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Preliminary research of terminal shock motion in tandem configuration turbine-based combined cycle inlet

Part of: APISAT 2015

Published online by Cambridge University Press:  23 January 2017

J. Liu ,
H. Yuan ,
Z. Hua ,
W. Chen  and
N. Ge
J. Liu*
Affiliation:
Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, People's Republic of China
H. Yuan*
Affiliation:
Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, People's Republic of China
Z. Hua
Affiliation:
AVIC Shenyang Aircraft Design and Research Institute, Shenyang, People's Republic of China
W. Chen
Affiliation:
Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, People's Republic of China
N. Ge
Affiliation:
Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, People's Republic of China
*
liujunnever@nuaa.edu.cn
yuan_hch7@sina.com
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Abstract

The pressure oscillation and terminal shock motion in a two dimensional inlet, which was designed for tandem configuration turbine-based combined cycle propulsion systems was investigated experimentally and numerically, respectively. The inlet was characterised by a bleed cavity upstream the inlet throat, an S-shape rectangular-to-circular diffuser and flowpaths for a turbine and a ramjet engine. The terminal shock motion was calculated through a second-order unsteady Reynolds-averaged Navier-Stokes scheme. The pressure and the terminal shock were unsteady when the combined cycle inlet operated at different conditions. With the terminal shock located in the throat and at the shoulder of the third ramp of the TBCC inlet, the pressure oscillation was significant and the shock exhibited unsteady streamwise motion with an oscillatory pattern. The amplitude of shock oscillation at these two conditions was 6mm and 12mm, respectively. When the shock was located downstream of the throat and upstream of the cowl lip, it oscillated in a small range. We defined this motion as the “shake” of the shock. This unsteady behaviour of the shock was caused by flow separation in the combined cycle inlet diffuser.

Keywords

hypersonic vehiclecombined cycle propulsion systemstandem configuration turbine-based combined cycle inletterminal shock oscillationwind-tunnel experimentunsteady numerical simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1237 , March 2017 , pp. 416 - 432
Copyright
Copyright © Royal Aeronautical Society 2017 

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References

REFERENCES

1. Hiraiwa, T., Ito, K., Sato, S. et al. Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center. Acta Astronautica, April 2008, 6, (3), pp 565–574. doi:10.1016/j.actaastro.2008.04.011.Google Scholar
2. Walker, S., Tang, M. and Mamplata, C. TBCC propulsion for a Mach 6 hypersonic airplane, AIAA Paper 2009-7238, 2009.Google Scholar
3. Fernández-Villacé, V., Paniagua, G. and Steelant, J. Installed performance evaluation of an air turbo-rocket expander engine. Aerospace Science and Technology, May 2014, 35, pp 63–79. http://dx.doi.org/10.1016/j.ast.2014.03.005.Google Scholar
4. Wang, Z.G., Wang, Y., Zhang, J.Q. et al. Overview of the key technologies of combined cycle engine precooling systems and the advanced applications of micro-channel heat transfer. Aerospace Science and Technology, August 2014, 3, (9), pp 31–39. http://dx.doi.org/10.1016/j.ast.2014.08.008.Google Scholar
5. Bilardo, V.J., Curran, F.M., Hunt, J.L. et al. The benefits of hypersonic airbreathing launch systems for access to space, AIAA Paper 2003-5265, 2003.Google Scholar
6. Mahoney, J.J. Inlets for supersonic missiles, AIAA Education Series, 1990.Google Scholar
7. Marshall, A.W., Gupta, A.K. and Lewis, M.J. Critical issues in TBCC modeling, AIAA Paper 2004-3827, 2004.Google Scholar
8. Takao, O., Yoshinari, E., Hidemasa, N. et al. Experimental approach to the HYPR Mach 5 ramjet propulsion system, AIAA Paper 1998-3277, 1998.Google Scholar
9. Albertson, C.W., Emami, S. and Trexler, C.A. Mach 4 test results of a dual-flowpath, turbine based combined cycle inlet, AIAA Paper 2006-8138, 2006.Google Scholar
10. Zhang, H.J., Guo, R.W. and Xie, L.R. Study of variable geometry bleed cavity of TBCC inlet, J Aerospace Power, December 2012, 27, (12), pp 2714–2723. doi: 10.13224/j.cnki.jasp.2012.12.015.Google Scholar
11. Zhang, H.J., Guo, R.W. and Xie, L.R. Design and validation of scheme over/under TBCC inlet, J Aerospace Power, November 2012, 27, (11), pp 2475–2483. doi: 10.13224/j.cnki.jasp.2012.11.021.Google Scholar
12. Fan, Y., Chang, J., Bao, W. et al. Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets. Aeronautical J, July 2010, 114, (1157), pp 445–450. doi: 10.1017/S0001924000003924.Google Scholar
13. Nakayama, T., Sato, T., Akatsuka, M. et al. Investigation on shock oscillation phenomenon in a supersonic air inlet, AIAA Paper 2011-3094, 2011.Google Scholar
14. Ogawa, T., Watanabe, Y., Murakami, A. et al. Shock wave oscillation phenomena depending on boundary layer conditions in transonic flow, AIAA Paper 2008-717, 2008.Google Scholar
15. Zhang, H.J., Liu, X.G., Guo, R.W. and Xie, L.R. Design of turbo diffuser for TBCC inlet and characteristics of turbo mode, J Aerospace Power, January 2014, 29, (1), pp 181–191. doi: 10.13224/j.cnki.jasp.2014.01.024.Google Scholar
16. Cheng, D.S., Tan, H.J., Sun, S. and Tong, Y. Computational study of a high-performance submerged inlet with bleeding vortex, J Aircraft, March 2012, 49, (3), pp 853–860. doi: 10.2514/1.C031483.Google Scholar
17. Spalart, P.R. and Allmaras, S.R. A one-equation turbulence model for aerodynamic flows, AIAA Paper 92-0439, 1992.Google Scholar
18. Newsome, R.W. Numerical simulation of near-critical and unsteady, subcritical inlet flow, AIAA J, October 1984, 22, (10), pp 1375–1379. doi: 10.2514/3.48577.CrossRefGoogle Scholar
19. Chang, J.T., Wang, L., Bao, W. and Qin, J. Novel oscillatory patterns of hypersonic inlet buzz, J Propulsion and Power, June 2012, 28, (6), pp 1214–1221. doi: 10.2514/1.B34553.Google Scholar
20. Tan, H.J., Li, L.G., Wen, Y.F. and Zhang, Q.F. Experimental investigation of the unstart process of a generic hypersonic inlet, AIAA J, February 2011, 49, (2), pp 279–288. doi: 10.2514/1.J050200.Google Scholar
21. Hyoung, J.L., Bok, J.L., Sung, D.K. and Jeung, I.S. Flow characteristics of small-sized supersonic inlets, J Propulsion and Power, February 2011, 27, (2), pp 306–318. doi: 10.2514/1.46101.Google Scholar
22. Vivek, P. and Mittal, S. Buzz instability in a mixed-compression air intake, J Propulsion and Power, March 2009, 25, (3), pp 819–822. doi: 10.2514/1.39751.Google Scholar