NDLI: Measurement and Modelling of Blade Tip Cooling in Gas Turbines

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Teloxa, Julio Narzary, Diganta Sierra, F. Z. Lei, Jiang Carrillo, Francisco Han, Je-Chin
Copyright Year	2013
Abstract	Blade tip cooling effectiveness simulations and measurements are reported. Measurements of metal blade surface temperature distributions were obtained in the laboratory using temperature sensitive paint technique, TSP, for mainstream Reynolds number, ReM = 200,000, and cooling Reynolds number, ReC = 10,000. The blade tip region consists of a cavity with thin walls on pressure and suction sides known as squealer rim. TSP technique is used to investigate the temperature demonstrating its applicability as cooling effectiveness measurement method on a blade tip region. Several film cooling holes placed along the airfoil camber line discharge coolant and spread over the tip cavity. Besides, conjugate cooling flow was numerically simulated, considering blade metal and mainstream contact under the effects of leakage through blade tip clearance using a finite volume program, Fluent, with good agreement between data and numerical results. Cooling effectiveness is investigated as function of blowing ratio and tip clearance.
Sponsorship	International Gas Turbine Institute
File Format	PDF
ISBN	9780791855157
DOI	10.1115/GT2013-94812
Volume Number	Volume 3B: Heat Transfer
Conference Proceedings	ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2013-06-03
Publisher Place	San Antonio, Texas, USA
Access Restriction	Subscribed
Subject Keyword	Leakage Suction Temperature distribution Temperature Cooling Blades Metals Reynolds number Clearances (engineering) Airfoils Modeling Flow (dynamics) Pressure Thin wall structures Cavities Gas turbines Simulation Coolants Engineering simulation Film cooling
Content Type	Text
Resource Type	Article

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