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