Accession Number : ADA138794
Title : Film Cooling on a Gas Turbine Blade Near the End Wall.
Descriptive Note : Interim rept.,
Corporate Author : MINNESOTA UNIV MINNEAPOLIS DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Goldstein,R J ; Chen,H P
PDF Url : ADA138794
Report Date : May 1983
Pagination or Media Count : 10
Abstract : Local film cooling effectiveness on a gas turbine blade with a row of discrete cooling jets was measured using a mass transfer technique. Emphasis is placed on phenomena near the end wall of the blade. This region contains a horseshoe vortex system modified by a passage vortex. On the concave (pressure) surface the film cooling performance is not greatly altered by the presence of the end wall. On the convex surface of the blade the film cooling is essentially absent in a triangular region extending from near the region of peak curvature on the blade to its trailing edge. This unprotected region closely corresponds to location of the passage vortex as indicated by flow visualization. The passage vortex sweeps away the injected coolant flow from the surface. Upstream of the unprotected area the injected flow is skewed toward the middle span of the blade. End wall influence extends about one-half cord length up from the end wall in the present experiments.
Descriptors : *Film cooling, *Gas turbine blades, Walls, Vortices, Heat transfer, Surfaces, Curved profiles, Coolants, Injection, Jet flow, Internal
Subject Categories : Thermodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE