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Heat Transfer Research
インパクトファクター: 0.404 5年インパクトファクター: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN 印刷: 1064-2285
ISSN オンライン: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.2018025718
pages 993-1006

NUMERICAL INVESTIGATION OF FILM COOLING SUBJECT TO BULK FLOW PULSATIONS

Mostafa A. H. Abdelmohimen
College of Engineering, King Khalid University, Saudi Arabia; Shoubra Faculty of Engineering, Benha University, Egypt

要約

One of the important parameters that affects the gas turbine blades film cooling is the behavior of the main flow. Due to the blade rotation, a periodical frequency is moving through the main flow. In this study, a numerical simulation is used to investigate the effect of the bulk flow pulsations on film cooling. The study is carried out on a flat plate surface with a simple cylindrical hole inclined by 30° with the direction of the main flow stream. The study is carried out at blowing ratios of 0.5, 1.0, and 2.0. The free stream Strouhal number ranged from 0 to about 0.49, and the coolant Strouhal number ranged from 0 to 4.1 compared to 0.2-6.0 for the operating turbine range. The free stream is represented by a sinusoidal profile with pulsation velocity amplitude in the free stream of ± 20% of the time-averaged free stream velocity. The realizable k-ε model is used to solve the momentum equation. A comparison with previous experimental studies is presented to verify the numerical model. The results show that the pulsating flow has a significant effect on the film cooling performance for pulsating frequency higher than 35 Hz. For pulsating frequency higher than 35 Hz, at blowing ratio 0.5, as the pulsating frequency increases, the film cooling effectiveness decreases while at blowing ratio 2.0, the film cooling effectiveness increases with increasing pulsating frequency. The reduction in the overall-time averaged film cooling effectiveness at pulsating frequency 75 Hz with blowing ratio equal to 0.5 is about 49.7% of the film cooling at zero pulsating frequency, while the increase in it at the pulsating frequency 75 Hz with blowing ratio equal to 2 is about 108%.

参考

  1. Abdelmohimen, M.A.H., Improving Film Cooling from Compound Angle Holes by Adding Secondary Holes Branched Out from the Main Holes, Heat Mass Transf., Springer, vol. 53, no. 5, pp. 1805-1815, 2017.

  2. Abdelmohimen, M.A.H., Numerical Investigation of Film Cooling from Two Rows of Holes with Anti-Vortex Holes Attached to the Upstream Row, Int. J. Eng. Tech. Innovation, vol. 5, no. 2, pp. 87-98, 2015.

  3. Abhari, R.S., Impact of Rotor-Stator Interaction on Turbine Blade Film Cooling, ASME Trans., J. Turbomachinery, vol. 118, pp. 103-113, 1996.

  4. Abhari, R.S. and Epstein, A.H., An Experimental Study of Film Cooling in a Rotating Transonic Turbine, ASME Trans., J. Turbomachinery, vol. 16, pp. 63-70, 1994.

  5. Bell, C.M., Ligrani, P.M., Hull, W.A., and Norton, C.M., Film Cooling Subject to Bulk Flow Pulsations: Effects of Blowing Ratio, Free Stream Velocity, and Pulsation Frequency, Int. J. Heat Mass Transf., vol. 42, pp. 4333-4344, 1999.

  6. Dhungel, A., Lu, Y., Phillips, W., Ekkad, S.V., and Heidmann, J., Film Cooling from a Row of Holes Supplemented with Anti-Vortex Holes, J. Turbomachinery, vol. 131, pp. 021007-021010, 2009.

  7. Doorly, D.J. and Oldfield, M.L.J., Simulation of the Effects of Shock Wave Passing on a Turbine Rotor Blade, ASME Trans., J. Eng. Gas Turbines Power, vol. 107, pp. 998-1006, 1985.

  8. Garg, V.K. and Abhari, R.S., Comparison of Predicted and Experimental Nusselt Number for a Film-Cooled Rotating Blade, Int. Gas Turbine and Aeroengine Congress and Exposition, Paper No. 96-GT-223, Birmingham, 1996.

  9. Johnson, B., Tian, W., Zhang, K., and Hu, H., An Experimental Study of Density Ratio Effects on the Film Cooling Injection from Discrete Holes by Using PIV and PSP Techniques, Int. J. Heat Mass Transf., vol. 76, pp. 337-349, 2014.

  10. Johnson, B., Zhang, K., Tian, W., and Hu, H., An Experimental Study of Film Cooling Effectiveness by Using PIV and PSP Techniques, AIAA 2013-0603, 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine, Texas, January 7-10, 2013.

  11. Juhany, K.A. and Hunt, M.L., Flowfield Measurements in Supersonic Film Cooling Including Effect of Shock-Wave Interaction, AIAA J, vol. 32, pp. 578-585, 1994.

  12. Kanda, T., Ono, F., Takahashi, M., and Saito, T., Wakamatsu Y., Experimental Studies of Supersonic Film Cooling with Shock Wave Interaction, AIAA J., vol. 34, pp. 265-271, 1996.

  13. Lawson, S.A. and Thole, K.A., Effects of Simulated Particle Deposition of Film Cooling, J. Turbomachinery, vol. 133, pp. 021009-1-021009-9, 2011.

  14. Lee, J.S. and Jung, I.S., Effect of Bulk Flow Pulsations on Film Cooling with Compound Angle Holes, Int. J. Heat Mass Transf., vol. 45, pp. 113-123, 2002.

  15. Ligrani, P.M. and Bell, C.M., Film Cooling Subject to Bulk Flow Pulsations: Effects of Density Ratio, Hole Length-to-Diameter Ratio, and Pulsation Frequency, Int. J. Heat Mass Transf., vol. 44, pp. 2005-2009, 2001.

  16. Ligrani, P.M., Gong, R., Cuthrell, J.M., and Lee, J.S., Bulk Flow Pulsations and Film Cooling—II. Flow Structure and Film Effectiveness, Int. J. Heat Mass Transf., vol. 39, no. 11, pp. 2283-2292, 1996a.

  17. Ligrani, P.M., Gong, R., Cuthrell, J.M., and Lee, J.S., Bulk Flow Pulsations and Film Cooling—I. Injectant Behavior, Int. J. Heat Mass Transf., vol. 39, no. 11, pp. 2271-2282, 1996b.

  18. Rigby, M.J., Johnson, A.B., and Oldfield, M.L.G., Gas Turbine Rotor Blade Film Cooling with and without Simulated NGV Shock Waves and Wakes, in Int. Gas Turbine and Aeroengine Congress and Exposition, Paper No. 90-GT-78, Brussels, 1990.

  19. Seo, H.J., Lee, J.S., and Ligrani, P.M., Effects of Bulk Flow Pulsations on Film Cooling from Different Length Injection Holes at Different Blowing Ratios, in Int. Gas Turbine and Aeroengine Congress and Exposition, Paper No. 98-GT-192, Stockholm, 1998.


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