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Thermal Details in a Rotor-Stator Cavity at Engine Conditions With a Mainstream PUBLIC ACCESS

[+] Author Affiliations
S. H. Ko, D. L. Rhode

Texas A&M University, College Station, TX

Paper No. 91-GT-275, pp. V001T01A087; 10 pages
doi:10.1115/91-GT-275
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

This investigation involves a numerical study of enclosed rotor-stator cavities of gas turbine engines. The complete elliptic form of the 2-D, axisymmetric Navier-Stokes equations for compressible turbulent flow were solved. Included are the complete fluid and thermal effects of the hot mainstream gas interacting with the cooling cavity purge flow at actual engine flow conditions for generalized geometries. Additional flow conditions above and below that for engine nominal conditions are also considered. The relationships among the important flow parameters are investigated by examining the entire set of computations. The predictions reveal that a small recirculation zone in the stator shroud axial gap region is the primary mechanism for the considerable thermal transport from the mainstream to the turbine blade root/retainer region of the rotor.

Copyright © 1991 by ASME
Topics: Engines , Rotors , Cavities , Stators
This article is only available in the PDF format.

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