Accession Number : AD0762527
Title : Heat Transfer Investigation for Multihole Aircraft Turbine Blade Cooling.
Descriptive Note : Final technical rept. 1 May 72-28 Feb 73,
Corporate Author : PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
Personal Author(s) : Mayle,R. E. ; Camarata,F. J.
Report Date : JUN 1973
Pagination or Media Count : 76
Abstract : Adiabatic film effectiveness and heat transfer measurements with injection of coolant air through arrays of holes in a flat plate into a uniformly moving mainstream are presented. Measurements were taken both within and downstream of the multihole pattern. The hole configurations considered are regular patterns of staggered holes. The holes are angled 30 degrees to the plate's surface with the projection of the hole axis on the surface forming a 45 degree angle to the mainstream. A semi-empirical relation for the adiabatic film effectiveness is presented. Also an empirical correlation of the Stanton number is presented for flow conditions where the coolant flow dominates the fluid mechanics near the surface. (Author)
Descriptors : (*GAS TURBINE BLADES, COOLING), (*TURBOJET INLETS, COOLING), TURBOJET ENGINES, FILM COOLING, CONVECTION(HEAT TRANSFER), CASCADE STRUCTURES, FLOW FIELDS, FLOW VISUALIZATION, NUMERICAL ANALYSIS
Subject Categories : Thermodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE