Affiliation:
1. e-mail:
2. Stanford University, Stanford, CA 94305
3. US Military Academy, West Point, New York 10996
Abstract
Measurements of the 3D velocity and concentration fields were obtained using magnetic resonance imaging for a pressure-side cutback film cooling experiment. The cutback geometry consisted of rectangular slots separated by straight lands; inside each of the slots was an airfoil-shaped blockage. The results from this trailing edge configuration, the “island airfoil,” are compared to the results obtained with the “generic airfoil,” a geometry with narrower slots, wider, tapered lands, and no blockages. The objective was to determine how the narrower lands and internal blockages affected the average film cooling effectiveness and the spanwise uniformity. Velocimetry data revealed that strong horseshoe vortices formed around the blockages in the slots, which resulted in greater coolant nonuniformity on the airfoil breakout surface and in the wake. The thinner lands of the island airfoil allowed the coolant to cover a larger fraction of the trailing edge span, giving a much higher spanwise-averaged surface effectiveness, especially near the slot exit where the generic airfoil lands are widest.
Reference21 articles.
1. Holloway, D., Leylek, J., and Buck, F., 2002, “Pressure-Side Bleed Film Cooling: Part I—Steady Framework for Experimental and Computational Results,” ASME Turbo Expo, June 3, ASME Paper No. GT2002-30471.10.1115/GT2002-30471
2. Holloway, D., Leylek, J., and Buck, F., 2002, “Pressure-Side Bleed Film Cooling: Part II—Unsteady Framework for Experimental and Computational Results,” ASME Turbo Expo, June 3, ASME Paper No. GT2002-30472. 10.1115/GT2002-30472
3. Experimental and Numerical Investigation of Trailing Edge Film Cooling by Circular Coolant Wall Jets Ejected From a Slot With Internal Rib Arrays;ASME J. Turbomach.,2004
4. Simulation of Turbine Blade Trailing Edge Cooling;ASME J. Fluid. Eng.,2009
5. Detached Eddy Simulation of Film Cooling Performance on the Trailing Edge Cutback of Gas Turbine Airfoils;ASME J. Turbomach.,2006
Cited by
13 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献