Numerical simulation study on labyrinth seal in compressor with FLADE structure of adaptive cycle engines
-
摘要:
自适应循环发动机叶尖风扇（fan on blade, FLADE）涵道转子叶片与内涵道转子叶片共用旋转轮盘，转静部件间隙导致了从FLADE涵道至内涵道的泄漏流，为发动机内外涵间封严措施带来了新的挑战。当FLADE结构被用于压气机时，内外涵间的封严泄漏流对质量流量变化影响更为突出，对气动性能影响更加显著。以某自适应循环发动机采用FLADE结构的压气机为研究对象，建立了包含内外涵间封严篦齿结构的1.5级压气机计算模型，采用数值模拟方法分析内外涵间篦齿泄漏流动对压气机气动性能的影响。研究结果表明：内外涵间封严篦齿泄漏使得内涵总压比升高0.519%，而FLADE涵道总压比降低0.264%；封严篦齿结构在封严腔内形成局部高压区域，对泄漏流起到抑制作用；封严篦齿泄漏流主要影响内涵静子前缘，其对主流的掺混作用主要作用在80%～99%叶高区，导致静子叶尖形成低能区，从而使内涵静子总压恢复系数降低，转子总压比升高进而影响1.5级压气机整体气动性能。
-
关键词:
- 自适应循环发动机 /
- 叶尖风扇(FLADE) /
- 封严篦齿 /
- 叶尖间隙 /
- 泄漏流
Abstract:In the adaptive cycle engine, the fan on blade (FLADE) bypass rotor blades and the inner bypass rotor blades share a common rotating disk. The clearance between the rotating and stationary components results in leakage flow from the FLADE bypass duct to the core duct, posing new challenges for sealing between the engine’s bypass and core flows. When the FLADE configuration is applied to a compressor, the sealing leakage flow between the bypass and core ducts has a more pronounced impact on mass flow variation and aerodynamic performance. Taking the compressor of a certain adaptive cycle engine with the FLADE structure as the research object, a 1.5-stage compressor computational model considering the labyrinth seal structure between the core and bypass ducts was established. Numerical simulation was employed to investigate the effect of leakage flow through the labyrinth seal on the aerodynamic performance of the compressor. The results indicated that the leakage through the labyrinth seal between the core and bypass streams increased the total pressure ratio 0.519% in the core duct while reducing it 0.264% in the FLADE bypass duct. Additionally, the labyrinth seal structure created a local high-pressure region within the seal cavity, effectively suppressing leakage flow. The leakage flow primarily affected the blade tip region of the inner stator blades, with significant mixing effects occurring predominantly at 80% to 90% blade span. This interaction resulted in a low-energy region at the stator leading edge, causing a decrease in stator total pressure recovery coefficient while increasing the rotor total pressure ratio, thus impacting the overall aerodynamic performance of the 1.5-stage compressor.
-
Key words:
- adaptive cycle engine /
- fan on blade (FLADE) /
- labyrinth seal /
- tip clearance /
- leakage flow
-
图 4 1.5级压气机内涵道网格示意图
Figure 4. Schematic diagram of 1.5-stage compressor grids in the inner duct
图 5 1.5级压气机外涵道网格示意图
Figure 5. Schematic diagram of 1.5-stage compressor grids in the outer duct
图 6 1.5级压气机封严腔网格示意图
Figure 6. Schematic diagram of grids in the sealing cavity of1.5-stage compressor
图 10 封严腔静压云图及流线分布
Figure 10. Contour plot of static pressure and streamline distribution in the sealing cavity
图 11 封严腔三维流线分布
Figure 11. Three-dimensional streamline distribution in the sealing cavity
图 12 封严腔壁面在多运行工况下的静压云图
Figure 12. Contour plot of static pressure on sealing cavity walls under multiple operating conditions
图 13 有无封严篦齿结构的数值模型示意图
Figure 13. Schematic diagram of the numerical model with and without labyrinth seal
图 16 1.5级压气机总体气动性能对比
Figure 16. Comparison of overall aerodynamic performance of the 1.5-stage compressor
图 17 1.5级压气机各部分组件气动性能对比
Figure 17. Comparison of aerodynamic performance across each component of the 1.5-stage compressor
图 19 内涵总压比径向分布
Figure 19. Radial distribution of total pressure ratio at the inner duct
图 20 外涵总压比径向分布
Figure 20. Radial distribution of total pressure ratio at the outer duct
图 21 内涵静子入口气流角径向分布
Figure 21. Flow angel radial distribution at stator inlet of inner duct
图 22 外涵静子入口气流角径向分布
Figure 22. Flow angel radial distribution at stator inlet of outer duct
图 23 内涵静子叶尖流域流线分布
Figure 23. Streamline distribution at stator blade tip region in the inner duct
图 24 内涵静子前缘面静压分布云图
Figure 24. Contour plot of static pressure on the leading edge surface of the stator in inner duct
图 25 外涵静子前缘面静压分布云图
Figure 25. Contour plot of static pressure on the leading edge surface of the stator in outer duct
图 26 内涵99%叶高静压分布云图
Figure 26. Contour plot of static pressure at 99% span in inner duct
图 27 内涵50%叶高静压分布云图
Figure 27. Contour plot of static pressure at 50% span in inner duct
表 2 有无封严篦齿结构气动性能对比
Table 2. Comparison of aerodynamic performance with and without labyrinth seal structure
气动性能 不考虑封严篦齿 考虑封严篦齿 内涵流量/（kg/s） 30.540 30.690 外涵流量/（kg/s） 8.601 8.475 入口流量/（kg/s） 39.140 39.170 内涵总压比 1.350 1.357 外涵总压比 1.515 1.511 内涵转子总压比 1.442 1.453 内涵静子总压恢复系数 0.9737 0.9688 外涵转子总压比 1.570 1.567 外涵静子总压恢复系数 0.9827 0.9826 
下载: 导出CSV
-
[1] 徐臻豪. 变循环发动机: 第六代战斗机动力[J]. 兵器知识, 2020(9): 28-31. doi: 10.19437/j.cnki.11-1470/tj.2020.09.010 [2] Grant R. Adaptive engines[J]. Air Force Magazine, 2012, 95(9): 62-65. [3] 陈敏, 张纪元, 唐海龙, 等. 自适应循环发动机总体设计技术探讨[J]. 航空动力学报, 2022, 37(10): 2046-2058. Chen Min, Zhang Jiyuan, Tang Hailong, et al. Discussion on overall performance design technology of adaptive cycle engine[J]. Journal of Aerospace Power, 2022, 37(10): 2046-2058. (in Chinese doi: 10.13224/j.cnki.jasp.20220294Chen Min, Zhang Jiyuan, Tang Hailong, et al. Discussion on overall performance design technology of adaptive cycle engine[J]. Journal of Aerospace Power, 2022, 37(10): 2046-2058. (in Chinese) doi: 10.13224/j.cnki.jasp.20220294 [4] 周拜豪, 张少平, 黄萍, 等. 压气机气动设计发展与思考[J]. 燃气涡轮试验与研究, 2025, 38(2): 45-57. Zhou Baihao, Zhang Shaoping, Huang Ping, et al. Evolution and perspectives in compressor aerodynamic design[J]. Gas Turbine Experiment and Research, 2025, 38(2): 45-57. (in Chinese doi: 10.3724/j.GTER.20250032Zhou Baihao, Zhang Shaoping, Huang Ping, et al. Evolution and perspectives in compressor aerodynamic design[J]. Gas Turbine Experiment and Research, 2025, 38(2): 45-57. (in Chinese) doi: 10.3724/j.GTER.20250032 [5] 方昌德. 变循环发动机[J]. 燃气涡轮试验与研究, 2004, 17(3): 1-5. Fang Changde. Variable cycle engines[J]. Gas Turbine Experiment and Research, 2004, 17(3): 1-5. (in ChineseFang Changde. Variable cycle engines[J]. Gas Turbine Experiment and Research, 2004, 17(3): 1-5. (in Chinese) [6] 王靖凯, 闫雨嘉, 崔金辉. 带Flade的ACE建模与稳态性能仿真分析[J]. 计算机仿真, 2023, 40(3): 36-40. Wang Jingkai, Yan Yujia, Cui Jinhui. Modeling and steady performance simulation of adaptive cycle engine with the flade[J]. Computer Simulation, 2023, 40(3): 36-40. (in Chinese doi: 10.3969/j.issn.1006-9348.2023.03.008Wang Jingkai, Yan Yujia, Cui Jinhui. Modeling and steady performance simulation of adaptive cycle engine with the flade[J]. Computer Simulation, 2023, 40(3): 36-40. (in Chinese) doi: 10.3969/j.issn.1006-9348.2023.03.008 [7] 陈雷, 孟德君, 阎深, 等. 涵道可调发动机模式选择阀被动调节特性数值模拟[J]. 燃气涡轮试验与研究, 2023, 36(1): 10-15, 48. Chen Lei, Meng Dejun, Yan Shen, et al. Numerical simulation on passive mode selector value characteristic of duct adjustable engine[J]. Gas Turbine Experiment and Research, 2023, 36(1): 10-15, 48. (in Chinese doi: 10.3969/j.issn.1672-2620.2023.01.002Chen Lei, Meng Dejun, Yan Shen, et al. Numerical simulation on passive mode selector value characteristic of duct adjustable engine[J]. Gas Turbine Experiment and Research, 2023, 36(1): 10-15, 48. (in Chinese) doi: 10.3969/j.issn.1672-2620.2023.01.002 [8] 滕进华, 王英锋. 带FLADE的ACE典型工况不同工作模式性能仿真分析[J]. 南京航空航天大学学报, 2024, 56(4): 630-638. Teng Jinhua, Wang Yingfeng. Simulation analysis of performance of ACE with FLADE under typical working conditions and different working modes[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2024, 56(4): 630-638. (in Chinese doi: 10.16356/j.1005-2615.2024.04.005Teng Jinhua, Wang Yingfeng. Simulation analysis of performance of ACE with FLADE under typical working conditions and different working modes[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2024, 56(4): 630-638. (in Chinese) doi: 10.16356/j.1005-2615.2024.04.005 [9] Roland B. An era of Dover-built TF39 engines throttles down[EB/OL]. (2016-04-12)[2025-08-13]. https://www.amc.af.mil/News/Article-Display/Article/785826/an-era-of-dover-built-tf39-engines-throttles-down/. [10] Zeng Yueliu, Wei Yuan. Analysis of aerodynamic design characteristics of flade fan[J]. Procedia Engineering, 2015, 99: 723-733. doi: 10.1016/j.proeng.2014.12.594 [11] Wellborn S R. Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance[D]. Ames: Iowa State University, 1996. [12] 梁津华, 徐连强, 邹咪, 等. 基于伴随法和网格变形技术的篦齿优化[J]. 燃气涡轮试验与研究, 2023, 36(4): 49-54. Liang Jinhua, Xu Lianqiang, Zou Mi, et al. Labyrinth seals optimization based on adjoint method and mesh deform[J]. Gas Turbine Experiment and Research, 2023, 36(4): 49-54. (in Chinese doi: 10.3969/j.issn.1672-2620.2023.04.008Liang Jinhua, Xu Lianqiang, Zou Mi, et al. Labyrinth seals optimization based on adjoint method and mesh deform[J]. Gas Turbine Experiment and Research, 2023, 36(4): 49-54. (in Chinese) doi: 10.3969/j.issn.1672-2620.2023.04.008 [13] 刘高文, 陈凯, 刚铁, 等. 压比和雷诺数对压气机级间篦齿封严流动特性的影响[J]. 航空动力学报, 2015, 30(7): 1554-1560. Liu Gaowen, Chen Kai, Gang Tie, et al. Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well[J]. Journal of Aerospace Power, 2015, 30(7): 1554-1560. (in Chinese doi: 10.13224/j.cnki.jasp.2015.07.003Liu Gaowen, Chen Kai, Gang Tie, et al. Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well[J]. Journal of Aerospace Power, 2015, 30(7): 1554-1560. (in Chinese) doi: 10.13224/j.cnki.jasp.2015.07.003 [14] 孔晓治, 刘高文, 雷昭, 等. 齿型对压气机级间封严特性影响的实验研究[J]. 推进技术, 2018, 39(9): 2085-2093. Kong Xiaozhi, Liu Gaowen, Lei Zhao, et al. Experimental investigation for effects of tooth shapes on compressor inter-stage seal[J]. Journal of Propulsion Technology, 2018, 39(9): 2085-2093. (in Chinese doi: 10.13675/j.cnki.tjjs.2018.09.020Kong Xiaozhi, Liu Gaowen, Lei Zhao, et al. Experimental investigation for effects of tooth shapes on compressor inter-stage seal[J]. Journal of Propulsion Technology, 2018, 39(9): 2085-2093. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.09.020 [15] 王广, 楚武利. 级间进出口几何角度对压气机气动性能和封严效果的影响[J]. 推进技术, 2020, 41(5): 1063-1071. Wang Guang, Chu Wuli. Influence of geometric angle of inter-stage inlet and outlet on aerodynamic performance and sealing of compressor[J]. Journal of Propulsion Technology, 2020, 41(5): 1063-1071. (in Chinese doi: 10.13675/j.cnki.tjjs.190254Wang Guang, Chu Wuli. Influence of geometric angle of inter-stage inlet and outlet on aerodynamic performance and sealing of compressor[J]. Journal of Propulsion Technology, 2020, 41(5): 1063-1071. (in Chinese) doi: 10.13675/j.cnki.tjjs.190254 [16] 方世川, 向宏辉, 梁崇志, 等. 跨声速压气机泄漏流预测数值模拟[J]. 燃气涡轮试验与研究, 2023, 36(6): 13-20. Fang Shichuan, Xiang Honghui, Liang Chongzhi, et al. Numerical simulation of transonic compressor leakage flow prediction[J]. Gas Turbine Experiment and Research, 2023, 36(6): 13-20. (in Chinese doi: 10.3969/j.issn.1672-2620.2023.06.003Fang Shichuan, Xiang Honghui, Liang Chongzhi, et al. Numerical simulation of transonic compressor leakage flow prediction[J]. Gas Turbine Experiment and Research, 2023, 36(6): 13-20. (in Chinese) doi: 10.3969/j.issn.1672-2620.2023.06.003 [17] 吴森林, 赵正, 王文琪, 等. 封严腔泄漏流对压气机性能影响的试验研究[J]. 航空动力学报, 2025, 40(6): 20230036. Wu Senlin, Zhao Zheng, Wang Wenqi, et al. Experimental investigation of the influence of seal cavity leakage on a compressor performance[J]. Journal of Aerospace Power, 2025, 40(6): 20230036. (in Chinese doi: 10.13224/j.cnki.jasp.20230036Wu Senlin, Zhao Zheng, Wang Wenqi, et al. Experimental investigation of the influence of seal cavity leakage on a compressor performance[J]. Journal of Aerospace Power, 2025, 40(6): 20230036. (in Chinese) doi: 10.13224/j.cnki.jasp.20230036 [18] 徐文峰, 邹世龙, 任国哲, 等. 篦齿封严结构对压气机叶栅性能影响研究[J]. 航空动力学报, 2025, 40(12): 20240075. Xu Wenfeng, Zou Shilong, Ren Guozhe, et al. Study on the influences of the labyrinth seal structure on the compressor cascade performance[J]. Journal of Aerospace Power, 2025, 40(12): 20240075. (in Chinese doi: 10.13224/j.cnki.jasp.20240075Xu Wenfeng, Zou Shilong, Ren Guozhe, et al. Study on the influences of the labyrinth seal structure on the compressor cascade performance[J]. Journal of Aerospace Power, 2025, 40(12): 20240075. (in Chinese) doi: 10.13224/j.cnki.jasp.20240075 [19] 王子楠, 耿少娟, 张宏武. 来流边界层对压气机平面叶栅角区流动的影响[J]. 推进技术, 2017, 38(1): 54-60. Wang Zinan, Geng Shaojuan, Zhang Hongwu. Effects of inlet boundary layer on corner flow in a linear compressor cascade[J]. Journal of Propulsion Technology, 2017, 38(1): 54-60. (in Chinese doi: 10.13675/j.cnki.tjjs.2017.01.008Wang Zinan, Geng Shaojuan, Zhang Hongwu. Effects of inlet boundary layer on corner flow in a linear compressor cascade[J]. Journal of Propulsion Technology, 2017, 38(1): 54-60. (in Chinese) doi: 10.13675/j.cnki.tjjs.2017.01.008 [20] 杨帆, 周莉, 王占学. 轮缘封严气流与主流干涉的损失机理研究[J]. 推进技术, 2020, 41(2): 285-293. Yang Fan, Zhou Li, Wang Zhanxue. Investigation on interaction loss mechanism between rim seal flow and mainstream[J]. Journal of Propulsion Technology, 2020, 41(2): 285-293. (in Chinese doi: 10.13675/j.cnki.tjjs.180812Yang Fan, Zhou Li, Wang Zhanxue. Investigation on interaction loss mechanism between rim seal flow and mainstream[J]. Journal of Propulsion Technology, 2020, 41(2): 285-293. (in Chinese) doi: 10.13675/j.cnki.tjjs.180812 [21] 曹传军, 敖天翔, 庄皓琬, 等. 封严篦齿对轴流压气机涡系结构与流动损失的影响[J]. 热能动力工程, 2023, 38(6): 20-30. Cao Chuanjun, Ao Tianxiang, Zhuang Haowan, et al. Effect of labyrinth seal on vortex structure and flow loss of axial compressor[J]. Journal of Engineering for Thermal Energy and Power, 2023, 38(6): 20-30. (in Chinese doi: 10.16146/j.cnki.rndlgc.2023.06.003Cao Chuanjun, Ao Tianxiang, Zhuang Haowan, et al. Effect of labyrinth seal on vortex structure and flow loss of axial compressor[J]. Journal of Engineering for Thermal Energy and Power, 2023, 38(6): 20-30. (in Chinese) doi: 10.16146/j.cnki.rndlgc.2023.06.003 [22] Zhu Mingmin, Teng Jinfang, Qiang Xiaoqing, et al. Impact of hub gap leakage on stator endwall flow in an axial compressor stage with casing treatment[J]. Aerospace Science and Technology, 2019, 94: 105399. doi: 10.1016/j.ast.2019.105399 [23] Kong Xiaozhi, Huang Tianshuo, Liu Yuxin, et al. Influences of the cavity leakage flow on shrouded stator performance at different inlet boundary layer shapes[J]. Physics of Fluids, 2023, 35(4): 045101. doi: 10.1063/5.0146925 [24] 李昶威, 孙丹, 赵欢, 等. 静态篦齿封严温变效应产生机理数值研究[J]. 航空动力学报, 2024, 39(2): 20220219. Li Changwei, Sun Dan, Zhao Huan, et al. Numerical study on the generation mechanism of temperature variation effect of static labyrinth seals[J]. Journal of Aerospace Power, 2024, 39(2): 20220219. (in Chinese doi: 10.13224/j.cnki.jasp.20220219Li Changwei, Sun Dan, Zhao Huan, et al. Numerical study on the generation mechanism of temperature variation effect of static labyrinth seals[J]. Journal of Aerospace Power, 2024, 39(2): 20220219. (in Chinese) doi: 10.13224/j.cnki.jasp.20220219 [25] 宋权斌, 张方圆, 王方才子, 等. 级间封严篦齿对压气机气动性能的影响机制研究[J]. 润滑与密封, 2025, 50(5): 70-77. Song Quanbin, Zhang Fangyuan, Wang Fangcaizi, et al. Research on the influence mechanism of inter-stage labyrinth seal on compressor aerodynamic performance[J]. Lubrication Engineering, 2025, 50(5): 70-77. (in Chinese doi: 10.3969/j.issn.0254-0150.2025.05.009Song Quanbin, Zhang Fangyuan, Wang Fangcaizi, et al. Research on the influence mechanism of inter-stage labyrinth seal on compressor aerodynamic performance[J]. Lubrication Engineering, 2025, 50(5): 70-77. (in Chinese) doi: 10.3969/j.issn.0254-0150.2025.05.009 -
点击查看大图
计量
- 文章访问数: 56
- HTML浏览量: 42
- PDF量: 2
- 被引次数: 0