Analysis of flow field of three-dimensional ejector nozzle with open-close alternate intake valve at transonic velocity
-
摘要:
通过仿真研究了跨声速飞行状态下（
Ma =1.2）一种带间隔式进气门的引射喷管流动特性，获得了二次流对三次流流动状态、喷管流动结构以及推力性能的影响规律。结果表明：带有间隔式辅助进气门的引射喷管内部存在显著的横向流动，诱导产生了多对流向涡结构，沿着流动方向流向涡的尺度逐渐减小。主流始终处于过膨胀状态，主导了引射喷管的内流流动，并和二次流之间形成了一道剪切层结构。随着二次流落压比的升高，二次流和三次流流量增加，其对主流的束缚作用增强，主流过膨胀现象得到有效抑制，推力性能从0.698增加至0.819。Abstract:To analyze the influence of different secondary air intake states, the flow characteristics of an ejector nozzle with open-close intake valves in the transonic flight state (
Ma =1.2) were simulated and studied. By changing the nozzle pressure ratio (NPR) of the secondary flow, the flow state of the third flow, the development characteristics of the vortex, and the thrust performance in the nozzle were analyzed. The results showed that the airflow in the ejector nozzle with the open-close alternate intake valve had the phenomenon of lateral flow, forming a vortex ring that the size of the flow vortex gradually decreased along the flow direction. The main flow maintained an over-expansion state, which dominated the inner flow of the ejector nozzle, and formed a shear layer structure with the secondary flow. With the increase of the NPR of the secondary flow, the flow rates of the secondary and third flows increased, which led to a stronger binding effect on the main flow. Therefore, the mainstream over-expansion phenomenon was effectively suppressed, so the thrust performance increased from 0.698 to 0.819.-
Key words:
- transonic speed /
- ejector nozzle /
- open-close alternate intake valve /
- vortex /
- thrust performance
-
图 1 引射喷管的三维物理模型结构示意图
Figure 1. Three-dimensional physical model structure of ejector nozzle
图 5 实验结果与仿真结果对比（Ma=1.1）
Figure 5. Comparison of experimental results and simulation results （Ma=1.1）
图 6 网格无关性验证的压力对比曲线
Figure 6. Pressure comparison curve for grid independence verification
图 7 引射喷管模型对称面的马赫数结构云图
Figure 7. Mach number diagram of symmetry plane of ejector nozzle model
图 8 引射喷管对称面上的沿程压力曲线变化
Figure 8. Change of pressure curve along symmetry plane of ejector nozzle
图 9 截面（距离侧壁10 mm）上的马赫数结构云图
Figure 9. Mach number structure on the surface （10 mm from the side wall）
图 12 监测面b（喷管拐点）漩涡结构图
Figure 12. Vortex structure of monitoring surface b （nozzle turning point）
图 13 监测面c（喷管拐点）漩涡结构图
Figure 13. Vortex structure of monitoring surface c （nozzle turning point）
图 11 监测面a（喷管喉部）流向涡结构图
Figure 11. Vortex ring structure of monitoring surface a （nozzle throat）
图 15 监测面e（喷管出口） 漩涡结构图
Figure 15. Vortex structure of monitoring surface e （outlet of nozzle）
表 1 引射喷管物理结构尺寸参数
Table 1. Physical structure size parameters of ejector nozzle
参数 数值 主流喷管高度Df/mm 120.75 次流喷管高度Ds/mm 40.38 主流喷管出口高度Dp/mm 55.75 喉道高度Dt/mm 135.00 出口高度De/mm 241.30 三次流辅助进气门开度α/（°） 22 尾喷管转角β/（°） 11.5 喷管出口到喉部距离Lp/mm 272.33 喷管出口到主喷管出口距离Le/mm 314.49 三次流辅助门长度Lt/mm 98.2 三次流辅助门宽度Lo/mm 100 三次流辅助门隔板宽度Lc/mm 100 
下载: 导出CSV
表 2 引射喷管边界条件及参数
Table 2. Boundary conditions and parameters of ejector nozzle
边界 边界条件 马赫数Ma 压力p0/Pa 温度T/K 自由来流 压力远场 1.2 30800 229.73 自由出口 压力出口边界 1.2 30800 229.73 引射喷管出口 压力出口边界 1.2 30800 229.73 主喷管入口 压力入口边界 1.2 165088（rnp=5.36） 1901.7 二次流入口 压力入口边界 1.2 30800（rnp=1.0）、33880（rnp=1.1）、
36960（rnp=1.2）、40040（rnp=1.3）296 对称面 对称面边界 1.2 物面 壁面边界 1.2
下载: 导出CSV
表 3 监测面位置参数
Table 3. Monitoring surface position parameters
截面 位置 a X=226.4 mm（尾喷管喉部） b X=313 mm（尾喷管拐点） c X=400 mm d X=450 mm e X=497 mm（喷管出口）
下载: 导出CSV
表 4 四种不同工况下的引射喷管推力性能参数
Table 4. Thrust performance parameters of ejector nozzle under four different working conditions
参数 rnp=1.0 rnp=1.1 rnp=1.2 rnp=1.3 主流流量/（kg/s） 1.63 1.63 1.63 1.63 二次流流量/（kg/s） 0.223 0.280 0.333 0.356 三次流流量/（kg/s） 0.284 0.292 0.288 0.331 二、三次流流量/（kg/s） 0.507 0.572 0.621 0.687 引射喷管出口流量/（kg/s） 2.143 2.207 2.257 2.321 引射喷管出口速度/（m/s） 1048.9 1013.13 986.47 957.42 引射喷管出口静压/Pa 20834.3 22199.9 23364.1 24575.0 推力系数 0.698 0.758 0.790 0.819 推力系数增长比/% 8.59 13.18 17.34
下载: 导出CSV
-
[1] 梁德旺. 流体力学基础[M]. 北京: 航空工业出版社, 1998. [2] TAKAHASHI M, SUNAMI T, TANNO H, et al. Performance characteristics of a scramjet engine at Mach 10 to 15 flight condition[R]. AIAA 2005-3350, 2005. [3] HEISER W H. Ejector thrust augmentation[J]. Journal of Propulsion and Power,2010,26(6): 1325-1330. doi: 10.2514/1.50144 [4] WILSON J,SGONDEA A,PAXSON D E,et al. Parametric investigation of thrust augmentation by ejectors on a pulsed detonation tube[J]. Journal of Propulsion and Power,2007,23(1): 108-115. doi: 10.2514/1.19670 [5] VIETS H. Thrust augmenting ejector analogy[J]. Journal of Aircraft,1977,14(4): 409-411. doi: 10.2514/3.44603 [6] CANDEL S. Concorde and the future of supersonic transport[J]. Journal of Propulsion and Power,2004,20(1): 59-68. doi: 10.2514/1.9180 [7] 张先锋,刘明侯,张根,等. 微喷管流场及其推力性能数值模拟[J]. 宇航学报,2006,27(4): 720-725. doi: 10.3321/j.issn:1000-1328.2006.04.030ZHANG Xianfeng,LIU Minghou,ZHANG Gen,et al. Simulations of flow field and thrust performance in micronozzle[J]. Journal of Astronautics,2006,27(4): 720-725. (in Chinese) doi: 10.3321/j.issn:1000-1328.2006.04.030 [8] DEBONIS J. Full Navier-Stokes analysis of a two-dimensional mixer/ejector nozzle for noise suppression[R]. AIAA-92-3570, 1992 [9] CHOW W L,ADDY A L. Interaction between primary and secondary streams of supersonic ejector systems and their performance characteristics[J]. AIAA Journal,1964,2(4): 686-695. doi: 10.2514/3.2403 [10] JOE D Jr. Improved methods of characterizing ejector pumping performance[J]. Journal of Propulsion and Power,1991,7(3): 412-419. doi: 10.2514/3.23342 [11] LUGINSLAND T. How the nozzle geometry impacts vortex breakdown in compressible swirling-jet flows[J]. AIAA Journal,2015,53(10): 1-15. [12] ARUN K R. RAJESH G. Physics of vacuum generation in zero-secondary flow ejectors[J]. Physics of Fluids,2018,30(6): 066102. doi: 10.1063/1.5030073 [13] KARTHICK S K,RAO S M V,JAGADEESH G,et al. Parametric experimental studies on mixing characteristics within a low area ratio rectangular supersonic gaseous ejector[J]. Physics of Fluids,2016,28(8): 076101. [14] 吴继平, 王振国. 等截面超-超引射器内流场的流动显示研究[C]//第八届全国实验流体力学学术会议. 广州: 中国力学学会, 2010: 259-263. [15] 陈健,王振国,吴继平,等. 等截面超-超引射器流场结构及引射性能[J]. 强激光与粒子束,2012,24(6): 1301-1305. doi: 10.3788/HPLPB20122406.1301CHEN Jian,WANG Zhenguo,WU Jiping,et al. Flow structure and performance of constant-area, supersonic-supersonic ejector[J]. High Power Laser and Particle Beams,2012,24(6): 1301-1305. (in Chinese) doi: 10.3788/HPLPB20122406.1301 [16] 吴达,董振宁. 气动可调喷管的研究[J]. 推进技术,1986,7(6): 31-37. doi: 10.13675/j.cnki.tjjs.1986.06.005 [17] 吴达,董振宁. 气动调节喷管的性能分析[J]. 航空学报,1987,8(6): 256-261. doi: 10.3321/j.issn:1000-6893.1987.06.005WU Da,DONG Zhenning. Analysis of the performance of aerodynamically variable nozzle[J]. Acta Aeronautica et Astronautica Sinica,1987,8(6): 256-261. (in Chinese) doi: 10.3321/j.issn:1000-6893.1987.06.005 [18] 周唯阳. 串联布局TBCC可调喷管的设计、仿真与实验研究[D]. 南京: 南京航空航天大学, 2012.ZHOU Weiyang. Computational and experimental study on a variable nozzle for TBCC with tandem layout[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese) -
点击查看大图
计量
- 文章访问数: 112
- HTML浏览量: 43
- PDF量: 39
- 被引次数: 0