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Experimental Investigation of Film Cooling Flow Induced by Shaped Holes on a Turbine Blade
Author(s) -
BARTHET Sylvain,
BARIO François
Publication year - 2001
Publication title -
annals of the new york academy of sciences
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.712
H-Index - 248
eISSN - 1749-6632
pISSN - 0077-8923
DOI - 10.1111/j.1749-6632.2001.tb05865.x
Subject(s) - blade (archaeology) , turbine blade , materials science , mechanics , flow (mathematics) , turbine , mechanical engineering , physics , engineering
A bstract : The present study is the second half of a piece of work carried out in collaboration with SNECMA. It investigates shaped hole film cooling, numerically and experimentally. The aim of this paper is the experimental analysis of shaped hole film cooling on a large scale turbine blade (1.4 m chord). The test section is a large scale turbine inlet guide vane cascade. The test airfoil is equipped with a row of nine 50° sloped shaped holes. They are located on the suction side at 20% of the curvilinear length of the blade from the stagnation point. The inlet film cooling hole diameter is 12 mm. The test jet flow is heated to 55°C above the crossflow temperature. Velocity and temperature field measurements have been done to obtain mean and fluctuating values. The results are compared to those obtained by Béral1 on the same experimental apparatus and in the same test conditions, for a row of cylindrical holes.