Hot Streak Clocking Effects in a 1-1/2 Stage Turbine PUBLIC ACCESS

[+] Author Affiliations
Daniel J. Dorney

Western Michigan University, Kalamazoo, MI

Karen Gundy-Burlet

NASA Ames Research Center, Moffett Field, CA

Paper No. 95-GT-202, pp. V001T01A059; 10 pages
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME


Experimental data has shown that combustor hot streaks can lead to pressure side “hot spots” on first-stage turbine rotor blades. Previous numerical studies have confirmed that unsteady Navier-Stokes procedures can be used to predict the rotor pressure surface temperature increase associated with these combustor hot streaks, and suggest that second-stage turbine stators can also be subjected to increased surface temperatures. In the current investigation, two-dimensional unsteady Navier-Stokes simulations have been performed to study the effects of combustor hot streak position (or clocking) on the temperature distributions along first-stage rotor and second-stage stator airfoils. The predicted results indicate that if the hot streak is positioned such that it impinges upon the first-stage stator, then the suction surfaces of the rotor and second-stage stator attain higher time-averaged temperatures than the pressure surfaces. If the hot streak is positioned such that it does not impinge upon the first-stage stator, then the pressure surfaces of the downstream blades reach higher time-averaged temperatures than the corresponding suction surfaces.

Copyright © 1995 by ASME
Topics: Turbines
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