| Citation: | Zhao Jinghan, Fang Xiangjun, Liu Xin, et al. Aerodynamic design and flow field analysis of integrated combustion vanes in heavy-duty gas turbines[J]. Journal of Aerospace Power, 2027, 42（1）：20250391 doi: 10.13224/j.cnki.jasp.20250391
|
A design method of combining overall configuration with local refinement for the integrated aerodynamic design of the combustor and the first-stage turbine guide vanes in a heavy-duty gas turbine was proposed. Three-dimensional numerical simulations were conducted to analyze the aerodynamic performance under different numbers of unit bodies and leading-edge truncation lengths. The results showed that the leading-edge structure had no significant effect on the outlet flow parameters, while increasing the truncation length effectively reduced the total pressure loss coefficient to below 5%, thus validating the effectiveness of the proposed method. Flow field analysis revealed that the integrated combustion vanes exhibited compound characteristics of axial contraction, circumferential swirl, and radial skewed flow, with blades and endwalls jointly governing flow acceleration and turning. Compared with conventional guide vanes, the integrated design eliminated the mechanisms of leading-edge impingement stagnation and horseshoe vortex formation, while wake-vortex-dominated periodic vortex pairs became the primary secondary flow structures.
| [1] |
曹玉璋, 陶智, 徐国强, 等. 航空发动机传热学[M]. 北京: 北京航空航天大学出版社, 2005.
|
| [2] |
朱莉娅, 徐国强. 涡轮冷却技术对航空发动机性能的影响[J]. 推进技术, 2014, 35(6): 793-798. Zhu Liya, Xu Guoqiang. Influence of turbine cooling technology on aero-engine performance[J]. Journal of Propulsion Technology, 2014, 35(6): 793-798. (in Chinese doi: 10.13675/j.cnki.tjjs.2014.06.011
Zhu Liya, Xu Guoqiang. Influence of turbine cooling technology on aero-engine performance[J]. Journal of Propulsion Technology, 2014, 35(6): 793-798. (in Chinese) doi: 10.13675/j.cnki.tjjs.2014.06.011
|
| [3] |
刘松龄, 陶智. 燃气涡轮发动机的传热和空气系统[M]. 上海: 上海交通大学出版社, 2018.
|
| [4] |
张少平, 侯美丽, 李恒, 等. 新一代航空发动机新结构设计及其对新材料与新工艺需求分析[J]. 航空学报, 2025, 46(23): 276-292. Zhang Shaoping, Hou Meili, Li Heng, et al. Analysis of new structural designs and requirements for new materials and manufacturing processes in next generation aircraft engines[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(23): 276-292. (in Chinese doi: 10.7527/S1000-6893.2025.31793
Zhang Shaoping, Hou Meili, Li Heng, et al. Analysis of new structural designs and requirements for new materials and manufacturing processes in next generation aircraft engines[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(23): 276-292. (in Chinese) doi: 10.7527/S1000-6893.2025.31793
|
| [5] |
刘李旭, 王新锋, 姚甜. 高熵合金在燃气轮机中的应用研究[J]. 中国设备工程, 2024(22): 21-23. Liu Lixu, Wang Xinfeng, Yao Tian. Study on application of high entropy alloy in gas turbine[J]. China Plant Engineering, 2024(22): 21-23. (in Chinese doi: 10.3969/j.issn.1671-0711.2024.22.009
Liu Lixu, Wang Xinfeng, Yao Tian. Study on application of high entropy alloy in gas turbine[J]. China Plant Engineering, 2024(22): 21-23. (in Chinese) doi: 10.3969/j.issn.1671-0711.2024.22.009
|
| [6] |
王一丹, 郭谦, 周琪杰, 等. 先进航空发动机高温功能涂层研究进展[J]. 航空材料学报, 2024, 44(5): 48-69. Wang Yidan, Guo Qian, Zhou Qijie, et al. Research progress in high temperature functional coatings for advanced aeroengines[J]. Journal of Aeronautical Materials, 2024, 44(5): 48-69. (in Chinese doi: 10.11868/j.issn.1005-5053.2024.000117
Wang Yidan, Guo Qian, Zhou Qijie, et al. Research progress in high temperature functional coatings for advanced aeroengines[J]. Journal of Aeronautical Materials, 2024, 44(5): 48-69. (in Chinese) doi: 10.11868/j.issn.1005-5053.2024.000117
|
| [7] |
王昆, 邹兰欣, 郭磊, 等. 航空发动机及燃气轮机热障涂层高温腐蚀与防护[J]. 中国腐蚀与防护学报, 2025, 45(1): 1-19. Wang Kun, Zou Lanxin, Guo Lei, et al. High-temperature corrosion and protection of thermal barrier coatings for aeroengines and gas turbines[J]. Journal of Chinese Society for Corrosion and Protection, 2025, 45(1): 1-19. (in Chinese doi: 10.11902/1005.4537.2024.227
Wang Kun, Zou Lanxin, Guo Lei, et al. High-temperature corrosion and protection of thermal barrier coatings for aeroengines and gas turbines[J]. Journal of Chinese Society for Corrosion and Protection, 2025, 45(1): 1-19. (in Chinese) doi: 10.11902/1005.4537.2024.227
|
| [8] |
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 doi: 10.13675/j.cnki.tjjs.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) doi: 10.13675/j.cnki.tjjs.200632
|
| [9] |
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
|
| [10] |
Aslanidou I, Rosic B, Kanjirakkad V, et al. Leading edge shielding concept in gas turbines with can combustors[J]. Journal of Turbomachinery, 2013, 135(2): 021019. doi: 10.1115/1.4007514
|
| [11] |
Jacobi S, Rosic B. Development and aerothermal investigation of integrated combustor vane concept[J]. Journal of Turbomachinery, 2016, 138: 011002. doi: 10.1115/1.4031560
|
| [12] |
Aslanidou I, Rosic B. Aerothermal performance of shielded vane design[J]. Journal of Turbomachinery, 2017, 139(11): 111003. doi: 10.1115/1.4037126
|
| [13] |
Jacobi S, Rosic B. Influence of combustor flow with swirl on integrated combustor vane concept full-stage performance[J]. Journal of Turbomachinery, 2018, 140: 011002. doi: 10.1115/1.4037820
|
| [14] |
Hughes M J, Berry J D, Zhao Wei, et al. DLN evo combustion technology development for a high-hydrogen flexible F-class retrofit[R]. ASME GT2023-101797, 2023.
|
| [15] |
吴晶峰, 蒋洪德. 重型燃气轮机燃烧室过渡段气动造型设计及性能分析[J]. 中国电机工程学报, 2013, 33(17): 90-97, 17. Wu Jingfeng, Jiang Hongde. Investigation of transition piece structure design and aerodynamic performance in heavy duty gas turbine combustors[J]. Proceedings of the CSEE, 2013, 33(17): 90-97, 17. (in Chinese
Wu Jingfeng, Jiang Hongde. Investigation of transition piece structure design and aerodynamic performance in heavy duty gas turbine combustors[J]. Proceedings of the CSEE, 2013, 33(17): 90-97, 17. (in Chinese)
|
| [16] |
叶莹, 尹钊, 赵洪雷, 等. 进口过渡段对热斑/气冷涡轮时序效应的影响[J]. 燃气轮机技术, 2017, 30(1): 15-20. Ye Ying, Yin Zhao, Zhao Honglei, et al. Influence of transition section to clocking effects of hot spot and cooled turbine[J]. Gas Turbine Technology, 2017, 30(1): 15-20. (in Chinese
Ye Ying, Yin Zhao, Zhao Honglei, et al. Influence of transition section to clocking effects of hot spot and cooled turbine[J]. Gas Turbine Technology, 2017, 30(1): 15-20. (in Chinese)
|
| [17] |
于征磊. 燃气轮机燃烧室过渡段流场数值模拟[D]. 长春: 吉林大学, 2011. Yu Zhenglei. Numerical simulation of flow in transition piece of gas turbine combustor[D]. Changchun: Jilin University, 2011. (in Chinese
Yu Zhenglei. Numerical simulation of flow in transition piece of gas turbine combustor[D]. Changchun: Jilin University, 2011. (in Chinese)
|
| [18] |
耿俊杰, 祁海鹰. 燃气轮机燃烧室过渡段“多造型函数组合”的设计方法[J]. 动力工程学报, 2020, 40(7): 540-548, 555. Geng Junjie, Qi Haiying. Design method for transition pieces in gas turbine combustors based on multi-modeling function combination[J]. Journal of Chinese Society of Power Engineering, 2020, 40(7): 540-548, 555. (in Chinese doi: 10.19805/j.cnki.jcspe.2020.07.004
Geng Junjie, Qi Haiying. Design method for transition pieces in gas turbine combustors based on multi-modeling function combination[J]. Journal of Chinese Society of Power Engineering, 2020, 40(7): 540-548, 555. (in Chinese) doi: 10.19805/j.cnki.jcspe.2020.07.004
|
| [19] |
付仲议, 杜英杰, 叶炜, 等. 燃烧室出口旋流对高压涡轮导叶压力面异型孔气膜冷却的影响[J]. 航空动力学报, 2026, 41(3): 20240828. Fu Zhongyi, Du Yingjie, Ye Wei, et al. Effect of combustor exit swirl on film cooling characteristics of shaped holes on the pressure surface of high-pressure turbine vanes[J]. Journal of Aerospace Power, 2026, 41(3): 20240828. (in Chinese doi: 10.13224/j.cnki.jasp.20240828
Fu Zhongyi, Du Yingjie, Ye Wei, et al. Effect of combustor exit swirl on film cooling characteristics of shaped holes on the pressure surface of high-pressure turbine vanes[J]. Journal of Aerospace Power, 2026, 41(3): 20240828. (in Chinese) doi: 10.13224/j.cnki.jasp.20240828
|
| [20] |
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. (in Chinese doi: 10.7652/xjtuxb202301015
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. (in Chinese) doi: 10.7652/xjtuxb202301015
|
| [21] |
江立军, 曹俊, 陶焰明, 等. 燃烧室涡轮交互作用尺度自适应模拟[J]. 航空动力学报, 2021, 36(10): 2186-2196. Jiang Lijun, Cao Jun, Tao Yanming, et al. Combustor turbine interaction based on scale adaptive simulation[J]. Journal of Aerospace Power, 2021, 36(10): 2186-2196. (in Chinese doi: 10.13224/j.cnki.jasp.20200493
Jiang Lijun, Cao Jun, Tao Yanming, et al. Combustor turbine interaction based on scale adaptive simulation[J]. Journal of Aerospace Power, 2021, 36(10): 2186-2196. (in Chinese) doi: 10.13224/j.cnki.jasp.20200493
|
| [22] |
周洁, 宛鹏翔, 韩省思, 等. 燃烧室-涡轮耦合流动传热超大涡模拟研究[J]. 推进技术, 2022, 43(3): 246-256. Zhou Jie, Wan Pengxiang, Han Xingsi, et al. Very-large eddy simulation of turbulent flow and heat transfer for coupled combustor-turbine components[J]. Journal of Propulsion Technology, 2022, 43(3): 246-256. (in Chinese doi: 10.13675/j.cnki.tjjs.200370
Zhou Jie, Wan Pengxiang, Han Xingsi, et al. Very-large eddy simulation of turbulent flow and heat transfer for coupled combustor-turbine components[J]. Journal of Propulsion Technology, 2022, 43(3): 246-256. (in Chinese) doi: 10.13675/j.cnki.tjjs.200370
|
| [23] |
方祥军, 刘思永, 王屏, 等. 大扩张通道超声高载荷对转涡轮动叶三维设计方法研究[J]. 航空学报, 2007, 28(1): 25-31. Fang Xiangjun, Liu Siyong, Wang (Bing| Ping), et al. Research of 3D design method for rotor of supersonic high loaded contra-rotating turbine with large expansile meridional channel[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(1): 25-31. (in Chinese doi: 10.3321/j.issn:1000-6893.2007.01.004
Fang Xiangjun, Liu Siyong, Wang (Bing| Ping), et al. Research of 3D design method for rotor of supersonic high loaded contra-rotating turbine with large expansile meridional channel[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(1): 25-31. (in Chinese) doi: 10.3321/j.issn:1000-6893.2007.01.004
|
| [24] |
刘智刚, 方祥军, 刘思永, 等. 某变循环发动机超声涡轮设计与分析[J]. 航空动力学报, 2010, 25(9): 2103-2110. Liu Zhigang, Fang Xiangjun, Liu Siyong, et al. Design and analysis of HP-turbine for variable cycle engine[J]. Journal of Aerospace Power, 2010, 25(9): 2103-2110. (in Chinese
Liu Zhigang, Fang Xiangjun, Liu Siyong, et al. Design and analysis of HP-turbine for variable cycle engine[J]. Journal of Aerospace Power, 2010, 25(9): 2103-2110. (in Chinese)
|
| [25] |
吴中野, 方祥军. 变几何低压涡轮气动性能研究[J]. 推进技术, 2018, 39(2): 269-276. Wu Zhongye, Fang Xiangjun. Research on variable geometry low pressure turbine aerodynamic performance[J]. Journal of Propulsion Technology, 2018, 39(2): 269-276. (in Chinese doi: 10.13675/j.cnki.tjjs.2018.02.004
Wu Zhongye, Fang Xiangjun. Research on variable geometry low pressure turbine aerodynamic performance[J]. Journal of Propulsion Technology, 2018, 39(2): 269-276. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.02.004
|
| [26] |
吴中野, 方祥军, 刘思永, 等. 1+1/2级超跨声对转涡轮气动性能试验及分析[J]. 航空学报, 2018, 39(9): 67-76. Wu Zhongye, Fang Xiangjun, Liu Siyong, et al. Test and analysis on aerodynamic performance of 1+1/2 supertransonic counter-rotating turbine[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(9): 67-76. (in Chinese doi: 10.7527/S1000-6893.2018.22155
Wu Zhongye, Fang Xiangjun, Liu Siyong, et al. Test and analysis on aerodynamic performance of 1+1/2 supertransonic counter-rotating turbine[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(9): 67-76. (in Chinese) doi: 10.7527/S1000-6893.2018.22155
|
DownLoad:
