Accession Number : AD0769878
Title : Investigation of Factors Affecting Heat Transfer to Turbine End Walls.
Descriptive Note : Final rept. 26 Oct 70-26 Aug 73,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB
Personal Author(s) : Louis,Jean F.
Report Date : OCT 1973
Pagination or Media Count : 43
Abstract : Short duration studies of heat transfer and film cooling effectiveness were made using a shock tunnel and a turbine blowdown facility. These facilities use the concept of short duration experiments to test turbines or turbine components under steady-state conditions which scale the metal operating temperatures down to room temperature, and subsequently scale pressures and mass flow rates so that Reynolds and Mach numbers are kept unchanged. Since the Prandtl number remains the same, the Nusselt number is also unchanged. The short operating time assures that the surfaces remain nearly isothermal and that fast instrumentation, pressure transducers and heat transfer gauges can be used to record average and unsteady pressures and heat transfer in this more amenable environment. The problem of primary concern is the heat transfer and cooling of stationary rotor shrouds (engine seals). (Modified author abstract)
Descriptors : (*Gas turbines, Heat transfer), Film cooling, Injection, Gas flow, Gas turbine rotors, Gas seals, Cooling, Shock tunnels
Subject Categories : Thermodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE