Experimental investigation on aerodynamic performance of hypersonic wind tunnel two-stage ejector

Guo Xiaoguo; Jiang Zepeng; Chen Xing; Wang Tiejin

doi:10.11729/syltlx20170041

Volume 32 Issue 4

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2018 > 32(4): 99-103

Guo Xiaoguo, Jiang Zepeng, Chen Xing, et al. Experimental investigation on aerodynamic performance of hypersonic wind tunnel two-stage ejector[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(4): 99-103. doi: 10.11729/syltlx20170041

Citation:

PDF( 1873 KB)

Experimental investigation on aerodynamic performance of hypersonic wind tunnel two-stage ejector

doi: 10.11729/syltlx20170041

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received Date: 2017-03-20
Rev Recd Date: 2017-12-04
Publish Date: 2018-08-25

Abstract

Abstract

The aerodynamic performance of the two-stage supersonic ejector is investigated by the Ma5~6 experiment on the FD-07 wind tunnel of CAAA. The experimental data is acquired by the test of the second stage ejector, the combined test of the first and the second stage ejectors, and the combined test of the main flow and the secondary flow. The conclusion can be organized as followed:(1) The ejector operating efficiency is higher and medium pressure gas consumption is less when the work pressure ratio of the two-stage ejector is setted to 0.8MPa and 1.0MPa, respecticely. (2) The low pressure environment of the test section is mainly determined by the main air flow. As far as the start-up pressure ratio of the wind tunnel is satisfied, the ope-rating parameters of the ejector have little effect on the pressure of the test section. (3) The first-stage supersonic ejector can be well segregated from the main airflow disturbance and the second-stage supersonic airlow interference, which is instructive for the theoretical study of the multi-stage ejector. The research work is carried out with the actual wind tunnel as the object, and effectively solves the problem that the running state of the FD-07 wind tunnel ejector is not clear. The ejector operating pressure scheme has been optimized so to be energy saving, and it has practical significance for the hypersonic wind tunnel performance improvement. The relevant test data can provide a reference for the study of aerodynamic performance of the supersonic ejector.
- hypersonic wind tunnel,
- two-stage ejector,
- aerodynamic performance,
- pressure optimization

FullText(HTML)

References(14)

References

[1]	Sun D W, Eames I W. Recent development in the design theories and applications of ejector-a review[J]. Journal of the Institute of Energy, 1995, 68:65-79.
[2]	Mikkelsen C D, Sandberg M R, Addy A L. Theoretical and experimental analysis of the constant-area, supersonic-supersonic ejector[R]. UILU ENG 76-4003, 1976.
[3]	Dutton J C, Carroll B F. Optimal supersonic ejector designs[J]. Journal of Fluids Engineering, 1986, 108(4):414-420. doi: 10.1115/1.3242597
[4]	徐万武, 邹建军, 王振国, 等.超声速环型引射器启动特性试验研究[J].火箭推进, 2005, 31(6):7-11. doi: 10.3969/j.issn.1672-9374.2005.06.002 Xu W W, Zou J J, Wang Z G, et al. Experimental investigation of the start performances of the supersonic annular ejector[J]. Journal of Rocket Propulsion, 2005, 31(6):7-11. doi: 10.3969/j.issn.1672-9374.2005.06.002
[5]	邹建军, 周进, 徐万武, 等.超音速环形引射器空气引射启动特性试验[J].国防科技大学学报, 2008, 30(1):1-4. doi: 10.3969/j.issn.1001-2486.2008.01.001 Zou J J, Zhou J, Xu W W, et al. Experimental investigation on the start performances of the supersonic annular ejector[J]. Journal of National University of Defense Technology, 2008, 30(1):1-4. doi: 10.3969/j.issn.1001-2486.2008.01.001
[6]	刘宗政, 郭隆德, 廖达雄, 等.基于多级等压混合的引射器参数匹配与优化[J].空气动力学学报, 2012, 30(5):573-577. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201205003 Liu Z Z, Guo L D, Liao D X, et al. Parameters match and optimization based on multilevel isotonic mixed ejector[J]. Acta Aerodynamica Sinica, 2012, 30(5):573-577. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201205003
[7]	王宗浩, 邹建军, 黄洁, 等.两级超声速引射器流动机理研究[J].推进技术, 2013, 34(10):1304-1309. http://d.old.wanfangdata.com.cn/Periodical/tjjs201310002 Wang Z H, Zou J J, Huang J. Supersonic to supersonic ejection mechanism of a two-stage ejector[J]. Journal of Propulsion Technology, 2013, 34(10):1304-1309. http://d.old.wanfangdata.com.cn/Periodical/tjjs201310002
[8]	刘化勇.超声速引射器的数值模拟方法及其引射特性研究[D].绵阳: 中国空气动力与研究发展中心, 2009. Liu H Y. Development of numerical method and investigation on performances of supersonic ejectors[D]. Mianyang: China Aerodynamics Research and Development Center, 2009.
[9]	陈立红, 张新宇, 顾洪斌.扩压段对高超声速推进风洞启动的影响[J].推进技术, 2004, 25(5):430-434. doi: 10.3321/j.issn:1001-4055.2004.05.011 Chen L H, Zhang X Y, Gu H B. Investigation for effect of supersonic diffusers on the start of the hypersonic propulsion test facility[J]. Journal of Propulsion Technology, 2004, 25(5):430-434. doi: 10.3321/j.issn:1001-4055.2004.05.011
[10]	Albertson C W, Emami S. Alleviation of facility/engine interactions in an open-jet scramjet test facility[R]. AIAA-2001-3677, 2001.
[11]	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. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs201206009 Chen J, Wang Z G, Wu J P, et al. Flow structure and perfor-mance of constant-area, supersonic-supersonic ejector[J]. High Power Laser and Particle Beams, 2012, 24(6):1301-1305. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs201206009
[12]	Dvorak V, Safarik P. Supersonic flow structure in the entrance part of a mixing chamber of 2D model ejector[J]. Journal of Thermal Science, 2003, 12(4):344-349. doi: 10.1007/s11630-003-0042-8
[13]	Dvorak V, Safarik P. Transonic instability in entrance part of mixing chamber of high-speed ejector[J]. Journal of Thermal Science, 2005, 14(3):258-263, 271. doi: 10.1007/s11630-005-0011-5
[14]	Dutton J C, Mikkelsen C D, Addy A L. A theoretical and experimental investigation of the constant area, supersonic-supersonic ejector[J]. AIAA Journal, 1981, 20(10):1392-1400. doi: 10.2514-3.51199/