ABSTRACT
Effect of film hole diameter to discharge coefficients and film cooling effectiveness of the lamilloy were experimentally investigated at the blowing ratios ranging from 0.6 to 2.5. Generally, the cooling effectiveness on the test surface is increased with the film hole diameters and blowing ratios increasing, and the variation tendency along the streamwise through the centerline of film holes also keeps consistent. In the upstream, all configurations have a relatively lower cooling effectiveness, however, with the flows to the downstream, cooling effectiveness grows gradually, and the peak values of effectiveness appeared periodically, the position matches the film hole positions. Besides, between the film holes, fluctuation exists simultaneously. By comparison, the cooling effectiveness and discharge coefficients are both increased with the blowing ratio with same film hole diameters, Moreover, under the same blowing ratios, the cooling effectiveness and discharge coefficients are getting higher when hole diameters increase.
KEYWORDS
PAPER SUBMITTED: 2019-05-28
PAPER REVISED: 2019-08-28
PAPER ACCEPTED: 2019-09-01
PUBLISHED ONLINE: 2020-02-15
THERMAL SCIENCE YEAR
2020, VOLUME
24, ISSUE
Issue 3, PAGES [1835 - 1843]
- Ashmole, P.J. Rolls-Royce Limited, East Kilbride. Introduction the Rolls-Royce Tay. AIAA/SAE/ASME 19th Joint Propulsion Conference. Washington, 1983, 1-12.
- Nealy, D.A., Reider, S.B. Evaluation of Laminated Porous Wall Materials for Combustor Liner Cooling. Transactions of the ASME. Journal of engineering for Power.1978, 79-GT-100, 268-276.
- Vajravelu, K., Li, R., Effects of Second-Order Slip and Drag Reduction in Boundary Layer Flows. Applied Mathematics & Nonlinear Sciences, 2018, 3(1): 291-302.
- Caraballo, T., Herrera-Cobos, M., Marín-Rubio, P. An Iterative Method for Non-autonomous Nonlocal Reaction-diffusion Equations. Applied Mathematics & Nonlinear Sciences, 2017, 2(1): 73-82.
- Wassell, A.B., Bhangu, J.K. The Development and Application of Improved Combustor Wall Cooling Techniques. ASME, 80-GT-66, 1980.
- Sweeney, P.C., Rhodes, J.F. An Infrared Technique for Evaluating Turbine Airfoil Cooling Designs, ASMS. Journal of Turbomachinery, 2001, 122: 170-177.
- Kong, M.Z., Zhu, H.R., Liu, S.L., Yuan, H.P. Research on Heat Transfer Characteristics of Lamilloy Internal Surfaces Using Transient Liquid Crystal Technique. Journal of Aerospace Power, 2009, 24(2): 340-346.
- Funazaki, K., Tarukawa, T., Kudo, T. Heat Transfer Characteristics of an Integrated Cooling Configuration of Ultra-High Temperature Turbine Blades, Experimental and Numerical Investigations, 2001-UT-0148, 185-192.
- Funazaki, K., Hachlya, K. Systematic Numerical Studies on Heat Transfer and Aerodynamic Characteristics of Impingement Cooling Devices Combined with Pins, 2003-UT-38256, 185-192
- Wu, H.L., Peng, X.F. Transpiration Cooling Using Porous Triple-Laminated Plates//ASME 2003 Heat Transfer Summer Conference. 2003: 735-740.
- Zhang, B., Dou, Y.Y., Hong, Q., Ji, H.H. Numerical Investigation of Flow and Heat Transfer Characteristics in Plate with Multiple Incline Stage Holes, Tehnički vjesnik 26, 2,2019, 471-477
- Andrews, G.E., Hussain, C. I. Enhanced Impingement Heat Transfer: The Influence of Impingement X/D for Interrupted Rib Obstacles (Rectangular Pin Fins), Journal of Turbomachinery, ASME APRIL 2006, Vol. 128/321