Hostname: page-component-76fb5796d-vfjqv Total loading time: 0 Render date: 2024-04-26T02:39:22.001Z Has data issue: false hasContentIssue false
  • English
  • Français

On the start condition of a second-throat ejector-diffuser

Published online by Cambridge University Press:  04 July 2016

J. J. Wang  and
F. Chen
J. J. Wang
Affiliation:
Institute of Applied Mechanics National Taiwan University Taipei, Taiwan, ROC
F. Chen
Affiliation:
Institute of Applied Mechanics National Taiwan University Taipei, Taiwan, ROC
Get access Rights & Permissions [Opens in a new window]

Abstract

The start condition of a second-throat ejector-diffuser (STED) system has been studied by solving the axisymmetric Navier-Stokes equations with a high order conservative supra-characteristics method (CSCM). According to the conventional concept, when a STED is started, the flow passing through the second-throat contraction should be supersonic so that the normal shock swallowing condition applying for a supersonic windtunnel holds. The present numerical results, however, suggest that a STED can be started with a normal shock forming ahead of the second-throat contraction because the high speed flow in the region close to the wall of the diffuser serves to release the mass blocked by the normal shock, leading to a decrease in chamber pressure as well as the start of the system. This not only contradicts the conventional concept of the start of a STED, but also provides an explanation for the experimental discrepancy between the start conditions of a STED and a supersonic windtunnel.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 998 , October 1996 , pp. 321 - 326
Copyright
Copyright © Royal Aeronautical Society 1996 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Alperin, M. and Wu, J.J. Recent development of a jet-diffuser ejector, JAircr, 1981, 18, p 1011.Google Scholar
2. Alperin, M. and Wu, J.J. Thrust augmenting ejectors, Part I, AIAA J, 1983, 21, p 1428.Google Scholar
3. Alperin, M. and Wu, J.J. Thrust augmenting ejectors, Part II, AIAA J, 1983, 21, p 1698.Google Scholar
4. Porter, J.L. and Squyers, R.A. A Summary/Overview of Ejector Augmentor Theory and Performance, ATC Report No R-91100/9CR-47A, Vought Advanced Technical Center, Dallas, Texas, 1981.Google Scholar
5. Nelson, CD. and Yang, T. Design of branched and unbranched axially symmetrical ducts with specified pressure distribution, AIAA J, 1981, 15, p 1272.Google Scholar
6. Yang, T. and Nelson, CD. Griffith diffusers, J Fluids Eng, ASME Trans, 1979, 101, p 473.Google Scholar
7. Yang, T., Stone, F., Jiang, T., and Pitts, D.R. An investigation of high performance, short thrust augmenting ejectors, J Fluids Eng, ASME Trans, 1985, 107, p 23.Google Scholar
8. German, R.C., Bauer, R.C., and Panesci, J.H. Methods for determining the performance of ejector-diffuser system, J Spacecr, 1966, 3, p 193.Google Scholar
9. Hale, J.W. Comparison of diffuser ejector performance with five different driving fluids, AEDC-TDR-63 207, Arnold Air Force Station, Tenn, October 1963.Google Scholar
10. Panesci, J.H. and German, R.C. An analysis of second throat diffuser performance for zerosecondary-flow ejector systems, AEDC TDR-63-249, Arnold Air Force Station, Tenn, October 1963.Google Scholar
11. Ducasse, P. Rocket altitude test facility register, AGARD-AG-297, Direction Tech des Eng, Paris, France, March 1987.Google Scholar
12. Lombard, C.K., Bardina, J., Venkatapathy, E. and Oliger, J. Multi-dimensional formulation of CSCM an upwind flux difference split method for the compressible Navier-Stokes equations, AIAA Paper 83-1895, 1983.Google Scholar
13. Anderson, D.A., Tannehill, J.C. and Pletcher, R.H. Computational Fluid Mechanics and Heat Transfer, McGraw-Hill, New York, 1984.Google Scholar
14. Lee, T.S., Liang, J.K. and Hsu, F.Y. Experimental study of second-throat diffuser ejectors, CSIST Report 1833-79, Taoyuan, Taiwan, October 1990.Google Scholar
15. Karniadakis, G.E. and Orszag, S.A. Nodes, modes and flow codes, Phys Today, 1983, 46, p 34.Google Scholar
16. Lakshminarayana, B. Turbulence modelling for complex shear flows, AIAA J, 1986, 24, p 1900.Google Scholar
17. Launder, B.E. Second-moment closure: present… and future? lnt J Heat Fluid Flow, 1989, 10, p 282.Google Scholar
18. Lumley, J.L. Some comments on turbulence, Phys Fluids A, 1992, 4, p203.Google Scholar
19. Chen, F., Liu, C.F. and Yang, J.Y. Supersonic flow in the second throat ejector diffuser system, J Spacecr Rocket, 1994, 31, p 123.Google Scholar
20. Liu, C.F. and Chen, F. Analysis of performance of the second-throat ejector-diffuser, J Chinese Soc Mech Eng, 1992, 13, p 478.Google Scholar