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RISTurbine Blade Platform Film Cooling With Simulated Swirl Purge Flow and Slashface Leakage Conditions
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The combined effects of inlet purge flow and the slashface leakage flow on the film cooling effectiveness of a turbine blade platform were studied using the pressure-sensitive paint (PSP) technique. Detailed film cooling ...
Turbine Blade Leading Edge Cooling With One Row of Normal or Tangential Impinging Jets
Publisher: The American Society of Mechanical Engineers (ASME)
Influence of Turbine Blade Leading Edge Profile on Film Cooling With Shaped Holes
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: This paper presents the turbine blade leading edge model film cooling effectiveness with shaped holes, using the pressure sensitive paint (PSP) mass transfer analogy method. The effects of leading edge profile, coolant to ...
Turbine Blade Platform Film Cooling With Fan-Shaped Holes Under Simulated Swirl Purge Flow and Slashface Leakage Conditions
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The combined effects of upstream purge flow, slashface leakage flow, and discrete hole film cooling on turbine blade platform film cooling effectiveness were studied using the pressure sensitive paint (PSP) technique. As ...
Full Scale Turbine Vane Endwall Film Cooling Effectiveness Distribution Using Pressure Sensitive Paint Technique
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Researchers in gas turbine field take great interest in the cooling performance on the firststage vane because of the complex flow characteristics and intensive heat load that comes from the exit of the combustion chamber. ...
Heat Transfer in a Rotating Cooling Channel (AR = 2:1) With Rib Turbulators and a Tip Turning Vane
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Experimental investigation on rotation and turning vane effects on heat transfer was performed in a two-pass rectangular internal cooling channel. The channel has an aspect ratio of AR = 2:1 and a 180 deg tip-turn, which ...
Film Cooling Effectiveness Comparison on Full-Scale Turbine Vane Endwalls Using Pressure-Sensitive Paint Technique
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Turbine vane endwalls are highly susceptible to intensive heat load due to their large exposed area and complex flow field especially for the first stage of the vane. Therefore, a suitable film cooling design that properly ...
Heat Transfer in a Rotating Two-Pass Rectangular Channel Featuring Reduced Cross-Sectional Area After Tip Turn (Aspect Ratio = 4:1 to 2:1) With Profiled 60 deg Angled Ribs
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The present study features a two-pass rectangular channel with an aspect ratio (AR) = 4:1 in the first pass and an AR = 2:1 in the second pass after a 180-deg tip turn. In addition to the smooth-wall case, ribs with a ...
Heat Transfer in a Rotating Two-Pass Rectangular Channel Featuring a Converging Tip Turn With Various 45 deg Rib Coverage Designs
Publisher: American Society of Mechanical Engineers (ASME)
Abstract: Varying aspect ratio (AR) channels are found in modern gas turbine airfoils for internal cooling purposes. Corresponding experimental data are needed in understanding and assisting the design of advanced cooling systems. ...
Effect of 45-deg Rib Orientations on Heat Transfer in a Rotating Two-Pass Channel With Aspect Ratio from 4:1 to 2:1
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The internal cooling passages of gas turbine blades mostly have varying aspect ratios from one passage to another. However, there are limited data available in the open literature that used a reduced cross section and ...