THERMAL SCIENCE

International Scientific Journal

Authors of this Paper

External Links

INFLUENCE OF DEFLECTION HOLE ANGLE ON EFFUSION COOLING IN A REAL COMBUSTION CHAMBER CONDITION

ABSTRACT
Fluid-solid coupling simulation is conducted to investigate the performance of effusion cooling in the real combustion chamber condition of strong rotation and primary holes. The wall temperature and film cooling effectiveness of different deflection angle is analyzed. From the results, it is concluded that the performance of effusion is better than conventional film cooling. The wall temperature and gradient is lower, the cooling efficiency is higher and the coolant is reduced by 20%, but pressure loss is slightly increased. The cooling effectiveness decreases behind primary holes because of local combustion. Comparison with the effect of deflection angle, the cooling performance of 60 deg deflection angle is best. The coolant is better attached to the wall downstream when the deflection angle is same as the rotating mainstream. In addition, the effect of deflection angle is not so significant on the coolant flow rate, but a large negative impact on the pressure loss. Although the cooling effectiveness of 60 deg deflection angle is highest, the total pressure recovery coefficient is lower. The maximum temperature drops about 70K and the outlet temperature distribution trends more consistent. So various factors should be taken into consideration when designing of deflection angle.
KEYWORDS
PAPER SUBMITTED: 2014-01-07
PAPER REVISED: 2014-02-27
PAPER ACCEPTED: 2014-03-08
PUBLISHED ONLINE: 2014-04-05
DOI REFERENCE: https://doi.org/10.2298/TSCI140107043L
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2015, VOLUME 19, ISSUE 2, PAGES [645 - 656]
REFERENCES
  1. Lefebvre, A. H., Ballal, D. R., Bahr, D. W., Gas turbine combustion: alternative fuels and emissions, Boca Raton, FL: CRC Press, 2010
  2. Li, L., Peng, X. F., Liu, T., Combustion and cooling performance in an aero-engine annular combustor, Applied thermal engineering, 26 (2006), 16, pp. 1771-1779
  3. Ali, A. B. S., Kriaa, W., Mhiri, H., Numerical investigations of cooling holes system role in the protection of the walls of a gas turbine combustion chamber, Heat and Mass Transfer, 48 (2012), 5, pp. 779-788
  4. Yu, Z., Xu, T., Li, J., Comparison of a series of double chamber models with various hole angles for enhancing cooling effectiveness, International Communications in Heat and Mass Transfer, 44 (2013), pp. 38-44
  5. Andrews, G. E., Asere, A. A., Gupta, M. L., Full coverage discrete hole film cooling- The influence of hole size, International Journal of Turbo and Jet-Engines, 2 (1985), 3, pp. 213-225
  6. Andrews, G. E., Hussain, I., Small diameter film cooling holes: the influence of hole size and pitch, International Journal of Turbo and Jet Engines, 5 (1988), 1-4, pp. 61-72
  7. Andrews, G. E., Gupta, M. L., Mkpadi, M. C., Full Coverage Discrete Hole Film Cooling: Cooling Effectiveness, International Journal of Turbo and Jet-Engines, 2 (1985), 3, pp. 199-212
  8. Lin, Y., Song, B., Li, B., Investigation of film cooling effectiveness of full-coverage inclined multihole walls with different hole arrangements, Proceedings, ASME Turbo Expo 2003: Power for Land, Sea, and Air, Atlanta, Georgia, USA, 2003, Vol. 5, pp. 651-660
  9. Zhang, C., Lin, Y., Xu, Q., Cooling effectiveness of effusion walls with deflection hole angles measured by infrared imaging, Applied Thermal Engineering, 29 (2009), 5, pp. 966-972
  10. Lin, Y., Song, B., Li, B., Measured film cooling effectiveness of three multihole patterns, Journal of heat transfer, 128 (2006), 2, pp. 192-197
  11. Scrittore, J. J., Thole, K. A., Burd, S. W., Experimental characterization of film-cooling effectiveness near combustor dilution holes, Proceedings, ASME Turbo Expo 2005: Power for Land, Sea, and Air, Reno, Nevada, USA, 2005, Vol. 3, pp. 1339-1347
  12. Scrittore, J. J., Thole, K. A., Burd, S. W., Investigation of velocity profiles for effusion cooling of a combustor liner, Journal of turbomachinery, 129 (2007), 3, pp. 518-526
  13. Goldstein, R. J., Jin, P., Film cooling downstream of a row of discrete holes with compound angle, Journal of turbomachinery, 123 (2001), 2, pp. 222-230
  14. Ling, J. C. P. W., Ireland, P. T., Tumer, L., Full Coverage Film Cooling for Combustor Transition Sections, Proceedings, ASME Turbo Expo 2002: Power for Land, Sea, and Air, Amsterdam, The Netherlands, 2002, Vol. 3, pp. 1011-1021
  15. Gustafsson, K. M., Johansson, T. G., An experimental study of surface temperature distribution on effusion-cooled plates, Journal of engineering for gas turbines and power, 123 (2001), 2, pp. 308-316
  16. Yang, C., Zhang, J., Influence of Multi-hole Arrangement on Cooling Film Development, Chinese Journal of Aeronautics, 25 (2012), 2, pp. 182-188
  17. Harrington, M. K., McWaters, M. A., Bogard, D. G., Full-coverage film cooling with short normal injection holes, Journal of turbomachinery, 123 (2001), 4, pp. 798-805
  18. Tarchi, L., Facchini, B., Maiuolo, F., Experimental investigation on the effects of a large recirculating area on the performance of an effusion cooled combustor liner, Journal of engineering for gas turbines and power, 134 (2012), 4
  19. Rohani, B., Saqr, K. M., Effects of hydrogen addition on the structure and pollutant emissions of a turbulent unconfined swirling flame, International Communications in Heat and Mass Transfer,39 (2012), 5, pp. 681-688
  20. Zeinivand, H., Bazdidi-Tehrani, F., Influence of stabilizer jets on combustion characteristics and NOx emission in a jet-stabilized combustor, Applied Energy, 92 (2012), pp. 348-360
  21. Murthy, J. Y., Mathur, S. R., Finite volume method for radiative heat transfer using unstructured meshes, Journal of thermophysics and heat transfer, 12 (1998), 3, pp. 313-321
  22. Dang, X. X., Experimental Investigation and Numerical Simulation of A Gas Turbine Annular Combustor with Dual-stage Swirler, Ph.D. thesis, Nanjing University of Aeronautics and Astronautics, Nanjing , China, 2009

© 2020 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence