Accession Number : AD0481393
Title : DESIGN PROCEDURE FOR TRANSPIRATION AIR COOLED TURBINE BLADES
Descriptive Note : Supplement to Final rept.
Corporate Author : CURTISS-WRIGHT CORP QUEHANNA PA
Personal Author(s) : Lang, R ; Lloyd, Wallis
PDF Url : AD0481393
Report Date : 15 Oct 1958
Pagination or Media Count : 30
Abstract : The calculation procedure for determining the coolant flow required to maintain a given wall temperature in transpiration-cooled turbine blades is presented. The basic method has evolved from numerous modifications based upon the experience acquired during testing and evaluation of transpiration cooled configurations. The theory supporting the equations is included. The calculation procedure presented has been tried and prove to be a useful tool. It is believed that continued testing will further the understanding of the influence of turbulent flow on the aerodynamic and heat transfer characteristics of this type of cooling. With refinement of the theoretical approach, improvement in the design procedure can be realized. In order that potentially feasible configurations can be evaluated quickly and economically, the calculation method has been programmed for the IBM 704 digital computer. A brief description of the methods of preparing input data for the machine and of the operation sequence employed by the machine is also included.
Descriptors : *GAS TURBINE BLADES, AERODYNAMIC CHARACTERISTICS, AIR COOLED, COMPUTER PROGRAMMING, CONFIGURATIONS, EVAPOTRANSPIRATION, FEASIBILITY STUDIES, GAS FLOW, HEAT TRANSFER, LAMINAR FLOW, ROTOR BLADES(TURBOMACHINERY), SWEAT COOLING, THERMAL CONDUCTIVITY, THERMAL RADIATION, TURBULENCE, VELOCITY
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE