Aerodynamic and thermal performance of a three dimensional annular transonic nozzle guide vane
Author:
Affiliation:
1. Von Karman Inst. for Fluid Dynamics, Rhode-Saint-Genese, Belgium
2. SNECMA, Moissy-Cramayel, France
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1994-2929
Reference13 articles.
1. Behavior of a Coolant Film With Two Rows of Holes Along the Pressure Side of a High-Pressure Nozzle Guide Vane
2. Aero-Thermal Performance of a Two-Dimensional Highly Loaded Transonic Turbine Nozzle Guide Vane: A Test Case for Inviscid and Viscous Flow Computations
3. Consigny,H.&Richards, B.E., 1982,"Shortduration measurementsof heat transfer rate to a gas turbine rotor blade",IofEngineeringforPower,Vol 104,pp 542-551 - Table.1:Hub and TipEndwallVelocityDistributions
4. Dunn, M.G., 1985, " Heat flux measurcments and analysis for a rotating turbine stage", AGARD CP 390, "HeatTransfcrand Coolingin GasTurbines"
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