NDLI: Film Cooling Performance in a Simulated Turbine Blade Tip Geometry

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Jae, H. Yoon Ricardo, F. Martinez-Botas
Copyright Year	2005
Abstract	One of the most problematic areas in gas turbine engines is the blade tip region, especially near the trailing edge, where it is very difficult to provide sufficient cooling. In all configurations with unshrouded tips, a clearance gap exists between the turbine blade and the outer shroud. The pressure difference between the suction and pressure sides of the blade drives a sink-like flow through this gap. The combination of leakage flow from the freestream and coolant flow induces high convective heat transfer coefficients on the blade tip surface. The resultant thermal loading can be significant and detrimental to the turbine blade tip durability, leading to early failure. Film cooling can be provided by means of a series of holes located on the tip itself providing protection not dissimilar to film cooling of the main blade. However, the interaction of coolant and the separation bubble resulted in a significantly different film cooling performance to that of non-tip cases. An experimental investigation of the simulated turbine blade tip is presented in here. The first section discusses PIV flow field measurements, the second covers the measurement of film cooling effectiveness and the third heat transfer measurements. All three parts investigate the effect of using different film cooling injection points and blowing ratios for injection on the blade tip itself, close to the pressure surface corner. Additionally, the effect of varying the corner radii between the pressure surface and the tip is reported. The experimental method uses the steady state liquid crystal technique. A Reynolds number of 30,000 based on the clearance gap hydraulic diameter for the main flow was used.
Sponsorship	International Gas Turbine Institute
Starting Page	739
Ending Page	754
Page Count	16
File Format	PDF
ISBN	0791847268
DOI	10.1115/GT2005-68863
e-ISBN	0791837548
Volume Number	Volume 3: Turbo Expo 2005, Parts A and B
Conference Proceedings	ASME Turbo Expo 2005: Power for Land, Sea, and Air
Language	English
Publisher Date	2005-06-06
Publisher Place	Reno, Nevada, USA
Access Restriction	Subscribed
Subject Keyword	Suction Turbine blades Cooling Blades Reynolds number Clearances (engineering) Durability Separation (technology) Flow (dynamics) Pressure Liquid crystals Steady state Convection Geometry Bubbles Gas turbines Coolants Film cooling Leakage flows Corners (structural elements) Failure Heat transfer
Content Type	Text
Resource Type	Article

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