Accession Number : ADA261849


Title :   Heat Transfer and Aerodynamics of a 3D Design Nozzle Guide Vane Tested in the Pyestock Isentropic Light Piston Facility


Descriptive Note : Technical memorandum


Corporate Author : DEFENCE RESEARCH AGENCY FARNBOROUGH (UNITED KINGDOM)


Personal Author(s) : Chana, K S


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a261849.pdf


Report Date : Dec 1992


Pagination or Media Count : 14


Abstract : In HP turbines, predictions of the heat transfer to the blade and endwalls is particularly important for an accurate assessment of turbine component life. On the endwalls, there are often complex 3D (secondary) flows present which make predictions of heat transfer particularly difficult, A detailed investigation of this area has been carried out on a fully annular cascade of highly 3D nozzle guide vanes. Measurements were made on the vane and endwalls to determine heat transfer and aerodynamic chacteristics. Testing was conducted in a short duration Isentropic Light Piston test facility, at engine representative Reynolds number, Mach number and gas-to-wall temperature ratio. Interpreted test data are compared with computations obtained at test conditions.


Descriptors :   *GAS TURBINES , *AERODYNAMIC CHARACTERISTICS , *GAS TURBINE NOZZLES , *SECONDARY FLOW , *GUIDE VANES , HEAT TRANSFER , MEASUREMENT , SYMPOSIA , TURBINES , UNITED KINGDOM , AERODYNAMICS , TURBINE COMPONENTS , DESIGN CRITERIA , NOZZLES , PREDICTIONS , BLADES , THREE DIMENSIONAL


Subject Categories : Aerodynamics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE