Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance

ZHANG Kaiyuan; LI Zhiyu; LI Zhigang; LI Jun

doi:10.7652/xjtuxb202406007

您当前的位置：

首页 >

文章列表页 >

Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance

更新时间：2025-07-28

- Effects of Combustor Louver Coolant and Double-Row Hole Jets on Turbine Endwall Film Cooling Performance
- Vol. 58, Issue 6, Pages: 65-76(2024)
- 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：
- 基金信息：
- DOI：10.7652/xjtuxb202406007
  CLC： TK474.7
- Published：2024
- 稿件说明：
移动端阅览
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：

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

蒋洪德, 任静, 李雪英, 等. 重型燃气轮机现状与发展趋势 [J]. 中国电机工程学报, 2014, 34(29): 5096-5102.

JIANG Hongde, REN Jing, LI Xueying, et al. Status and development trend of the heavy duty gas turbine [J]. Proceedings of the CSEE, 2014, 34(29): 5096-5102.

孙添一, 张垲垣, 李志刚, 等. 燃烧室出流条件对涡轮静叶端壁流动结构和传热冷却特性的影响 [J]. 西安交通大学学报, 2023, 57(1): 152-163.

SUN Tianyi, ZHANG Kaiyuan, LI Zhigang, et al. Effect of combustor outflow conditions on the flow structure and heat transfer cooling characteristics of turbine vane endwall [J]. Journal of Xi'an Jiaotong University, 2023, 57(1): 152-163.

ZHANG Jingzhou, ZHANG Shengchang, WANG Chunhua, et al. Recent advances in film cooling enhancement: a review [J]. Chinese Journal of Aeronautics, 2020, 33(4): 1119-1136.

韦宏, 祖迎庆. 双层壁冷却结构中多排射流冲击冷却的换热和流阻特性 [J]. 航空动力学报, 2021, 36(8): 1621-1632.

WEI Hong, ZU Yingqing. Heat transfer and flow resistance characteristics of multi-row jet impingement cooling in double-wall cooling structure [J]. Journal of Aerospace Power, 2021, 36(8): 1621-1632.

何娟, 邓清华, 高铁瑜, 等. 周向角和直径比对切向双旋流冷却流动与传热特性的作用机理 [J]. 西安交通大学学报, 2020, 54(9): 89-99.

HE Juan, DENG Qinghua, GAO Tieyu, et al. Effects of circumferential angle and diameter ratio on the flow and heat transfer characteristics of double swirl cooling [J]. Journal of Xi'an Jiaotong University, 2020, 54(9): 89-99.

KIM J J, SOHN H S, SONG H S, et al. Effect of profiled endwall on heat transfer under different turbulence intensities [J]. International Communications in Heat and Mass Transfer, 2022, 133: 105935.

朱俊强, 屈骁, 张燕峰, 等. 高负荷低压涡轮内部非定常流动机理及其控制策略研究进展 [J]. 推进技术, 2017, 38(10): 2186-2199.

ZHU Junqiang, QU Xiao, ZHANG Yanfeng, et al. Research progress on unsteady flow mechanism and control strategies of high-lift low pressure turbine [J]. Journal of Propulsion Technology, 2017, 38(10): 2186-2199.

LANGSTON L S. Secondary flows in axial turbines: a review [J]. Annals of the New York Academy of Sciences, 2001, 934(1): 11-26.

FRIEDRICHS S, HODSON H P, DAWES W N. Aerodynamic aspects of endwall film-cooling [J]. Journal of Turbomachinery, 1997, 119(4): 786-793.

MAHI M Y, CHUKWUEMEKA E, DONOVAN S, et al. The influence of turbulence and Reynolds number on endwall heat transfer in a vane cascade [J]. Journal of Turbomachinery, 2023, 145(7): 071012.

李劲劲, 何坤, 晏鑫, 等. 透平叶片近前缘端壁处换热性能的研究 [J]. 西安交通大学学报, 2017, 51(7): 44-50, 104.

LI Jinjin, HE Kun, YAN Xin, et al. Investigation on the heat transfer performance of endwall near the blade leading-edge [J]. Journal of Xi'an Jiaotong University, 2017, 51(7): 44-50, 104.

EL-GABRY L, XU Hongzhou, LIU K, et al. Effect of coolant injection angle on nozzle endwall film cooling: experimental and numerical analysis in linear cascade [C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2018: V05CT19A016.

CHEN Pingting, WANG Lang, LI Xueying, et al. Effect of axial turbine non-axisymmetric endwall contouring on film cooling at different locations [J]. International Journal of Heat and Mass Transfer, 2020, 147: 118995.

李智梅, 萨达姆·侯赛因, 何坤, 等. 前缘倒角造型对叶片端区气热性能影响的研究 [J]. 西安交通大学学报, 2022, 56(1): 130-141.

LI Zhimei, SADAM H, HE Kun, et al. Investigation into the effect of leading-edge contouring on aero-thermal performance in blade endwall region [J]. Journal of Xi'an Jiaotong University,2022, 56(1): 130-141.

XU Shuai, PU Jian, WANG Jianhua, et al. Effects of mainstream cross-flow and wall contouring on film cooling effectiveness of cylindrical-holes embedded in elliptical craters [J]. International Journal of Heat and Mass Transfer, 2022, 194: 123014.

SHIAU C C, SAHIN I, WANG Nian, et al. Turbine vane endwall film cooling comparison from five film-hole design patterns and three upstream injection angles [J]. Journal of Thermal Science and Engineering Applications, 2019, 11(3): 031012.

ZHOU Wenwu, SHAO Hongyi, QENAWY M, et al. Improved turbine vane endwall film cooling by using sand-dune-inspired design [J]. Journal of Thermal Science, 2022, 31(3): 958-973.

周国宇. 透平封严结构及端壁泄漏的流动与传热特性研究 [D]. 北京: 清华大学, 2016.

THRIFT A A, THOLE K A, HADA S. Effects of orientation and position of the combustor-turbine interface on the cooling of a vane endwall [J]. Journal of Turbomachinery, 2012, 134(6): 061019.

MÜLLER G, LANDFESTER C, BÖHLE M, et al. Turbine vane endwall film cooling effectiveness of different purge slot configurations in a linear cascade [J]. Journal of Turbomachinery, 2020, 142(3): 031008.

张杰, 刘存良, 张丽, 等. 槽缝射流和泄漏间隙对轴对称涡轮端壁换热特性的影响 [J]. 推进技术, 2022, 43(4): 195-203.

ZHANG Jie, LIU Cunliang, ZHANG Li, et al. Effects of slot injection and leakage gap on heat transfer characteristics of an axisymmetric turbine endwall [J]. Journal of Propulsion Technology, 2022, 43(4): 195-203.

ORNANO F, POVEY T. Experimental and computational study of the effect of momentum-flux ratio on high-pressure nozzle guide vane endwall cooling systems [J]. Journal of Turbomachinery, 2017, 139(12): 121002.

MAO Shuo, SIBOLD R, NG W F, et al. Experimental study of the endwall heat transfer of a transonic nozzle guide vane with upstream jet purge cooling: part 2 effect of combustor-nozzle guide vane misalignment [J]. Journal of Turbomachinery, 2022, 144(5): 051004.

雷蒋, 鲁瑞山, 秦岭, 等. 静叶栅上游端壁双射流气膜冷却特性实验 [J]. 火箭推进, 2020, 46(2): 36-43.

LEI Jiang, LU Ruishan, QIN Ling, et al. Experimental study of film-cooling characteristics of DJFC holes located upstream of a vane [J]. Journal of Rocket Propulsion, 2020, 46(2): 36-43.

ALQEFL M H. Aero-thermal aspects of endwall cooling flows in a gas turbine nozzle guide vane [D]. Twin Cities: University of Minnesota, 2019.

MAO Shuo, VAN HOUT D, ZHANG Kaiyuan, et al. The cooling effect of combustor exit louver scheme on a transonic nozzle guide vane endwall [C]//ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2022: V06AT11A007.

ZHANG Kaiyuan, LI Zhiyu, WU Jun, et al. Turbine nozzle endwall aero-thermal characteristics under combustor louver coolant with interface cavity [J]. Applied Thermal Engineering, 2023, 219, Part D: 119683.

NAWATHE K P. Experiments on film cooling of gas turbine vane passage surfaces: the effects of various distributions of combustor coolant and endwall injection coolant [D]. Twin Cities: University of Minnesota, 2019.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure

Numerical Study on Deflected Internal Flow and Heat Transfer and Cooling Characteristics of Curved Double-Wall Structures with Pin-Fins

Study on Aerodynamic Characteristics of Gas Turbine Cascade Endwall Under the Interaction of Discrete Film Cooling Holes and Gap Cooling Air Mixing

Numerical Investigation of Interactive Film Cooling Effect Between Blade Showerhead and Endwall in Turbine Cascade Leading Edge Region

Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness

Related Author

WANG Xiangyu

XU Yao

XU Mengjuan

LIU Zhao

FENG Zhenping

QUAN Shuaiyu

BAI Bo

ZHANG Kaiyuan

Related Institution

School of Mechanical Engineering，Xi'an Jiaotong University

School of Energy and Power Engineering，Xi'an Jiaotong University

西安交通大学叶轮机械研究所，710049，西安Institute of Turbomachinery, Xi'an Jiaotong University, Xi'an 710049, China

Institute of Turbomachinery, Xi'an Jiaotong University

TaiHang Laboratory

⁰