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Heat Transfer Analysis Along the Blades of a Gas Turbine Stator by Thermal and Kinematic Boundary Layers Theory FREE

[+] Author Affiliations
Y. Becko

ACEC — Westinghouse Research Laboratory, Charleroi, Belgium

Paper No. 75-GT-15, pp. V01AT01A014; 9 pages
doi:10.1115/75-GT-15
From:
  • ASME 1975 International Gas Turbine Conference and Products Show
  • Volume 1A: General
  • Houston, Texas, USA, March 2–6, 1975
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7976-4
  • Copyright © 1975 by ASME

abstract

A numerical procedure is presented for the analysis of thermal and kinematic boundary layers behavior along the blades of a gas turbine stator. Dealing with both laminar and turbulent two-dimensional compressible flows, it solves by marching integration the B.L. equations, based on Spalding’s effective viscosity model, with quite general thermal boundary conditions. It accounts for main stream turbulent level influence and, using transition criteria based upon local profiles, is able to adapt itself to any flow modification like turbulent layer laminarization, laminar to turbulent transition, separation of laminar or turbulent type.

Copyright © 1975 by ASME
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