基于TBCC进排气一体化的引射喷管气动设计研究

张可心; 黄河峡; 谭慧俊

doi:10.13224/j.cnki.jasp.20230521

基于TBCC进排气一体化的引射喷管气动设计研究

doi: 10.13224/j.cnki.jasp.20230521

1.
中科南京未来能源系统研究院，南京 211135
2.
南京航空航天大学能源与动力学院，南京 210016

基金项目: 中科南京未来能源系统研究院院级项目（KCW-31）

详细信息

作者简介:
张可心（1994-），女，工程师，硕士，主要从事内流气体动力学研究。E-mail：zhangkexin@njiet.cn

中图分类号: V211.3
计量
- 文章访问数: 280
- HTML浏览量: 144
- PDF量: 52
- 被引次数: 0
出版历程
- 收稿日期: 2023-08-10
- 网络出版日期: 2025-02-22

Research on aerodynamic design of an ejector nozzle based on TBCC integrated engine

1.
Nanjing Institute of Future Energy System，Nanjing 211135，China
2.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
针对引射喷管在设计点的型面设计参数开展了数值仿真研究，探究了主喷管长度、引射喷管喉道面积、喉道位置、扩张段面积变化规律对流动特性及推力性能的影响。研究表明：减小主喷管长度、适当增加引射喷管喉道面积、使引射喷管喉道位置向后移动、增加扩张段横截面积均有利于提升引射喷管的推力系数，而各型面参数对引射喷管的影响主要体现在主流膨胀程度及剪切层特性上。经验证，在全包线工作范围（马赫数为0～4）内引射喷管取得较优的气动性能，设计状态推力系数可达0.96。
- 引射喷管 /
- 型面参数 /
- 剪切层特性 /
- 流动特性 /
- 推力性能
Abstract:
The effects of main design parameters of the ejector nozzle, including the length of the main nozzle, the throat area of the ejector nozzle, the position of the throat and the area of the expansion section, on the internal flow-field and thrust performance in the design state were studied through numerical simulations. The results showed that, in order to improve the thrust coefficient of the ejector nozzle, it is advantageous to reduce the length of the main nozzle, appropriately increase the throat area of the ejector nozzle, move the position of the ejector nozzle throat backward and increase the cross-sectional area of the expansion section in the ejector. The influence of various design parameters on the flow mechanism was mainly embodied in the degree of the mainstream expansion and the characteristics of the shear layer. It was verified that the ejector nozzle could achieve good aerodynamic performance within the full operating range (Mach number of 0 to 4). In the design state, the thrust coefficient could reach 0.96.
- ejector nozzle /
- profile parameters /
- shear layer characteristics /
- flow characteristics /
- thrust performance

HTML

图 1 引射喷管物理模型

Figure 1. Physical model of ejector nozzle

下载: 全尺寸图片幻灯片

图 2 不同网格量的引射喷管马赫数云图

Figure 2. Mach number contours of ejector nozzle with different grids

下载: 全尺寸图片幻灯片

图 3 不同网格量的引射喷管壁面静压分布

Figure 3. Static pressure distribution on wall of ejector nozzle with different grids

下载: 全尺寸图片幻灯片

图 4 NASA风洞试验模型^[17]

Figure 4. Experimental model in NASA wind tunnel^[17]

下载: 全尺寸图片幻灯片

图 5 NASA风洞试验验证（ω=0.1）

Figure 5. Validation with NASA wind tunnel test （ω=0.1）

下载: 全尺寸图片幻灯片

图 6 R_np,p=5.3，R_np,s=2.1试验^[18]与仿真纹影流场结构对比

Figure 6. Comparison of flow field structure between experimental schlieren^[18] and numerical schlieren at R_np,p=5.3, R_np,s=2.1

下载: 全尺寸图片幻灯片

图 7 R_np,p=5.3，R_np,s=2.1试验与仿真壁面静压对比

Figure 7. Comparison of static pressure on wall between experimental results and numerical results at R_np,p=5.3, R_np,s=2.1

下载: 全尺寸图片幻灯片

图 8 主喷管长度变化区间

Figure 8. Variation range of main nozzle length

下载: 全尺寸图片幻灯片

图 9 Ma₀=4, R_np,p=75, ω=0.04, 不同主喷管长度时引射喷管的马赫数图及流线图

Figure 9. Mach number contours and streamlines of ejector nozzle with different main nozzle length at Ma₀=4, R_np,p=75, ω=0.04

下载: 全尺寸图片幻灯片

图 10 不同主喷管长度的引射喷管壁面静压曲线

Figure 10. Curves of static pressure on wall of ejector nozzle with different main nozzle lengths

下载: 全尺寸图片幻灯片

图 11 不同主喷管长度下引射喷管出口轴向速度径向分布曲线

Figure 11. Curves of axial velocity along radial direction at exit station of ejector nozzle with different main nozzle lengths

下载: 全尺寸图片幻灯片

图 12 不同主喷管长度下引射喷管出口静压变化曲线

Figure 12. Curves of static pressure at exit station of ejector nozzle with different main nozzle lengths

下载: 全尺寸图片幻灯片

图 13 不同主喷管长度时引射喷管推力系数变化曲线

Figure 13. Variation of thrust coefficient of ejector nozzle with different main nozzle lengths

下载: 全尺寸图片幻灯片

图 14 不同主喷管长度时引射喷管总压恢复系数系数变化曲线

Figure 14. Variation of total pressure recovery coefficient of ejector nozzle with different main nozzle lengths

下载: 全尺寸图片幻灯片

图 15 不同喉道面积的引射喷管

Figure 15. Ejector nozzle with different throat areas

下载: 全尺寸图片幻灯片

图 16 Ma₀=4, R_np,p=75, ω=0.04, 不同喉道面积时引射喷管的马赫数图及流线图

Figure 16. Mach number contours and streamlines of ejector nozzle with different throat areas at Ma₀=4, R_np,p=75, ω=0.04

下载: 全尺寸图片幻灯片

图 17 不同喉道面积时引射喷管壁面静压曲线

Figure 17. Curves of static pressure on wall of ejector nozzle with different throat areas

下载: 全尺寸图片幻灯片

图 18 不同喉道面积时引射喷管出口静压曲线

Figure 18. Curves of static pressure at exit station of ejector nozzle with different throat areas

下载: 全尺寸图片幻灯片

图 19 不同喉道面积时引射喷管推力系数变化曲线

Figure 19. Variation of thrust coefficient of ejector nozzle with different throat areas

下载: 全尺寸图片幻灯片

图 20 不同喉道面积时引射喷管总压恢复系数变化曲线

Figure 20. Variation of total pressure recovery coefficient of ejector nozzle with different throat areas

下载: 全尺寸图片幻灯片

图 21 不同喉道位置的引射喷管

Figure 21. Ejector nozzle with different throat positions

下载: 全尺寸图片幻灯片

图 22 Ma₀=4, R_np,p=75, ω=0.04, 不同喉道位置时引射喷管的马赫数图及流线图

Figure 22. Mach number contours and streamlines of ejector nozzle with different throat positions at Ma₀=4, R_np,p=75, ω=0.04

下载: 全尺寸图片幻灯片

图 23 不同喉道位置时引射喷管壁面静压曲线

Figure 23. Curves of static pressure on wall of ejector nozzle with different throat positions

下载: 全尺寸图片幻灯片

图 24 不同喉道位置时引射喷管出口静压曲线

Figure 24. Curves of static pressure at exit station of ejector nozzle with different throat positions

下载: 全尺寸图片幻灯片

图 25 不同喉道位置时引射喷管推力系数变化曲线

Figure 25. Variation of thrust coefficient of ejector nozzle with different throat positions

下载: 全尺寸图片幻灯片

图 26 不同喉道位置时引射喷管总压恢复系数变化曲线

Figure 26. Variation of total pressure recovery coefficient of ejector nozzle with different throat positions

下载: 全尺寸图片幻灯片

图 27 不同尾缘角的引射喷管

Figure 27. Ejector nozzle with different tail angles

下载: 全尺寸图片幻灯片

图 28 Ma₀=4, R_np,p=75, ω=0.04, 不同尾缘角时引射喷管的马赫数图及流线图

Figure 28. Mach number contours and streamlines of ejector nozzle with different tail angles at Ma₀=4, R_np,p=75, ω=0.04

下载: 全尺寸图片幻灯片

图 29 不同尾缘角时引射喷管壁面静压曲线

Figure 29. Curves of static pressure on wall of ejector nozzle with different tail angles

下载: 全尺寸图片幻灯片

图 30 不同尾缘角时引射喷管出口静压分布曲线

Figure 30. Curves of static pressure at exit station of ejector nozzle with different tail angles

下载: 全尺寸图片幻灯片

图 31 不同尾缘角时引射喷管推力系数变化曲线

Figure 31. Variation of thrust coefficient of ejector nozzle with different tail angles

下载: 全尺寸图片幻灯片

图 32 不同尾缘角时引射喷管总压恢复系数变化曲线

Figure 32. Variation of total pressure recovery coefficient of ejector nozzle with different tail angles

下载: 全尺寸图片幻灯片

表 1 引射喷管的主要型面参数

Table 1. Major profile parameters of ejector nozzle

无量纲参数	数值
主喷管出口直径D_p/D	0.72
引射喷管喉道直径D_t/D	1.12
主喷管等直段长度L/D	0.20
引射喷管喉道直径距离主喷管出口的轴向距离（L_t−L_p）/D_p	−0.06
引射喷管长度L_e/D	1.36
辅助进气门旋转角度θ/（°）	0～30
尾缘角β/（°）	4

下载: 导出CSV

表 2 来流条件

Table 2. Incoming-flow conditions

参数	数值
马赫数Ma	4
环境压力/Pa	2971.75
环境温度/K	926.35
主流落压比	75
主流总温/K	2100

下载: 导出CSV

表 3 不同主喷管长度时引射喷管的性能参数

Table 3. Performance parameters of ejector nozzle with different main nozzle lengths

L/D	动量推力F_v/N	推力系数C_f	总压恢复系数σ
0.20	62447.77	0.9426	0.9268
0.27	62425.72	0.9392	0.9364
0.34	62060.10	0.9333	0.9416
0.48	60330.20	0.9160	0.9502
0.54	59073.75	0.9065	0.9593
0.61	57607.59	0.8999	0.9690

下载: 导出CSV

表 4 不同引射喷管喉道面积时引射喷管性能参数

Table 4. Performance parameters of ejector nozzle with different throat areas

D_t/D	动量推力F_v/N	推力系数C_f	总压恢复系数σ
0.98	61130.57	0.9261	0.9566
1.01	61148.43	0.9261	0.9545
1.04	61172.31	0.9264	0.9518
1.06	60967.88	0.9262	0.9419
1.09	61256.22	0.9282	0.9453
1.12	61114.93	0.9286	0.9386

下载: 导出CSV

表 5 不同喉道位置下引射喷管性能参数

Table 5. Performance parameters of ejector nozzle with different throat positions

ϛ	动量推力F_v/N	推力系数C_f	总压恢复系数σ
0.06	60910.77	0.9504	0.9209
0.04	61605.00	0.9508	0.9406
0.22	61189.24	0.9481	0.9205
0.32	61370.51	0.9471	0.9200
0.41	61645.96	0.9460	0.9215
0.51	62009.16	0.9442	0.9246

下载: 导出CSV

表 6 不同尾缘角引射喷管性能参数

Table 6. Performance parameters of ejector nozzle with different tail angles

β/（°）	动量推力F_v/N	推力系数C_f	总压恢复系数σ
4	61748.99	0.9522	0.9255
8	62448.76	0.9490	0.9289
12	62929.94	0.9473	0.9317
16	63226.47	0.9468	0.9346
20	63337.15	0.9469	0.9368

下载: 导出CSV

表 7 全包线工作范围内引射喷管性能参数

Table 7. Performance parameters of ejector nozzle in full operation range

Ma	引射系数ω	推力系数C_f	总压恢复系数σ
0	0.017	0.9085	0.89
0.9	0.022	0.9670	0.87
1.1	0.154	0.9808	0.88
3	0.010	0.9819	0.94
4	0.032	0.9611	0.92

下载: 导出CSV

参考文献(18)

[1]	刘大响,金捷. 21世纪世界航空动力技术发展趋势与展望[J]. 中国工程科学,2004,6(9): 1-8. LIU Daxiang,JIN Jie. The development trends and prospect of world aeropropulsion technology in the 21st century[J]. Engineering Science,2004,6(9): 1-8. (in Chinese doi: 10.3969/j.issn.1009-1742.2004.09.001 LIU Daxiang, JIN Jie. The development trends and prospect of world aeropropulsion technology in the 21st century[J]. Engineering Science, 2004, 6(9): 1-8. (in Chinese) doi: 10.3969/j.issn.1009-1742.2004.09.001
[2]	KELLY M,MENICH R,OLDS J. What’s cheaper to fly: rocket or TBCC? Why?[R]. Huntsville,US: SpaceOps 2010 Conference Delivering on the Dream,2010.
[3]	COCKRELL C,AUSLENDER A,GUY R,et al. Technology roadmap for dual-mode scramjet propulsion to support space-access vision vehicle development[R]. AIAA2002-5188,2002.
[4]	KOJIMA T,TAGUCHI H,KOBAYASHI H,et al. Design and fabrication of variable nozzle for precooled turbojet engine[R]. AIAA2009-7312,2009.
[5]	HARDY J M,DELERY J. Present possibilities for a theoretical study of a supersonic ejector nozzle[R]. NASA TT F-9870,1966.
[6]	黄河峡,张可心,谭慧俊,等. 带第三流路辅助进气的引射喷管流动特性研究[J]. 推进技术,2020,41(12): 2729-2738. HUANG Hexia,ZHANG Kexin,TAN Huijun,et al. Flow characteristics of an integrated ejector nozzle with tertiary intake[J]. Journal of Propulsion Technology,2020,41(12): 2729-2738. (in Chinese HUANG Hexia, ZHANG Kexin, TAN Huijun, et al. Flow characteristics of an integrated ejector nozzle with tertiary intake[J]. Journal of Propulsion Technology, 2020, 41(12): 2729-2738. (in Chinese)
[7]	ANDERSON B. Factors which influence the analysis and design of ejector nozzles[R]. AIAA1972-46,1972.
[8]	吴达,陈芬. 引射增力器的性能分析和实验研究[J]. 推进技术,1988,9(2): 14-21,94-95. WU Da,CHEN Fen. Analytical and experimental study of thrust augmentation ejector[J]. Journal of Propulsion Technology,1988,9(2): 14-21,94-95. (in Chinese WU Da, CHEN Fen. Analytical and experimental study of thrust augmentation ejector[J]. Journal of Propulsion Technology, 1988, 9(2): 14-21, 94-95. (in Chinese)
[9]	吴达,董振宁. 气动可调喷管的研究[J]. 推进技术,1986,7(6): 31-37. WU Da,DONG Zhenning. Study on pneumatic adjustable nozzle[J]. Journal of Propulsion Technology,1986,7(6): 31-37. (in Chinese WU Da, DONG Zhenning. Study on pneumatic adjustable nozzle[J]. Journal of Propulsion Technology, 1986, 7(6): 31-37. (in Chinese)
[10]	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. WU 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 WU 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
[11]	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
[12]	BRADSHAW P,FERRISS D H,JOHNSON R F. Turbulence in the noise-producing region of a circular jet[J]. Journal of Fluid Mechanics,1964,19(4): 591-624. doi: 10.1017/S0022112064000945
[13]	HUDDLESTON S C,WILSTED H D,ELLIS C W. Performance of several air ejectors with conical mixing sections and small secondary flow rates[M]//National Advisory Committee for Aeronautics Collection. Washington,US: National Advisory Committee for Aeronautics,1948.
[14]	伊赫桑·巴伦. 纯物质热化学数据手册[M]. 北京: 科学出版社,2003.
[15]	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. Design,simulation and experimental study of TBCC adjustable nozzle with series arrangement[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2012. (in Chinese ZHOU Weiyang. Design, simulation and experimental study of TBCC adjustable nozzle with series arrangement[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)
[16]	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
[17]	ANDERSON B H. Assessment of an analytical procedure for predicting supersonic ejector nozzle performance[R]. NASA TN D-7601,1974.
[18]	林坚强. 宽范围串联TBCC组合喷管性能研究与实验验证[D]. 南京: 南京航空航天大学,2020. LIN Jianqiang. Performance study and experimental verification of TBCC combined nozzle with wide range series connection[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2020. (in Chinese LIN Jianqiang. Performance study and experimental verification of TBCC combined nozzle with wide range series connection[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. (in Chinese)