某发动机涡轮导向器叶片冷却结构优化设计及实验

江金涛; 董素艳; 董荣晓; 王之声; 史鹏宇; 刘蓬晖; 范玮

doi:10.13224/j.cnki.jasp.20240833

某发动机涡轮导向器叶片冷却结构优化设计及实验

doi: 10.13224/j.cnki.jasp.20240833

1.
西北工业大学动力与能源学院，西安 710029
2.
中国运载火箭技术研究院空间物理重点实验室，北京 100076

基金项目: 国家自然科学基金重点项目（52336006）；超高温冷却叶片多学科协同设计平台开发项目

详细信息

作者简介:
江金涛（1991-），男，博士生，主要从事燃烧室设计研究。E-mail：npu_jt@mail.nwpu.edu.cn

通讯作者:
董素艳（1974-），男，副研究员，博士，主要从事涡轮叶片设计及仿真研究。E-mail：dsy@nwpu.edu.cn

中图分类号: V231.1
计量
- 文章访问数: 499
- HTML浏览量: 543
- PDF量: 51
- 被引次数: 0
出版历程
- 收稿日期: 2024-12-10
- 网络出版日期: 2025-08-19

Optimization design and experiment on the cooling structure of turbine guide vane in an engine

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710029，China
2.
Science and Technology on Space Physics Laboratory，China Academy of Launch Vehicle Technology，Beijing 100076，China

摘要

摘要:
针对某型发动机涡轮导向器叶片尾缘出现烧蚀及裂纹的问题，结合增材制造复杂型面快速成型的工艺特点，采用数值模拟方法对涡轮叶片冷却结构进行优化设计，并对涡轮导向器叶片冷却结构方案进行了实验研究。搭建的涡轮叶片综合冷效实验平台可以模拟真实的发动机工作参数，基于实验平台开展了落压比、温度比及流量比等关键参数对叶片综合冷却效率及无量纲温度分布的试验研究。实验结果表明：流量比对涡轮叶片综合冷却效率的影响高于温度比及落压比，在实验工况范围内，当流量比从0.75%增大至1.50%时，叶片综合冷却效率从0.123增大至0.183，提高了48.78%；当温度比从1.5增大至2.0时，叶片综合冷却效率从0.165增大至0.199，提高了20.61%；当落压比从1.4增大至2.2时，叶片综合冷却效率从0.141增大至0.162，提高了14.08%。
- 增材制造 /
- 涡轮叶片 /
- 冷却结构 /
- 气膜冷却 /
- 冷却效率
Abstract:
To address the issue of ablation and cracks on the trailing edge of the turbine guide blade in an aeroengine, the process characteristics of rapid prototyping of complex surfaces were combined using additive manufacturing, numerical simulation methods were employed to optimize the design of turbine blade cooling structures, and experimental research on the cooling structure schemes of turbine guide blades was conducted. The constructed experimental platform can simulate real engine operating parameters for turbine blade cooling efficiency. Based on this experimental platform, experiments were conducted on the effects of parameters such as pressure ratio, temperature ratio, and flow ratio on the overall cooling efficiency and dimensionless temperature distribution of the blade. The experimental results indicated that the effect of flow rate ratio on the cooling efficiency of the turbine blades was greater than that of temperature ratio and pressure ratio. Within the experimental operating range, as the flow ratio increased from 0.75% to 1.50%, the blade cooling efficiency increased from 0.123 to 0.183, representing an improvement of 48.78%. When the temperature ratio increased from 1.5 to 2.0, the blade cooling efficiency rose from 0.165 to 0.199, an increase of 20.61%. As the pressure ratio increased from 1.4 to 2.2, the blade cooling efficiency grew from 0.141 to 0.162, an enhancement of 14.08%.
- additive manufacturing /
- turbine blade /
- cooling structure /
- film cooling /
- cooling efficiency

HTML

图 1 实验系统图

Figure 1. Schematic of experimental system

下载: 全尺寸图片幻灯片

图 2 叶片实验段模型

Figure 2. Model of turbine blade experimental section

下载: 全尺寸图片幻灯片

图 3 涡轮叶片表面热电偶测点布置示意图

Figure 3. Schematic diagram of thermocouple measurement points on the turbine blade surface

下载: 全尺寸图片幻灯片

图 4 带热电偶测试叶片实物图

Figure 4. Photos of experimental blade with thermocouples

下载: 全尺寸图片幻灯片

图 5 原涡轮叶片模型图

Figure 5. Prototype turbine blade model

下载: 全尺寸图片幻灯片

图 6 计算域及边界条件

Figure 6. Schematic diagram of computational domain and boundary conditions

下载: 全尺寸图片幻灯片

图 7 计算域及网格划分

Figure 7. Computational domain and mesh

下载: 全尺寸图片幻灯片

图 8 网格细节图

Figure 8. Details of mesh

下载: 全尺寸图片幻灯片

图 9 仿真与实验数据对比

Figure 9. Comparison of simulation and experimental data

下载: 全尺寸图片幻灯片

图 10 叶片表面温度分布云图

Figure 10. Surface temperature distribution of turbine blades

下载: 全尺寸图片幻灯片

图 11 冷却结构方案1模型图

Figure 11. Model of cooling structure scheme 1

下载: 全尺寸图片幻灯片

图 12 冷却结构方案1叶片表面温度分布

Figure 12. Blade surface temperature distribution of cooling structure scheme 1

下载: 全尺寸图片幻灯片

图 13 冷却结构方案1气膜孔出流流线图

Figure 13. Streamlines emanating from film cooling holes of cooling structure scheme 1

下载: 全尺寸图片幻灯片

图 14 冷却结构方案2模型图

Figure 14. Model of cooling structure scheme 2

下载: 全尺寸图片幻灯片

图 15 冷却结构方案2叶片表面温度分布

Figure 15. Blade surface temperature distribution of cooling structure scheme 2

下载: 全尺寸图片幻灯片

图 16 冷却结构方案2气膜孔出流流线图

Figure 16. Streamlines emanating from film cooling holes of cooling structure scheme 2

下载: 全尺寸图片幻灯片

图 17 冷却结构方案3模型图

Figure 17. Model of cooling structure scheme 3

下载: 全尺寸图片幻灯片

图 18 冷却结构方案3叶片表面温度分布

Figure 18. Blade surface temperature distribution of cooling structure scheme 3

下载: 全尺寸图片幻灯片

图 19 冷却结构方案3气膜孔出流流线图

Figure 19. Streamlines emanating from film cooling holes of cooling structure scheme 2

下载: 全尺寸图片幻灯片

图 20 流量比对涡轮叶片冷却性能影响

Figure 20. Effect of flow ratio on turbine blade cooling performance

下载: 全尺寸图片幻灯片

图 21 叶片综合冷却效率随流量比变化曲线

Figure 21. Variation curve of blade cooling efficiency with flow ratio

下载: 全尺寸图片幻灯片

图 22 温度比对涡轮叶片冷却性能影响

Figure 22. Effect of temperature ratio on turbine blade cooling performance

下载: 全尺寸图片幻灯片

图 23 叶片综合冷却效率随温度比变化曲线

Figure 23. Variation curve of blade cooling efficiency with temperature ratio

下载: 全尺寸图片幻灯片

图 24 落压比对涡轮叶片冷却性能影响

Figure 24. Effect of pressure ratio on turbine blade cooling performance

下载: 全尺寸图片幻灯片

图 25 叶片综合冷却效率随落压比变化曲线

Figure 25. Variation curve of blade cooling efficiency with pressure ratio

下载: 全尺寸图片幻灯片

图 26 叶片综合冷却效率曲线斜率随流量比变化

Figure 26. Slope of the blade cooling efficiency curve varies with flow ratio

下载: 全尺寸图片幻灯片

图 27 叶片综合冷却效率曲线随温度比变化

Figure 27. Slope of the blade cooling efficiency curve varies with temperature ratio

下载: 全尺寸图片幻灯片

图 28 叶片综合冷却效率随落压比变化

Figure 28. Slope of the blade cooling efficiency curve varies with pressure ratio

下载: 全尺寸图片幻灯片

表 1 实验中测量参数、范围及精度

Table 1. Experimental parameters, ranges, and measurement uncertainties

参数	测量仪器	范围	精度/%
叶片表面温度进/出口总温进/出口总压进/出口静压	K型热电偶 K型热电偶压力传感器A 压力传感器B	273～1000 K 273～1000 K 0.5～1.5 MPa 0.1～5.0 MPa	0.5 0.5 0.5 0.5
二次流质量流量	流量计	0.1～100 g/s	1.0
二次流质量流量	流量控制器	0.1～5.0 g/s	0.05

下载: 导出CSV

表 2 网格无关性验证

Table 2. Gird-independence validation

网格数量/10⁶	3.0	4.0	6.5	9.0
叶片平均温度/K	1069.7	1075.3	1078.6	1074.3

下载: 导出CSV

表 3 计算工况

Table 3. Calculation conditions

参数	数值
$p_{{\mathrm{in}}}^*$/MPa	1.34
T_g/K	1284.6
$\dot m_{\mathrm{g}} $/（kg/s）	0.585
p_c/MPa	1.41
T_c/K	708.5

下载: 导出CSV

表 4 冷却结构方案1～3空气流量参数对比

Table 4. Comparison of cooling air flow parameters among cooling structure scheme 1—3

方案编号	冷却空气质量流量/（kg/s）
方案编号	前缘	尾缘
1	0.063	0.027
2	0.042	0.040
3	0.033	0.033

下载: 导出CSV

表 5 原涡轮叶片和冷却结构方案3的气动参数对比

Table 5. Comparison of aerodynamic parameters between prototype turbine blade and cooling structure scheme 3

参数	原叶片	方案3	偏差/%
燃气出口总压/MPa	1.244	1.210	2.8
燃气出口静压/MPa	0.625	0.624	0.2
二次流出口总压/MPa	1.385	1.382	0.2
二次流出口静压/MPa	1.378	1.377	0.1

下载: 导出CSV

表 6 叶片实验工况

Table 6. Turbine blade experimental conditions

参数	数值
B/%	0.75，1.00，1.25，1.50
K	1.5，1.6，1.7，1.9，2.0
β	1.4，1.6，1.8，2.0，2.2

下载: 导出CSV

参考文献(34)

[1]	廉筱纯, 吴虎. 航空发动机原理[M]. 西安: 西北工业大学出版社, 2005: 122-145. LIAN Xiaochun, WU Hu. Aeroengine principle[M]. Xi’an: Northwestern Polytechnical University Press, 2005: 122-145. (in Chinese LIAN Xiaochun, WU Hu. Aeroengine principle[M]. Xi’an: Northwestern Polytechnical University Press, 2005: 122-145. (in Chinese)
[2]	ZENG Qinghua, CHEN Xuanwu. Combustor technology of high temperature rise for aero engine[J]. Progress in Aerospace Sciences, 2023, 140: 100927. doi: 10.1016/j.paerosci.2023.100927
[3]	孔祥灿, 张子卿, 朱俊强, 等. 航空发动机气冷涡轮叶片冷却结构研究进展[J]. 推进技术, 2022, 43(5): 200632. KONG Xiangcan, ZHANG Ziqing, ZHU Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese KONG Xiangcan, ZHANG Ziqing, ZHU Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese)
[4]	NOURIN F N, AMANO R S. Review of gas turbine internal cooling improvement technology[J]. Journal of Energy Resources Technology, 2021, 143(8): 080801. doi: 10.1115/1.4048865
[5]	ZHU Huaitao, XIE Gongnan, ZHU Rui, et al. Comparisons on flow characteristics and film cooling performance of cylindrical and sister holes with/without internal coolant crossflow[J]. International Journal of Thermal Sciences, 2022, 182: 107791. doi: 10.1016/j.ijthermalsci.2022.107791
[6]	YE Lin, LIU Cunliang, LIU Haiyong, et al. Experimental and numerical study on the effects of rib orientation angle on film cooling performance of compound angle holes[J]. International Journal of Heat and Mass Transfer, 2018, 126: 1099-1112. doi: 10.1016/j.ijheatmasstransfer.2018.06.064
[7]	CHEN Guanjiang, LIU Yuyang, RAO Yu, et al. Numerical investigation on conjugate heat transfer of impingement/effusion double-wall cooling with different crossflow schemes[J]. Applied Thermal Engineering, 2019, 155: 515-524. doi: 10.1016/j.applthermaleng.2019.04.019
[8]	ZHANG Mingjie, WANG Nian, HAN J C. Internal heat transfer of film-cooled leading edge model with normal and tangential impinging jets[J]. International Journal of Heat and Mass Transfer, 2019, 139: 193-204. doi: 10.1016/j.ijheatmasstransfer.2019.04.140
[9]	ZHANG Mingjie, WANG Nian, HAN J C. Overall effectiveness of film-cooled leading edge model with normal and tangential impinging jets[J]. International Journal of Heat and Mass Transfer, 2019, 139: 577-587. doi: 10.1016/j.ijheatmasstransfer.2019.05.037
[10]	贾广森, 张丽, 卢聪明, 等. 内冷通道横流条件下气膜冷却特性[J]. 航空动力学报, 2015, 30(4): 823-830. JIA Guangsen, ZHANG Li, LU Congming, et al. Film cooling performance with internal coolant channel crossflow[J]. Journal of Aerospace Power, 2015, 30(4): 823-830. (in Chinese JIA Guangsen, ZHANG Li, LU Congming, et al. Film cooling performance with internal coolant channel crossflow[J]. Journal of Aerospace Power, 2015, 30(4): 823-830. (in Chinese)
[11]	THOLE K A, GRITSCH M, SCHULZ A, et al. Effect of a crossflow at the entrance to a film-cooling hole[J]. Journal of Fluids Engineering, 1997, 119(3): 533-540. doi: 10.1115/1.2819277
[12]	RAO Yu, CHEN Peng, WAN Chaoyi. Experimental and numerical investigation of impingement heat transfer on the surface with micro W-shaped ribs[J]. International Journal of Heat and Mass Transfer, 2016, 93: 683-694. doi: 10.1016/j.ijheatmasstransfer.2015.10.022
[13]	KALGHATGI P, ACHARYA S. Flow dynamics of a film cooling jet issued from a round hole embedded in contoured crater[J]. Journal of Turbomachinery, 2019, 141(8): 081006. doi: 10.1115/1.4043071
[14]	张志鑫, 曾武, 卞祥德, 等. 热障涂层对涡轮动叶温度及应力的影响研究[J]. 推进技术, 2023, 44(5): 2204035. ZHANG Zhixin, ZENG Wu, BIAN Xiangde, et al. Effects of thermal barrier coating on temperature and stress of turbine rotor blade[J]. Journal of Propulsion Technology, 2023, 44(5): 2204035. (in Chinese ZHANG Zhixin, ZENG Wu, BIAN Xiangde, et al. Effects of thermal barrier coating on temperature and stress of turbine rotor blade[J]. Journal of Propulsion Technology, 2023, 44(5): 2204035. (in Chinese)
[15]	朱剑琴, 赵超凡, 邱璐, 等. 热障涂层在涡轮叶片应用中的热防护有效性[J]. 航空动力学报, 2019, 34(11): 2503-2508. ZHU Jianqin, ZHAO Chaofan, QIU Lu, et al. Thermal protection effectiveness of thermal barrier coatings in turbine blade applications[J]. Journal of Aerospace Power, 2019, 34(11): 2503-2508. (in Chinese ZHU Jianqin, ZHAO Chaofan, QIU Lu, et al. Thermal protection effectiveness of thermal barrier coatings in turbine blade applications[J]. Journal of Aerospace Power, 2019, 34(11): 2503-2508. (in Chinese)
[16]	骆剑霞. 涡轮叶片内冷结构对外部气膜冷却特性的影响研究[D]. 西安: 西北工业大学, 2015. LUO Jianxia. Study on the influence of internal cooling structure of turbine blades on external film cooling characteristics[D]. Xi’an: Northwestern Polytechnical University, 2015. (in Chinese LUO Jianxia. Study on the influence of internal cooling structure of turbine blades on external film cooling characteristics[D]. Xi’an: Northwestern Polytechnical University, 2015. (in Chinese)
[17]	THOLE K, SINHA A, BOGRAD D, et al. Mean temperature measurements of jets with a crossflow for gas turbine film cooling application [C]// Proceedings of the Third International Conference on Theoretical, Applied and Experimental Mechanics. Austin, Texas, US: University of Texas at Austin, 1992: 69-85.
[18]	李佳, 任静, 蒋洪德. 密度比和吹风比对透平静叶气膜冷却的影响[J]. 工程热物理学报, 2011, 32(8): 1295-1298. LI Jia, REN Jing, JIANG Hongde. Effects of density ratio and blowing ratio on the film cooling effectiveness on a turbine vane[J]. Journal of Engineering Thermophysics, 2011, 32(8): 1295-1298. (in Chinese LI Jia, REN Jing, JIANG Hongde. Effects of density ratio and blowing ratio on the film cooling effectiveness on a turbine vane[J]. Journal of Engineering Thermophysics, 2011, 32(8): 1295-1298. (in Chinese)
[19]	JOHNSON B, TIAN Wei, ZHANG Kai, et al. An experimental study of density ratio effects on the film cooling injection from discrete holes by using PIV and PSP techniques[J]. International Journal of Heat and Mass Transfer, 2014, 76: 337-349. doi: 10.1016/j.ijheatmasstransfer.2014.04.028
[20]	PEDERSEN D R, ECKERT E R G, GOLDSTEIN R J. Film cooling with large density differences between the mainstream and the secondary fluid measured by the heat-mass transfer analogy[J]. Journal of Heat Transfer, 1977, 99(4): 620-627. doi: 10.1115/1.3450752
[21]	JUNG I S, LEE J S, LIGRANI P M. Effects of bulk flow pulsations on film cooling with compound angle holes: heat transfer coefficient ratio and heat flux ratio[J]. Journal of Turbomachinery, 2002, 124(1): 142-151. doi: 10.1115/1.1400110
[22]	HAN B, SOHN D K, LEE J S. Flow and heat transfer measurements of film injectant from a row of holes with compound angle orientations[J]. KSME International Journal, 2002, 16(9): 1137-1146. doi: 10.1007/BF02984433
[23]	HAYDT S, LYNCH S, LEWIS S. The effect of a meter-diffuser offset on shaped film cooling hole adiabatic effectiveness[J]. Journal of Turbomachinery, 2017, 139(9): 091012. doi: 10.1115/1.4036199
[24]	HAYDT S, LYNCH S, LEWIS S. The effect of area ratio change via increased hole length for shaped film cooling holes with constant expansion angles[J]. Journal of Turbomachinery, 2018, 140(5): 051002. doi: 10.1115/1.4038871
[25]	HAYDT S, LYNCH S. Cooling effectiveness for a shaped film cooling hole at a range of compound angles[J]. Journal of Turbomachinery, 2019, 141(4): 041005. doi: 10.1115/1.4041603
[26]	SAMBHAV K, TANDON P, KAPOOR S G, et al. Mathematical modeling of cutting forces in microdrilling[J]. Journal of Manufacturing Science and Engineering, 2013, 135(1): 014501. doi: 10.1115/1.4007955
[27]	於之杰, 郭玉佩, 孙汉斌, 等. 先进材料及工艺的结构完整性研究进展[J]. 航空学报, 2024, 45(18): 029888. YU Zhijie, GUO Yupei, SUN Hanbin, et al. Recent progress in structural integrity of novel materials and advanced techniques[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 029888. (in Chinese YU Zhijie, GUO Yupei, SUN Hanbin, et al. Recent progress in structural integrity of novel materials and advanced techniques[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 029888. (in Chinese)
[28]	刘新灵, 陶春虎, 刘春江, 等. 航空发动机叶片气膜孔加工方法及其演变分析[J]. 材料导报, 2013, 27(21): 117-120. LIU Xinling, TAO Chunhu, LIU Chunjiang, et al. Investigation of processing methods and development of gas holes of engine blade[J]. Materials Review, 2013, 27(21): 117-120. (in Chinese LIU Xinling, TAO Chunhu, LIU Chunjiang, et al. Investigation of processing methods and development of gas holes of engine blade[J]. Materials Review, 2013, 27(21): 117-120. (in Chinese)
[29]	DEBROY T, WEI H L, ZUBACK J S, et al. Additive manufacturing of metallic components-process, structure and properties[J]. Progress in Materials Science, 2018, 92: 112-224. doi: 10.1016/j.pmatsci.2017.10.001
[30]	李志勇, 韩冬雪, 焦世坤, 等. 激光增材制造在航天领域的实践与展望[J]. 中国激光, 2024, 51(24): 2402305. LI Zhiyong, HAN Dongxue, JIAO Shikun, et al. Practice and prospect of laser additive manufacturing in aerospace field[J]. Chinese Journal of Lasers, 2024, 51(24): 2402305. (in Chinese doi: 10.3788/CJL240687 LI Zhiyong, HAN Dongxue, JIAO Shikun, et al. Practice and prospect of laser additive manufacturing in aerospace field[J]. Chinese Journal of Lasers, 2024, 51(24): 2402305. (in Chinese) doi: 10.3788/CJL240687
[31]	陶云亚, 薛伟鹏, 唐洪飞, 等. 激光增材制造技术在涡轮叶片中的应用[J]. 燃气涡轮试验与研究, 2016, 29(6): 44-50, 55. TAO Yunya, XUE Weipeng, TANG Hongfei, et al. Application of laser additive manufacturing technology in turbine blade and vane[J]. Gas Turbine Experiment and Research, 2016, 29(6): 44-50, 55. (in Chinese doi: 10.3969/j.issn.1672-2620.2016.06.010 TAO Yunya, XUE Weipeng, TANG Hongfei, et al. Application of laser additive manufacturing technology in turbine blade and vane[J]. Gas Turbine Experiment and Research, 2016, 29(6): 44-50, 55. (in Chinese) doi: 10.3969/j.issn.1672-2620.2016.06.010
[32]	MOFFAT R J. Describing the uncertainties in experimental results[J]. Experimental Thermal and Fluid Science, 1988, 1(1): 3-17. doi: 10.1016/0894-1777(88)90043-X
[33]	WALTERS D K, LEYLEK J H. Impact of film-cooling jets on turbine aerodynamic losses[J]. Journal of Turbomachinery, 2000, 122(3): 537-545. doi: 10.1115/1.1303818
[34]	NA S, ZHU Bin, BRYDEN M, et al. CFD analysis of film cooling[R]. AIAA 2006-22, 2006.