Turbine-based combined-cycle inlet mode transition opertation conditions and transition schemes
-
摘要:
为实现组合动力推进系统（TBCC）平稳的模态转换，采用风洞试验和数值仿真方法开展了TBCC进气道模态转换过程分流模式及分流策略研究。提出了将组合动力进气道模态转换过程工作状态分为超声分流、超/亚声分流以及亚声分流3种模式，并给出不同分流模式的判断依据。根据不同分离模式涡轮和冲压通道所能承受的极限背压，构建了包含3种分流模式的进气道模态转换工作区。基于模态转换工作区，给出了两种模态转换分流策略。结果表明：模态转换过程，涡轮通道超声分流模式极限背压从32倍减小至13倍，冲压通道极限背压从16倍增大到32倍；超声分流模式两个通道的流量和涡轮/冲压通道的入口面积成正比，一旦进入超/亚声分流模式，两个通道之间将发生气动耦合现象，在模态转换40%～60%时，涡轮通道流量系数比超声分流降低12%，冲压通道流量系数增大7%。
Abstract:To achieve smooth mode transition of turbine-based combined-cycle (TBCC) propulsion system, the transition operation modes and transition schemes of TBCC inlet were investigated through wind tunnel test and numerical simulations. Three transition operation modes of TBCC inlet, including supersonic operation mode, supersonic/subsonic operation mode and subsonic mode, and the criteria for different operation modes were put forward. Then the operation zone, which included the three transition operation modes of inlet mode transition, was established according to the maximum backpressure of turbojet and ramjet flowpath at different modes. Two mode transition schemes were presented based on the operation zone. The results indicated that during TBCC inlet mode transition, the maximum backpressure of the turbojet flowpath of supersonic operation mode decreased from 32 times to 13 times, while it increased from 16 times to 32 times for the ramjet flowpath. The mass flow into two flowpath was changed linearly to the entrance area of turbojet/ramjet flowpaths during supersonic mode transition. Once the inlet operated in supersonic/subsonic mode during mode transition, aerodynamic coupling between two flowpath occurred. During mode transition from 40% to 60%, mass flow ratio of the turbojet flowpath decreased by 12% compared with supersonic operation mode and increased by 7% for the ramjet flowpath.
-
图 5 TBCC进气道典型过渡模态不同节流条件风洞试验与数值仿真沿程静压对比曲线
Figure 5. Comparison of static pressure between tests and numerical simulation along the flowpaths of typical transition mode of TBCC inlet at different throttle ratios
图 6 进气道不同分流模式风洞试验与数值仿真纹影对比
Figure 6. Comparison of schlieren between tests and numerical simulation at different inlet opertation conditions
图 7 TBCC进气道不同分流模式示意图
Figure 7. Scheme of TBCC inlet under different operation conditions
图 8 进气道超声分流模式不同背压马赫数等值图
Figure 8. Mach number contour along the flowpath of supersonic opertation conditions at different backpressures
图 9 进气道超声分流模式不同背压出口性能变化曲线
Figure 9. Inlet performance of supersonic opertation conditions at different backpressures
图 10 TBCC进气道超声分流及超/亚声分流模式的纹影及沿程静压
Figure 10. TBCC inlet schlieren and static pressure along the flowpath at supersonic and supersonic/subsonic opertation conditions
图 11 进气道超/亚声分流模式对称面马赫等值图
Figure 11. Mach number contour on symmetry plane at supersonic/subsonic opertation conditions
图 12 进气道超/亚声分流模式马赫数云图及流量系数变化曲线
Figure 12. Mach number contour and mass flow ratio of inlet supersonic/subsonic opertation conditions
图 13 进气道亚声分流模式对称面马赫等值图
Figure 13. Mach number contour on symmetry plane at subsonic opertation condition
图 14 进气道模态转换过程分流模式及涡轮/冲压通道背压
Figure 14. Backpressure of turbojet/ramjet flowpath during inlet mode transition at different schemes
图 15 进气道模态转换背压控制规律
Figure 15. Backpressure control scheme during inlet mode transition
图 16 TBCC进气道模态转换过程纹影及沿程静压
Figure 16. TBCC inlet schlieren and static pressure along the flowpath during mode transition
图 17 不同模态转换分流策略涡轮/冲压通道流量系数
Figure 17. Mass flow ratio of turbojet/ramjet flowpath at different mode transition schemes
表 1 进气道超/亚声分流模式下相关截面马赫数
Table 1. Mach number of critical section at supersonic/subsonic opertation conditions
高背压
来源出口
背压马赫数 喉道 涡轮进口 冲压进口 冲压通道 30.5 1.257 0.791 1.218 涡轮通道 27 1.003 0.756 1.029 
下载: 导出CSV
表 2 进气道亚声分流模式下相关截面马赫数
Table 2. Mach number of critical section of subsonic opertation conditions
涡轮
背压冲压
背压马赫数 喉道 涡轮进口 冲压进口 27 30.5 1.009 0.756 1.029 27.5 31 0.960 0.766 0.954 28 31.5 0.813 0.755 0.831
下载: 导出CSV
-
[1] 尹泽勇, 尤延铖, 朱呈祥, 等. 面向高超声速民机的多通道双涡轮引射冲压组合动力[J]. 航空学报, 2023, 44(2): 627181. YIN Zeyong, YOU Yancheng, ZHU Chengxiang, et al. Multi-ducted twin-turbines ejector-ramjet/scramjet combined cycle engine for hypersonic civil vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(2): 627181. (in ChineseYIN Zeyong, YOU Yancheng, ZHU Chengxiang, et al. Multi-ducted twin-turbines ejector-ramjet/scramjet combined cycle engine for hypersonic civil vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(2): 627181. (in Chinese) [2] 左林玄, 张辰琳, 王霄, 等. 高超声速飞机动力需求探讨[J]. 航空学报, 2021, 42(8): 525798. ZUO Linxuan, ZHANG Chenlin, WANG Xiao, et al. Requirement of hypersonic aircraft power[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(8): 525798. (in ChineseZUO Linxuan, ZHANG Chenlin, WANG Xiao, et al. Requirement of hypersonic aircraft power[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(8): 525798. (in Chinese) [3] LYU Ganlin, GAO Zhenxun, QIAN Zhansen, et al. Studies on unsteady mode transition of a turbine based combined cycle (TBCC) inlet with multiple movable panels[J]. Aerospace Science and Technology, 2021, 111: 106546. doi: 10.1016/j.ast.2021.106546 [4] 赵家辉, 杨顺华, 游进, 等. 双通道内并联式进气道模态转换过程流动特性分析[J]. 航空动力学报, 2023, 38(1): 173-183. ZHAO Jiahui, YANG Shunhua, YOU Jin, et al. Analysis of flow characteristics during modal conversion of dual-channel internal parallel inlet[J]. Journal of Aerospace Power, 2023, 38(1): 173-183. (in ChineseZHAO Jiahui, YANG Shunhua, YOU Jin, et al. Analysis of flow characteristics during modal conversion of dual-channel internal parallel inlet[J]. Journal of Aerospace Power, 2023, 38(1): 173-183. (in Chinese) [5] ZHENG Jialin, CHANG Juntao, MA Jicheng, et al. Analysis of aerodynamic/propulsive couplings during mode transition of over-under turbine-based-combined-cycle engines[J]. Aerospace Science and Technology, 2020, 99: 105773. doi: 10.1016/j.ast.2020.105773 [6] 刘君, 袁化成, 郭荣伟. 内并联式TBCC进气道模态转换过程流动特性分析[J]. 宇航学报, 2016, 37(4): 461-469. LIU Jun, YUAN Huacheng, GUO Rongwei. Analysis of over/under TBCC inlet mode transition flow characteristic[J]. Journal of Astronautics, 2016, 37(4): 461-469. (in ChineseLIU Jun, YUAN Huacheng, GUO Rongwei. Analysis of over/under TBCC inlet mode transition flow characteristic[J]. Journal of Astronautics, 2016, 37(4): 461-469. (in Chinese) [7] SANDERS B, WEIR L. Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system[R]. NASA/CR-2008-215214, 2008. [8] SAUNDERS J D, SLATER J W, DIPPOLD V, et al. Inlet mode transition screening test for a turbine-based combined-cycle propulsion system[R]. Cleveland, US: 55th JANNAF Propulsion Meeting, 2008. [9] SAUNDERS J, STUEBER T, THOMAS S, et al. Testing of the NASA hypersonics project combined cycle engine large scale inlet mode transition experiment (CCE LlMX) [R]. NASA/TM-2012-217217, 2012. [10] CHEN Min, TANG Hailong, ZHANG Kun, et al. Turbine-based combined cycle propulsion system integration concept design[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2013, 227(7): 1068-1089. doi: 10.1177/0954410012449246 [11] 张明阳, 周莉, 王占学, 等. 外并联式TBCC发动机模态转换性能模拟与分析[J]. 推进技术, 2018, 39(11): 2429-2437. ZHANG Mingyang, ZHOU Li, WANG Zhanxue, et al. Simulation and analysis of mode transition performance for an over-under TBCC engine[J]. Journal of Propulsion Technology, 2018, 39(11): 2429-2437. (in ChineseZHANG Mingyang, ZHOU Li, WANG Zhanxue, et al. Simulation and analysis of mode transition performance for an over-under TBCC engine[J]. Journal of Propulsion Technology, 2018, 39(11): 2429-2437. (in Chinese) [12] ZHENG Jialin, CHANG Juntao, MA Jicheng, et al. Modeling and analysis of windmilling operation during mode transition of a turbine-based-combined cycle engine[J]. Aerospace Science and Technology, 2021, 109: 106423. doi: 10.1016/j.ast.2020.106423 [13] XIANG Xianhong, LIU Yuan, QIAN Zhansen. Aerodynamic design and numerical simulation of over-under turbine-based combined-cycle (TBCC) inlet mode transition[J]. Procedia Engineering, 2015, 99: 129-136. doi: 10.1016/j.proeng.2014.12.516 [14] LIU Yuan, WANG Lu, QIAN Zhansen. Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet[J]. Aerospace Science and Technology, 2018, 79: 647-657. doi: 10.1016/j.ast.2018.06.014 [15] 刘愿, 钱战森, 向先宏. 外并联式TBCC进气道模态转换风洞试验及模型典型影响因素分析[J]. 实验流体力学, 2019, 33(5): 19-28. LIU Yuan, QIAN Zhansen, XIANG Xianhong. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 19-28. (in ChineseLIU Yuan, QIAN Zhansen, XIANG Xianhong. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 19-28. (in Chinese) [16] YANG Hui, MA Jun, MAN Yanjin, et al. Numerical simulation of variable-geometry inlet for TRRE combined cycle engine[R]. AIAA 2017-2437, 2017. [17] WEI Baoxi, LING Wenhui, LUO Feiteng, et al. Propulsion performance research and status of TRRE engine experiment[R]. AIAA 2017-2351, 2017. [18] 胡占仓, 蔡泽君, 王天洋, 等. 转级模式对三维内转组合进气道模态转换性能的影响分析[J]. 推进技术, 2020, 41(12): 2670-2680. HU Zhancang, CAI Zejun, WANG Tianyang, et al. Analysis of effects of mode transition type on performance of mode transition for 3D inward-turning combined inlet[J]. Journal of Propulsion Technology, 2020, 41(12): 2670-2680. (in ChineseHU Zhancang, CAI Zejun, WANG Tianyang, et al. Analysis of effects of mode transition type on performance of mode transition for 3D inward-turning combined inlet[J]. Journal of Propulsion Technology, 2020, 41(12): 2670-2680. (in Chinese) [19] 张华军, 郭荣伟, 谢旅荣. 内并联型TBCC进气道方案设计及验证[J]. 航空动力学报, 2012, 27(11): 2475-2483. ZHANG Huajun, GUO Rongwei, XIE Lyurong. Design and validation of scheme of over/under TBCC inlet[J]. Journal of Aerospace Power, 2012, 27(11): 2475-2483. (in ChineseZHANG Huajun, GUO Rongwei, XIE Lyurong. Design and validation of scheme of over/under TBCC inlet[J]. Journal of Aerospace Power, 2012, 27(11): 2475-2483. (in Chinese) [20] YUAN Huacheng, LIU Jun, ZHANG Jinsheng, et al. The design and validation of over/under turbine-based combined cycle inlet[J]. Aerospace Science and Technology, 2020, 105: 105960. doi: 10.1016/j.ast.2020.105960 [21] LIU Jun, YUAN Huacheng, GUO Rongwei. Unsteady flow characteristic analysis of turbine based combined cycle (TBCC) inlet mode transition[J]. Propulsion and Power Research, 2015, 4(3): 141-149. doi: 10.1016/j.jppr.2015.07.006 [22] LIU Jun, YUAN Huacheng, YAO Meng, et al. Numerical simulation of terminal shock oscillation in over/under turbine-based combined-cycle inlet[J]. International Journal of Turbo & Jet-Engines, 2021, 38(1): 73-83. [23] LIU Jun, YUAN Huacheng, CHEN Wenfang, et al. Investigation of translation scheme turbine-based combined-cycle inlet mode transition[J]. Aerospace Science and Technology, 2021, 116: 106894. doi: 10.1016/j.ast.2021.106894 [24] 王超, 张悦, 谭慧俊, 等. 内并联型进气道模态转换过程中流道间干扰特性研究[J]. 推进技术, 2022, 43(7): 200764. WANG Chao, ZHANG Yue, TAN Huijun, et al. Study on interference characteristics between channels during modal conversion of internal parallel inlet[J]. Journal of Propulsion Technology, 2022, 43(7): 200764. (in ChineseWANG Chao, ZHANG Yue, TAN Huijun, et al. Study on interference characteristics between channels during modal conversion of internal parallel inlet[J]. Journal of Propulsion Technology, 2022, 43(7): 200764. (in Chinese) -
点击查看大图
计量
- 文章访问数: 369
- HTML浏览量: 251
- PDF量: 39
- 被引次数: 0