室出口温度分布均匀性并解决火焰筒前端壁面烧蚀问题

建立了带有多斜孔发散冷却结构的贫燃预混燃烧室三维模型

基于k-ω SST湍流模型、FGM燃烧模型、离散相模型及DO辐射模型等

模拟研究了冷却孔直径和角度对燃烧室性能及壁面冷却效果的影响规律。结果表明:当冷却孔直径从0.5 mm增大至1.0 mm时

出口温度分布系数从0.068增至0.438

径向温度分布系数从0.060增至0.419

燃烧效率从99.94%降低至99.25%; 随着冷却孔直径的增大

燃烧室出口平均温度和燃烧效率不断降低

出口温度场分布逐渐恶化; 当冷却孔角度为20°、40°和60°时

火焰筒前端受到高温旋流燃气直接冲击

冷却效果较差

而冷却空气在火焰筒中后段形成了发展光顺、厚度均匀的温度层

冷却效果较好; 当冷却孔角度为90°时

垂直布置的冷却孔能够改善火焰筒前端高温旋流燃气冲刷壁面的问题

但火焰筒中后段的壁面冷却效果大幅恶化。该研究结果能够为贫燃预混燃烧室发散冷却结构的设计提供一定的参考。

Abstract

To improve the uniformity of the temperature distribution at the outlet of the combustor and solve the wall ablation issue at the front end of the liner

a three-dimensional model of a lean-burn premixed combustor with an effusion cooling structure is established. Based on the k-ω SST turbulence model

FGM combustion model

discrete phase model

and DO radiation model

the effects of the cooling hole diameter and angle on the performance of the combustor performance and the wall cooling effect is simulated and studied. The results indicate that when the cooling hole diameter increases from 0.5 mm to 1.0 mm

the outlet temperature distribution factor rises from 0.068 to 0.438

the radial temperature distribution factor surges from 0.060 to 0.419

and the combustion efficiency decreases from 99.94% to 99.25%. As the cooling hole diameter increases

the average outlet temperature and combustion efficiency continuously decrease

and the temperature distribution at the outlet of the combustor gradually deteriorates. When the cooling hole angles are 20°

40°

and 60°

the front section of the liner is directly impacted by high-temperature swirling gases

resulting in poor cooling effectiveness. However

effective cooling is achieved in the middle and rear sections of the liner

which forms a smooth and uniform temperature layer. When the cooling hole angle is 90°

vertically arranged cooling holes alleviate the issue of high-temperature swirling gases impacting the front section of the liner

but the cooling effect in the middle and rear sections of the liner significantly deteriorates. The research results may provide a certain reference for the design of divergent cooling structures in lean-burn premixed combustors.

关键词

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references

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