Thermal Details in a Rotor–Stator Cavity at Engine Conditions With a Mainstream

[+] Author and Article Information
S. H. Ko, D. L. Rhode

Turbomachinery Laboratories, Mechanical Engineering Department, Texas A&M University, College Station, TX 77843

J. Turbomach 114(2), 446-453 (Apr 01, 1992) (8 pages) doi:10.1115/1.2929164 History: Received March 04, 1991; Online June 09, 2008


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 those 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 © 1992 by The American Society of Mechanical Engineers
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