THERMAL SCIENCE

International Scientific Journal

Thermal Science - Online First

External Links

online first only

Numerical investigation of heat transfer in film layer under supersonic consition of convergent-divergent transition

ABSTRACT
The distribution of film cooling effectiveness in supersonic mainstream of circle-rectangular Convergent-Divergent transition has been numerically investigated under different pressure ratios. The shock wave exerted superior influence on film cooling. In supersonic main flow, extra compression waves formed in upstream of the film holes, resulted by the obstruction of the multiple cooling jets. This exerted extra pressure to the boundary layer, induced adverse pressure gradient, and led to weakening of the film flow attachment ability and decreasing of local cooling effectiveness. Bow oblique shock wave occurred in front of holes, the two oblique bow shaped low pressure zones formed on both sides of the hole, and low cooling effectiveness zones appeared accordingly. The inefficient region at the leading edge of the hole destroyed the film developing between holes, decreased the cooling effectiveness accumulation in the rear part. The decrease of hole incline angle caused an increase of cooling effectiveness, which reduced reverse velocity gradient caused by shock wave in the boundary layer and improved film attachment. The influence of main flow pressure ratio to film cooling was also investigated, and found with increasing of the ratio, the influence will became even significant.
KEYWORDS
PAPER SUBMITTED: 2019-04-01
PAPER REVISED: 2019-07-19
PAPER ACCEPTED: 2019-07-22
PUBLISHED ONLINE: 2019-08-10
DOI REFERENCE: https://doi.org/10.2298/TSCI190401310Z
REFERENCES
  1. Bertin, J. J., Hypersonic Aerothermodynamics, American Institute of Aeronautics and Astronautics, Inc, New York, USA, 1994.
  2. Saunders, O. A, Calder, P. H., Heat Transfer in a Nozzle at Supersonic Speeds, Proceedings of the Institution of Mechanical Engineers, Part B: Management and engineering manufacture, 1(1953), 12, pp. 232-239.
  3. Adamson, Jr. T.C., On the structure of jets from highly underexpanded nozzles into still air, Journal of the Aerospace sciences, 26(1959), 1, pp. 16-24.
  4. Carlson, D. J., C. H. Lewis, Normal shock location in underexpanded gas and gas-particle jets, AIAA Journal, 2 (1964), 4, pp.776-777.
  5. Holden, Michael, S., Experimental studies of shock wave-boundary layer interaction, In Von Karman Inst. for Fluid Dyn, Laminar and Turbulent Separation Including 3-Dimensional Effects 90 p (SEE N79-22422 13-34), 1974.
  6. Sandham, N. D., et al., Transitional shock-wave/boundary-layer interactions in hypersonic flow, Journal of Fluid Mechanics, 752(2014), pp. 349-382.
  7. Shimshi, E. , et al., Viscous simulation of shock-reflection hysteresis in overexpanded planar nozzles. Journal of Fluid Mechanics, 635(2009), pp. 189-206.
  8. HOLDEN M., Rodriguez K., Nowak R., et al. Experimental studies of shock wave/wall jet interaction in hypersonic flow//28th Aerospace Sciences Meeting. 1994: 607.
  9. Zaman, K., Bencic, T. J., Fagan, A F, et al., Shock-Induced Boundary-Layer Separation in Round Convergent-Divergent Nozzles, AIAA Journal, 54(2015), 2, pp. 434-442.
  10. Johnson, A. D., Papamoschou, D. Instability of shock-induced nozzle flow separation. Physics of Fluids, 22(2010), 1, pp. 016102.
  11. Kanda, T., Ono, F., Experimental studies of supersonic film cooling with shock wave interaction (II), Journal of thermophysics and heat transfer, 11(1997), 4, pp. 590-592.
  12. Ligrani, P. M., Saumweber C., Schulz A, et al., Shock wave-film cooling interactions in transonic flows//ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001: V003T01A019-V003T01A019.
  13. Juhany, K. A., Hunt, M. L., Sivo, J. M., Influence of injectant Mach number and temperature on supersonic film cooling, Journal of thermophysics and heat transfer, 8(1994), 1, pp. 59-67.
  14. O'CONNOR, J P., Haji-Sheikh, A., Numerical study of film cooling in supersonic flow, AIAA journal, 30(1992), 10, pp. 2426-2433.
  15. Takita K., Masuya G., Effects of combustion and shock impingement on supersonic film cooling by hydrogen, AIAA journal, 38(2000), 10, pp. 1899-1906.
  16. Back, L. H., Gier, H. L., Massier, P F. Comparison of measured and predicted flows through conical supersonic nozzles, with emphasis on the transonic region, AIAA Journal, 3(1965), 9, pp. 1606-1614.
  17. Aupoix, B., Mignosi, A., Viala, S., et al., Experimental and numerical study of supersonic film cooling, AIAA journal, 36(1998), 6, pp. 915-923.
  18. OLSEN, GEORGE, et al., Experimental results for film cooling in 2-d supersonic flow including coolant delivery pressure, geometry, and incident shock effects, 28th Aerospace Sciences Meeting, 1990.
  19. Dutton, J. C. Swirling supersonic nozzle flow, Journal of Propulsion and Power, 3(1987), 4, pp. 342-349.
  20. Peng, W., Sun, X., Jiang, P., et al., Effect of continuous or discrete shock wave generators on supersonic film cooling, International Journal of Heat and Mass Transfer, 108 (2017), pp. 770-783.