二次冲击对静叶前缘冷却性能影响的对比研究

陈欣楠; 李志刚; 李军; 徐庆宗; 杜强

doi:10.7652/xjtuxb202305004

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二次冲击对静叶前缘冷却性能影响的对比研究

能源与动力 | 更新时间：2025-07-09

- 二次冲击对静叶前缘冷却性能影响的对比研究
- A Comparative Study on the Effect of Second-Impingement on the Cooling Performance of Vane Leading Edge
- 西安交通大学学报 2023年57卷第5期页码：34-45
- 作者机构：
  
  1. 西安交通大学叶轮机械研究所,西安,710049
  2. 中国科学院工程热物理研究所,北京,100190
- 作者简介：
  
  : 2022-08-22。作者简介: 陈欣楠(1998—),男,博士生
  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-0022-0043)。
- 基金信息：
  
  : 2022-08-22。作者简介: 陈欣楠(1998—),男,博士生;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-0022-0043)。
- DOI：10.7652/xjtuxb202305004
  中图分类号： TK474.7
- 网络首发：2023-05-10，
  
  纸质出版：2023
- 稿件说明：
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陈欣楠, 李志刚, 李军, 等. 二次冲击对静叶前缘冷却性能影响的对比研究[J]. 西安交通大学学报, 2023,57(5):34-45.

CHEN Xinnan, LI Zhigang, LI Jun, et al. A Comparative Study on the Effect of Second-Impingement on the Cooling Performance of Vane Leading Edge[J]. 2023, 57(5): 34-45.
陈欣楠, 李志刚, 李军, 等. 二次冲击对静叶前缘冷却性能影响的对比研究[J]. 西安交通大学学报, 2023,57(5):34-45. DOI： 10.7652/xjtuxb202305004.

CHEN Xinnan, LI Zhigang, LI Jun, et al. A Comparative Study on the Effect of Second-Impingement on the Cooling Performance of Vane Leading Edge[J]. 2023, 57(5): 34-45. DOI： 10.7652/xjtuxb202305004.

摘要

为了进一步优化现代先进燃机高压涡轮静叶前缘区域的冷却性能

基于NASA C3X叶型建立了上游腔室采用冲击冷却与气膜冷却组合的阵列冲击-气膜复合冷却静叶模型

采用流固共轭传热方法数值研究了涡轮静叶内部冷气的流动和传热特性

针对常用的冷气流量范围分析了引入二次冲击结构对静叶前缘冷却性能的影响。结果表明:二次冲击对靶面对流换热影响较小

但能有效提高冷气在整个流路中的对流换热强度

还能平衡不同区域气膜孔排的冷气流量分配。二次冲击有效降低了气膜孔附近的固体温度

尤其是对于气膜孔较密集的前缘。同时

在固体导热的作用下

气膜孔附近的低温区会影响到无气膜孔区域

降低整个固体域的温度。二次冲击显著改善了叶片上游表面尤其是前缘的复合冷却性能

其中

对上游表面的优化率大体上随冷气流量的增大先升高后降低

在质量流量比M为1.25%时最高

约为4.44%; 对前缘的优化率大体上随冷气流量的增大先降低后升高

在M为1.50%时最低

约为9.66%

在M为2.25%时最高

约为11.70%。

Abstract

To further optimize the cooling performance at the vane leading edge of the modern advanced high-pressure turbine

this paper establishes a NASA C3X turbine vane model in which the upstream chamber is subject to the array impingement-film composite cooling. Fluid-solid conjugate heat transfer analyses are conducted to numerically investigate the flow and heat transfer characteristics of the coolant inside the vane. The effect of second-impingement structure on the composite cooling performance of the leading edge is studied with the amount of coolant mass flux in the common range. The results show that the second-impingement has little effect on convective heat transfer of the target

but can enhance the convective heat transfer intensity of the coolant in the whole flow path. The second-impingement can also balance the distribution of coolant in film holes in different regions and effectively reduce the temperature of the solid domain near film holes

especially for the leading-edge area with the showerhead. Meanwhile

under the heat conduction of the solid domain

the low temperature area near film holes will affect the region nearby

causing a reduction in overall temperature. In addition

the second-impingement significantly improves the composite cooling of the vane surface

especially the leading edge. The optimizing effect on the upstream surface generally increases first and then decreases with the increase of the mass flux of coolant

reaching a highest value of about 4.44% when M is 1.25%. The optimizing effect on the leading edge generally decreases first and then increases with the increase of the mass flux of coolant

reaching a highest value of about 9.66% when M is 1.50%

and a lowest value of about 11.70% when M is 2.25%.

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Keywords

references

翁史烈, 王永泓, 宋华芬, 等. 现代燃气轮机装置 [M]. 上海: 上海交通大学出版社, 2015: 1-10.

HAN J C, DUTTA S, EKKAD S. Gas turbine heat transfer and cooling technology [M]. 2nd ed. Boca Raton, FL, USA: CRC Press, 2013: 1-2.

MOORE J D, EASTERBY C C, BOGARD D G. Effects on film cooling performance in the showerhead from geometric parameterization of shaped hole designs [J]. Journal of Turbomachinery, 2022, 144(9): 091006.

范小军, 杜长河, 李亮, 等. 4种冷却结构对叶片前缘流动换热影响的比较研究 [J]. 西安交通大学学报, 2017, 51(7): 37-43.

FAN Xiaojun, DU Changhe, LI Liang, et al. Comparative analysis for flow and heat transfer behavior of blade leading edge among four cooling structures [J]. Journal of Xi'an Jiaotong University, 2017, 51(7): 37-43.

李健武, 符阳春, 张志伟, 等. 进口雷诺数和湿空气含湿量对冲击冷却流动和传热特性的影响 [J]. 西安交通大学学报, 2020, 54(5): 170-178.

LI Jianwu, FU Yangchun, ZHANG Zhiwei, et al. Influences of inlet Reynolds number and humidity ratio of moist air on flow and heat transfer characteristics of impingement cooling [J]. Journal of Xi'an Jiaotong University, 2020, 54(5): 170-178.

FAWZY H, ZHENG Qun, JIANG Yuting, et al. Conjugate heat transfer of impingement cooling using conical nozzles with different schemes in a film-cooled blade leading-edge [J]. Applied Thermal Engineering, 2020, 177: 115491.

BANG M, KIM S, PARK H S, et al. Impingement/effusion cooling with a hollow cylinder structure for additive manufacturing: effect of channel gap height [J]. International Journal of Heat and Mass Transfer, 2021, 175: 121420.

TEPE A Ü, UYSAL Ü, YETI 瘙塁 KEN Y, et al. Jet impingement cooling on a rib-roughened surface using extended jet holes [J]. Applied Thermal Engineering, 2020, 178: 115601.

姜伟, 谢诞梅, 高尚, 等. 倾角孔对叶片前缘冷却效率影响的数值研究 [J]. 推进技术, 2015, 36(7): 1062-1068.

JIANG Wei, XIE Danmei, GAO Shang, et al. Numerical study of influence of inclined hole on film-cooling effectiveness at leading edge of a turbine blade [J]. Journal of Propulsion Technology, 2015, 36(7): 1062-1068.

李继宸, 朱惠人, 陈大为, 等. 尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究 [J]. 西安交通大学学报, 2019, 53(9): 167-175.

LI Jichen, ZHU Huiren, CHEN Dawei, et al. Experimental study on film cooling effectiveness of the turbine blade with compound-angled fan-shaped holes under wake influence [J]. Journal of Xi'an Jiaotong University, 2019, 53(9): 167-175.

李雪英, 李明飞, 任静, 等. 气膜冷却布置对前缘流动传热的影响 [J]. 工程热物理学报, 2014, 35(12): 2372-2375.

LI Xueying, LI Mingfei, REN Jing, et al. The influence of film cooling arrangement on leading edge flow and heat transfer [J]. Journal of Engineering Thermophysics, 2014, 35(12): 2372-2375.

XIE Gang, TAO Zhi, ZHOU Zhiyu, et al. Effect of leading edge diameter ratio and mainstream Reynolds number on film cooling performance of rotating blade leading edge [J]. Applied Thermal Engineering, 2021, 186: 116047.

CHOWDHURY N H K, QURESHI S A, ZHANG Mingjie, et al. Influence of turbine blade leading edge shape on film cooling with cylindrical holes [J]. International Journal of Heat and Mass Transfer, 2017, 115, Part B: 895-908.

ZHANG Mingjie, WANG Nian, CHEN A F, et al. Influence of turbine blade leading edge profile on film cooling with shaped holes [J]. Journal of Thermal Science and Engineering Applications, 2018, 10(5): 051006.

BRYANT C E, WIESE C J, RUTLEDGE J L, et al. Experimental evaluations of the relative contributions to overall effectiveness in turbine blade leading edge cooling [J]. Journal of Turbomachinery, 2019, 141(4): 041007.

陈欣楠, 李志刚, 李军. 冲击孔偏置对静叶前缘和吸力面冷却性能的影响 [J]. 西安交通大学学报, 2022, 56(4): 50-61.

CHEN Xinnan, LI Zhigang, LI Jun. Effect of impingement offset structure on the performance of leading edge composite cooling and suction surface film cooling [J]. Journal of Xi'an Jiaotong University, 2022, 56(4): 50-61.

张志欣, 李冯, 刘钊, 等. 气膜孔角度对动叶前缘冲击/气膜复合冷却的影响 [J]. 工程热物理学报, 2021, 42(1): 130-135.

ZHANG Zhixin, LI Feng, LIU Zhao, et al. Effect of film hole angle on combined impingement and film cooling on a blade leading edge model [J]. Journal of Engineering Thermophysics, 2021, 42(1): 130-135.

刘钊, 贾哲, 张志欣, 等. 透平动叶前缘冲击-气膜复合冷却与旋流-气膜复合冷却的热流耦合对比研究 [J]. 西安交通大学学报, 2021, 55(4): 116-125.

LIU Zhao, JIA Zhe, ZHANG Zhixin, et al. A comparative study on conjugate heat transfer of impingement-film composite cooling and swirl-film composite cooling on leading edge of a turbine blade [J]. Journal of Xi'an Jiaotong University, 2021, 55(4): 116-125.

JAISWAL A K, MAHAPATRA P S, PRASAD B V S S S. Effect of microchannel on combined impingement and film cooling of a concave surface [J]. International Communications in Heat and Mass Transfer, 2021, 126: 105441.

HYLTON L D, NIRMALAN V, SULTANIAN B K, et al. The effects of leading edge and downstream film cooling on turbine vane heat transfer: NASA-CR-182133 [R].Cleveland, OH, USA: NASA Lewis Research Center, 1988.

DEES J E, BOGARD D G, LEDEZMA G A, et al. Overall and adiabatic effectiveness values on a scaled up, simulated gas turbine vane [J]. Journal of Turbomachinery, 2013, 135(5): 051017.

UNDERWOOD S C. Aerothermodynamics of impingement and film cooling in a gas turbine blade [D]. Lawrence, USA: University of Kansas, 2018.

RAVELLI S, DOBROWOLSKI L, BOGARD D G. Evaluating the effects of internal impingement cooling on a film cooled turbine blade leading edge [C]//ASME Turbo Expo 2010: Power for Land, Sea, and Air. New York, NY, USA: ASME, 2010: 1655-1665.

MATHEW S, RAVELLI S, BOGARD D G. Evaluation of CFD predictions using thermal field measurements on a simulated film cooled turbine blade leading edge [J]. Journal of Turbomachinery, 2013, 135(1): 011021.

HYLTON L D, MIHELC M S, TURNER E R, et al. Analytical and experimental evaluation of the heat transfer distribution over the surfaces of turbine vanes: NASA-CR-168015 [R].Cleveland, OH, USA: NASA Lewis Research Center, 1988.

CHEN Xinnan, LI Zhigang, LI Jun, et al. Effect of Inlet preswirl on the film cooling characteristics of turbine vane surface [C]//ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2022: V06AT12A032.

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