Unsteady flow characteristics in hyper-burner with trapped vortex cavity during mode transition
-
摘要:
为获得凹腔驻涡超级燃烧室燃烧模式转换过程流动特性，设计了矩形模型试验件，采用三维动网格仿真方法进行基准方案、先慢后快方案和先快后慢方案（记为Case A、Case B、Case C）这3个不同后涵道引射门调节方案下流动特性研究。燃烧室入口总质量流量为1.5 kg/s，涡轮和冲压通道进气温度分别为550 K和300 K，后涵道引射门运动时间为2 s。计算获得了模态转换过程超级燃烧室的流场结构、质量流量分配特性以及掺混特性，结果表明：3个方案流场结构及变化规律基本一致；0～0.16 s，模态转换影响凹腔内涡形态和涡心位置，但凹腔和径向稳定器仍能建立完整稳定的涡系；平板引射门掺混促进作用较弱，热混合效率小于0.3；0.25 s，3个方案中Case B冷却通道质量流量占比最大，总压损失最小；总压损失主要发生在0.36>
x /D >0.63（x 为沿程位置，D 为燃烧室总长）区域。Abstract:To capture the flow characteristics during transitions in a trapped vortex cavity hyper-burner, a rectangular model was designed. A three-dimensional dynamic mesh simulation method was employed to investigate the flow characteristics of the hyper-burner under three different regulation schemes of rear variable area bypass injector (RVABI): baseline scheme (Case A), slow-then-fast scheme (Case B), and fast-then-slow scheme (Case C). The operating conditions included a mass flow rate of 1.5 kg/s, turbine inlet temperature of 550 K, ramjet inlet temperature of 300 K, and a RVABI movement duration of 2 s. The flow characteristics, mass flow distribution characteristics, and the mixing characteristics were obtained. The results indicated that: the flow characteristics of the three schemes were basically consistent. 0—0.16 s, although the adjustment of the RVABI affected the shape and core position of vortex within cavity, a complete and stable vortex structure can still be established. The flat RVABI had a relatively weak mixing, which was less than 0.3. Among the three schemes for 0.25 s, Case B had the largest mass flow ratio of cooling channel and the smallest total pressure loss. The total pressure loss mainly occurred within region 0.36>
x /D >0.63 (wherex was the position along flow direction,D was the length of hyper-burner).-
Key words:
- hyper-burner /
- trapped vortex cavity /
- mode transition /
- flow characteristics /
- dynamic mesh
-
图 7 冷却通道流向截面平均总温
Figure 7. Average total temperature of flow-direction cross-section in cooling channel
图 13 Case A凹腔径向截面速度云图
Figure 13. Velocity contour of Case A radial cross-section of cavity
图 14 Case A稳定器截面速度云图及流线图
Figure 14. Velocity contour and streamline of Case A stabilizer cross-section
图 16 Case A凹腔径向截面速度矢量和流线图
Figure 16. Vector and streamline of Case A cavity radial section
图 17 Case A凹腔轴向截面速度矢量和流线
Figure 17. Vector and streamline of Case A cavity flow section
图 18 冷却通道流量占总入口流量之比
Figure 18. Mass flow ratio of cooling channel with total inlet flow
图 20 t=0.25 s时的热混合效率沿程分布
Figure 20. Distribution of thermal mixing efficiency along flow direction for t=0.25 s
图 22 引射门出口截面涡轮与冲压来流速度差
Figure 22. Turbine and ramjet incoming velocity difference at ejector outlet
图 24 t=0.25 s时沿程总压恢复系数
Figure 24. Total pressure recovery coefficient along flow direction for t=0.25 s
图 25 Case A在0、0.25、2.0 s时刻沿程总压恢复系数
Figure 25. Total pressure recovery coefficient along flow direction for Case A at 0, 0.25, 2.0 s
表 1 涡轮和冲压模态稳态入口气流参数
Table 1. Inlet parameters in steady state of turbine and ramjet mode
参数 数值或说明 涡轮入口 冲压入口 总压 常压 常压 总温/K 550 300 流量/（kg/s） 1.5 1.5 马赫数 0.41 0.25 
下载: 导出CSV
表 2 内涵和引气入口稳态气流参数
Table 2. Inlet parameters in steady state of internal bypass and entraining
参数 数值或说明 内涵入口 引气入口 总压 常压 常压 总温/K 310 310 流量/（kg/s） 0.333 0.14 马赫数 0.21 0.37
下载: 导出CSV
-
[1] BARTOLOTTA P A,MCNELIS N B. High speed turbines: development of a turbine accelerator (RTA) for space access[R]. AIAA 2003-6943,2003. [2] SHAFER D G,MCNELIS N B. Development of a ground based Mach 4+ revolutionary technology demonstrator(RTATD)for access to space[R]. ISABE 2003-1125,2003. [3] MCNELIS N,BARTOLOTTA P. Revolutionary turbine accelerator (RTA) demonstrator[R]. AIAA 2005-3250,2005. [4] 钟世林,康玉东,李茜. 宽域涡轮发动机技术发展[J]. 航空动力,2023(4): 19-23. ZHONG Shilin,KANG Yudong,LI Qian. Technology development of wide-range gas turbine engine[J]. Aerospace Power,2023(4): 19-23. (in ChineseZHONG Shilin, KANG Yudong, LI Qian. Technology development of wide-range gas turbine engine[J]. Aerospace Power, 2023(4): 19-23. (in Chinese) [5] Hermeus Corp. Chimera completes ground testing-heads to hypersonic facility for next tests [EB/OL]. (2022-06-07)[2024-11-01]. https://www. hermeus. com/blog-chimera-testing-update/. [6] LEE J,WINSLOW R,BUEHRLE R. The GE-NASA RTA hyperburner design and development[R]. NASA/TM 2005-213803,2005. [7] DAVOUDZADEH F,BUEHRLE R J,LIU N S,et al. Numerical simulation of the rta combustion rig[R]. NASA/TM 2005-213899,2005. [8] 程晓军,范育新,蔡迪,等. 超级燃烧室混合室掺混特性数值研究[J]. 推进技术,2014,35(8): 1094-1101. CHENG Xiaojun,FAN Yuxin,CAI Di,et al. Numerical study of mixing characteristics in hyper-burner mixing chamber[J]. Journal of Propulsion Technology,2014,35(8): 1094-1101. (in ChineseCHENG Xiaojun, FAN Yuxin, CAI Di, et al. Numerical study of mixing characteristics in hyper-burner mixing chamber[J]. Journal of Propulsion Technology, 2014, 35(8): 1094-1101. (in Chinese) [9] 程晓军,范育新,蔡迪,等. 一种波瓣混合器超级燃烧室的掺混特性[J]. 航空动力学报,2014,29(7): 1606-1614. CHENG Xiaojun,FAN Yuxin,CAI Di,et al. Mixing characteristics of hyperburner with a lobed mixer[J]. Journal of Aerospace Power,2014,29(7): 1606-1614. (in ChineseCHENG Xiaojun, FAN Yuxin, CAI Di, et al. Mixing characteristics of hyperburner with a lobed mixer[J]. Journal of Aerospace Power, 2014, 29(7): 1606-1614. (in Chinese) [10] FAN Yuxin,XIAOJUN Cheng,DI Cai. Effect of fuel injection with mixer in TBCC hyperburner[R]. AIAA-2014-3747,2014. [11] 蔡迪. TBCC超级燃烧室掺混技术研究[D]. 南京: 南京航空航天大学,2014. CAI Di. Study on mixing technology of TBCC super combustion chamber[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2014. (in ChineseCAI Di. Study on mixing technology of TBCC super combustion chamber[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2014. (in Chinese) [12] 程晓军. 串联式TBCC超级燃烧室燃烧组织及性能研究[D]. 南京: 南京航空航天大学,2015. CHENG Xiaojun. Study on combustion structure and performance of series TBCC super combustor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2015. (in ChineseCHENG Xiaojun. Study on combustion structure and performance of series TBCC super combustor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2015. (in Chinese) [13] 程晓军,范育新,王家骅. 薄膜蒸发稳定器在超级燃烧室内贫油点熄火特性[J]. 推进技术,2015,36(2): 246-252. CHENG Xiaojun,FAN Yuxin,WANG Jiahua. Performances of lean ignition and lean blowout with film evaporation flameholder in hyperburner[J]. Journal of Propulsion Technology,2015,36(2): 246-252. (in ChineseCHENG Xiaojun, FAN Yuxin, WANG Jiahua. Performances of lean ignition and lean blowout with film evaporation flameholder in hyperburner[J]. Journal of Propulsion Technology, 2015, 36(2): 246-252. (in Chinese) [14] 朱志新,何小民,薛冲,等. 涡轮基组合循环发动机超级燃烧室燃烧性能试验[J]. 航空动力学报,2015,30(9): 2115-2121. ZHU Zhixin,HE Xiaomin,XUE Chong,et al. Experiment on performance of a hyper-combustor utilized in turbine based combined cycle engine[J]. Journal of Aerospace Power,2015,30(9): 2115-2121. (in ChineseZHU Zhixin, HE Xiaomin, XUE Chong, et al. Experiment on performance of a hyper-combustor utilized in turbine based combined cycle engine[J]. Journal of Aerospace Power, 2015, 30(9): 2115-2121. (in Chinese) [15] 张来平,邓小刚,张涵信. 动网格生成技术及非定常计算方法进展综述[J]. 力学进展,2010,40(4): 424-447. ZHANG Laiping,DENG Xiaogang,ZHANG Hanxin. Reviews of moving grid generation techniques and numerical methods for unsteady flow[J]. Advances in Mechanics,2010,40(4): 424-447. (in Chinese doi: 10.6052/1000-0992-2010-4-J2009-123ZHANG Laiping, DENG Xiaogang, ZHANG Hanxin. Reviews of moving grid generation techniques and numerical methods for unsteady flow[J]. Advances in Mechanics, 2010, 40(4): 424-447. (in Chinese) doi: 10.6052/1000-0992-2010-4-J2009-123 [16] 潘宏亮,叶进颖,邹祥瑞,等. RBCC变结构燃烧室动态特性研究[J]. 工程热物理学报,2018,39(9): 2087-2096. PAN Hongliang,YE Jinying,ZOU Xiangrui,et al. Study on dynamic characteristics of RBCC variable structure combustion chamber[J]. Journal of Engineering Thermophysics,2018,39(9): 2087-2096. (in ChinesePAN Hongliang, YE Jinying, ZOU Xiangrui, et al. Study on dynamic characteristics of RBCC variable structure combustion chamber[J]. Journal of Engineering Thermophysics, 2018, 39(9): 2087-2096. (in Chinese) [17] 钱宇,蒋皓. 基于动网格的NACA0012翼型动态失速仿真计算[J]. 计算机仿真,2020,37(4): 44-47,297. QIAN Yu,JIANG Hao. Dynamic stall simulation of NACA0012 airfoil based on dynamic grid[J]. Computer Simulation,2020,37(4): 44-47,297. (in Chinese doi: 10.3969/j.issn.1006-9348.2020.04.009QIAN Yu, JIANG Hao. Dynamic stall simulation of NACA0012 airfoil based on dynamic grid[J]. Computer Simulation, 2020, 37(4): 44-47, 297. (in Chinese) doi: 10.3969/j.issn.1006-9348.2020.04.009 [18] 康泰云. 带旁路引气的混合扩压器稳态/非稳态流场特性研究[D]. 南京: 南京航空航天大学,2020. KANG Taiyun. Study on steady/unsteady flow field characteristics of mixed diffuser with bypass bleed air[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2020. (in ChineseKANG Taiyun. Study on steady/unsteady flow field characteristics of mixed diffuser with bypass bleed air[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. (in Chinese) [19] 谢翌,刘友宏. 波瓣穿透率对波瓣混合排气系统性能影响[J]. 推进技术,2011,32(2): 207-213,252. XIE Yi,LIU Youhong. Effects of lobe penetration ratio on performance of mixer exhaust system[J]. Journal of Propulsion Technology,2011,32(2): 207-213,252. (in ChineseXIE Yi, LIU Youhong. Effects of lobe penetration ratio on performance of mixer exhaust system[J]. Journal of Propulsion Technology, 2011, 32(2): 207-213, 252. (in Chinese) -
点击查看大图
计量
- 文章访问数: 533
- HTML浏览量: 319
- PDF量: 49
- 被引次数: 0