燃气轮机透平动叶横流带肋通道中气膜冷却研究进展

doi:10.12096/j.2096-4528.pgt.24186

发电技术 ›› 2024, Vol. 45 ›› Issue (5): 781-792.DOI: 10.12096/j.2096-4528.pgt.24186

• 燃气轮机发电技术 •

燃气轮机透平动叶横流带肋通道中气膜冷却研究进展

张超¹^,², 张海川¹^,², 付经伦³^,⁴, 童志庭¹^,², 朱俊强³^,⁴

^1.天津市先进机电系统设计与智能控制重点实验室(天津理工大学机械工程学院)，天津市西青区 300384
^2.机电工程国家级实验教学示范中心(天津理工大学)，天津市西青区 300384
^3.中国科学院大学，北京市海淀区 100049
^4.先进燃气轮机实验室(中国科学院工程热物理研究所)，北京市海淀区 100190

收稿日期:2024-08-20 修回日期:2024-10-01 出版日期:2024-10-31 发布日期:2024-10-29
作者简介:张超(1983)，男，博士，副教授，研究方向为燃气轮机叶片流动与冷却、高效能源动力机械设计，czhangxj@email.tjut.edu.cn；
张海川(1997)，男，硕士研究生，研究方向为气膜冷却技术，zhanghaichuan5@163.com；
付经伦(1979)，女，博士，研究员，研究方向为叶轮机械内透平与关联部件间复杂流动与设计、高负荷冷却透平设计方法，fujl@iet.cn；
童志庭(1977)，男，博士，副教授，研究方向为叶轮机械设计与数值仿真、综合能源系统，tongzhiting1215@163.com；
朱俊强(1964)，男，中国科学院院士，研究员，博士生导师，研究方向为航空发动机基础理论、关键技术攻关和工程应用，zhujq@iet.cn。
基金资助:
国家自然科学基金项目(51976139);江苏省碳达峰碳中和科技创新专项资金(BE2022614)

Research Progress on Film Cooling Fed by Crossflow Ribbed Passage of Gas Turbine Blades

Chao ZHANG¹^,², Haichuan ZHANG¹^,², Jinglun FU³^,⁴, Zhiting TONG¹^,², Junqiang ZHU³^,⁴

^1.Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control (School of Mechanical Engineering, Tianjin University of Technology), Xiqing District, Tianjin 300384, China
^2.National Demonstration Center for Experimental Mechanical and Electrical Engineering Education (Tianjin University of Technology), Xiqing District, Tianjin 300384, China
^3.University of Chinese Academy of Sciences, Haidian District, Beijing 100049, China
^4.Advanced Gas Turbine Laboratory (Institute of Engineering Thermophysics, Chinese Academy of Sciences), Haidian District, Beijing 100190, China

Received:2024-08-20 Revised:2024-10-01 Published:2024-10-31 Online:2024-10-29
Supported by:
National Natural Science Foundation of China(51976139);Special Funds for Science and Technology Innovation of Carbon Peaking and Carbon Neutrality of Jiangsu Province(BE2022614)

摘要/Abstract

摘要：

目的燃气轮机透平进口温度已经远超叶片材料的许用温度，发展更加高效的透平冷却技术，尤其是气膜冷却技术至关重要。在透平动叶中部区域的气膜冷却通常由横流带肋通道供应，因此对近年来横流带肋通道中气膜冷却研究进展进行了综述。方法介绍了不同冷气供应方式下气膜冷却性能的差异，归纳了肋片角度、肋片形式、气膜孔与肋片的相对位置、横流通道进口雷诺数对流动和气膜冷却性能的影响，总结了针对横流带肋冷气条件下气膜孔型设计的研究进展。结果横流带肋通道内部冷却结构和横流通道进口雷诺数对气膜冷却性能影响显著，横流进气改变了孔出口下游的冷却效率分布，同时孔进口处流动受气膜孔与肋片的相对位置及雷诺数变化的影响。展向非对称气膜孔型和对横流进气不敏感的气膜孔型可有效提升气膜冷却性能。结论为进一步推动横流带肋通道气膜冷却技术的发展，建议深入研究各影响因素与气膜冷却性能之间的关系，并对适用于横流带肋进气的专用气膜孔型进行优化设计。

关键词: 燃气轮机, 气膜冷却, 透平冷却, 带肋通道, 透平叶片, 肋片, 叶片冷却, 冷却效率

Abstract:

Objectives The inlet temperature of gas turbine has far exceeded the allowable temperature of the blade material, so it is very important to develop more efficient turbine cooling technology, especially the film cooling technology. The film cooling in the central region of the turbine blade is usually supplied by the crossflow ribbed passage. Therefore, the research progress of the film cooling in the crossflow ribbed passage in recent years was reviewed. Methods The variations in film cooling performance under different coolant supply modes were introduced. The impacts of rib angle, rib shape, relative position of film holes and ribs, and Reynolds number at the inlet of the crossflow channel on flow and film cooling performance were summarized. The research progress of film cooling hole shape design under the condition of crossflow ribbed cooling air was concluded. Results The internal cooling structures within the crossflow ribbed passage and the Reynolds number at the entrance of the crossflow channel exert significant influences on film cooling performance, while the distribution of cooling effectiveness at the hole outlet downstream is altered during crossflow intake. Moreover, the flow at the hole entrance is influenced by both the relative position of the hole and rib as well as changes in Reynolds number. The asymmetrical spanwise cooling hole and the hole insensitive to the crossflow can enhance the film cooling performance. Conclusions In order to further promote the development of film cooling technology in the crossflow ribbed passage, it is recommended to thoroughly study the relationship between film cooling performance and all influencing factors, and to optimize the design of special film cooling hole suitable for crossflow ribbed inlet.

Key words: gas turbine, film cooling, turbine cooling, ribbed passage, turbine blade, rib, blade cooling, cooling efficiency

中图分类号:

TK 14

张超, 张海川, 付经伦, 童志庭, 朱俊强. 燃气轮机透平动叶横流带肋通道中气膜冷却研究进展[J]. 发电技术, 2024, 45(5): 781-792.

Chao ZHANG, Haichuan ZHANG, Jinglun FU, Zhiting TONG, Junqiang ZHU. Research Progress on Film Cooling Fed by Crossflow Ribbed Passage of Gas Turbine Blades[J]. Power Generation Technology, 2024, 45(5): 781-792.

图/表 13

图1 典型透平动叶冷却结构

Fig. 1 Typical cooling structure of turbine blades

图2 不同冷气方向时面积平均冷却效率对比

Fig. 2 Comparison of area averaged cooling effectiveness in different coolant flow directions

图3 横流进气时凹坑型气膜孔的冷却效率分布云图

Fig. 3 Contours of cooling effectiveness distribution of cratered film cooling holes with crossflow

表1 斜置直肋片的角度和冷却性能较优的肋角度

Tab. 1 Angles of inclined straight ribs and the angles of ribs with better cooling performance

来源	肋角度	冷却性能较优的肋角度
文献[18]	60°, 120°	120°
文献[19-20]	45°, 135°	135°
文献[21-22]	45°, 135°	135°
文献[23]	45°, 60°, 90°, 120°, 135°	45°, 135°

图4 45°和135°横流带肋通道示意图

Fig. 4 Diagram of 45° and 135° crossflow ribbed passages

表2 不同形式的肋片结构对比

Tab. 2 Comparison of different rib configurations

来源	肋片形式	连续或间断形式
文献[24]	45°斜置肋	连续
文献[25]	60°斜置肋	连续
文献[26]	直肋	连续、中间间断、侧向间断
文献[17]	直肋、V形肋	连续
文献[27]	正负V形肋	连续
文献[28]	90°直肋、正负月牙形肋	连续
文献[29]	方形肋、圆形肋	连续

图5 光滑、带肋通道及气膜孔附近冷气流线对比

Fig. 5 Comparison of streamlines near the smooth, ribbed passage walls and film cooling holes

图6 月牙形肋通道中气膜孔与肋的相对位置

Fig. 6 Relative position of film cooling hole and crescent rib in coolant supply passage

图7 气膜孔与肋的相对位置示意图

Fig. 7 Schematic diagram of the positions of film cooling hole relative to the rib

图8 槽型孔排相对流向位置

Fig. 8 Relative streamwise positions between the slot diffusion hole and the rib

图9 光滑通道和135°带肋通道冷却效率分布云图

Fig. 9 Contours of cooling effectiveness distribution of the smooth and 135° ribbed passages

图10 中心不对称槽型扩张孔

Fig. 10 Asymmetrical slot cross-section diffusion hole

图11 垂直槽型扩张孔

Fig. 11 Vertically oriented slot cross-section diffusion hole

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燃气轮机透平动叶横流带肋通道中气膜冷却研究进展

Research Progress on Film Cooling Fed by Crossflow Ribbed Passage of Gas Turbine Blades

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