INVESTIGATION ON THE PRESSURE MATCHING PERFORMANCE OF THE CONSTANT AREA SUPERSONIC-SUPERSONIC EJECTOR

Abstract

The pressure matching performance of the constant area supersonic-supersonic ejector has been studied by varying the primary and secondary Mach numbers. The effect of the primary fluid injection configurations in ejector, namely peripheral and central, has been investigated as well. Schlieren pictures of flow structure in the former part of the mixing duct with different stagnation pressure ratio of the primary and secondary flows have been taken. Pressure ratios of the primary and secondary flows at the limiting condition have been obtained from the results of pressure and optical measurements. Additionally, a computational fluid dynamics analysis has been performed to clarify the physical meaning of the pressure matching performance diagram of the ejector. The obtained results show that the pressure matching performance of the constant area supersonic-supersonic ejector increases with the increase of the secondary Mach number, and the performance decreases slightly with the increase of the primary Mach number. The phenomenon of boundary layer separation induced by shock wave results in weaker pressure matching performance of the central ejector than that of the peripheral one. Furthermore, based on the observations of the experiment, a simplified analytical model has been proposed to predict the limiting pressure ratio, and the predicted values obtained by this model agree well with the experimental data.

Keywords

Dates

  • Submission Date2012-04-05
  • Revision Date2012-05-12
  • Acceptance Date2012-05-13

DOI Reference

10.2298/TSCI120405114C

References

  1. Kumaran, R. M., et al., Optimization of Second Throat Ejectors for High-Altitude Test Facility, Journal of Propulsion and Power, 25(2009), 3, pp. 697-706
  2. Nelson, K. W., Experimental Investigation of an Ejector Scramjet RBCC at Mach 4.0 and 6.5 Simulated Flight Conditions, Ph. D. thesis, The University of Alabama in Huntsville, Huntsville, USA, 2002
  3. Zhu, Y. H., et al., Numerical Investigation of Geometry Parameters for Design of High Performance Ejectors. Applied Thermal Engineering, 29(2009), pp. 898-905
  4. Singhal, G., et al., Pressure Recovery Studies on a Supersonic COIL With Central Ejector Configuration, Optics & Laser Technology, 42(2010), pp.1145-1153
  5. Shwartz, J., Gerald, T. W., Joel, M. A., Tactical High-Energy laser. Proceedings (Basu, S., Riker, J. F.), Laser and Beam Control Technologies, San Jose, USA, 2002, Vol 4632, pp. 10-20
  6. Zimet, E., Steady State and Transient Operation of an Ejector for a Chemical Laser Cold Flow Mixing Experiment, Report No. TR 76-142, White Oak Laboratory, MD., USA, 1976
  7. Guile, R. N., US Patent, 4 379 679, 1983
  8. Mikkelsen, C. D., Sandberg, M. R., Addy, A. L., Theoretical and Experimental Analysis of the Constant-Area, Supersonic-Supersonic Ejector. Report No. UILU-ENG-76-4003. University of Illinois at Urbana-Champaign, IL., USA, 1976
  9. Dutton, J. C., Mikkelsen, C. D., Addy, A. L., A Theoretical and Experimental Investigation of the Constant Area, Supersonic-Supersonic Ejector, AIAA Journal, 20(1982), 10, pp. 1392-1400
  10. Dvorak, V., Safarik, P., Supersonic Flow Structure in the Entrance Part of a Mixing Chamber of 2D Model Ejector. Journal of the Thermal Science, 12(2003), 4, pp. 344-349
  11. Dvorak, V., Safarik, P., Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector, Journal of Thermal Science, 14(2005), 3, pp. 258-271
  12. Fluent Inc., Fluent 6.3 User's Guide, 2006
  13. Bartosiewicz, Y., et al., Numerical and Experimental Investigations on Supersonic Ejectors, International Journal of Heat and Fluid Flow, 26(2005), pp. 56-70
  14. Sriveerakul, T., Aphornratana, S., Chunnanond, K., Performance Prediction of Steam Ejector Using Computational Fluid Dynamics: Part 1. Validation of the CFD Results, International Journal of Thermal Sciences, 46(2007), pp. 812-822