Accession Number : AD0758782
Title : Velocity and Heat Transfer Analysis in Channels with a Porous Wall.
Descriptive Note : Technical rept. Apr-Jun 71,
Corporate Author : AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
Personal Author(s) : Debruge,Lucien L.
Report Date : SEP 1972
Pagination or Media Count : 97
Abstract : A method of cooling turbine blades internally by continuous injection through an interior baffle is analyzed. The analytical model consists of a two-dimensional channel formed by a solid wall (blade surface) and a porous plate (injection source). Based on incompressible and laminar flow assumptions the velocity and the temperature fields are determined. The Nusselt number for a power-law surface temperature variation is obtained and expressed in terms of the Prandtl and Reynolds numbers. The related problem of cooling the turbine disc is also solved. (Author)
Descriptors : (*AXIAL FLOW COMPRESSOR BLADES, COOLING), AIR COOLED, TURBOJET ENGINES, GAS FLOW, WALLS, POROUS MATERIALS, MODEL TESTS, INCOMPRESSIBLE FLOW, LAMINAR FLOW, REYNOLDS NUMBER, SURFACE TEMPERATURE, VELOCITY
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE