Hot streaks and phantom cooling in a turbine rotor passage. II - Combined effects and analytical modellingExperimental documentation and analytical correlations demonstrating the effects of hot streak accumulation and phantom cooling on turbine rotor airfoil surface temperature are presented. Results are shown which quantify the impact of a nonuniform temperature profile at the entrance of a turbine due to combustor-generated hot and cold streaks, and cooling air discharged from the trailing edge of the upstream stator. Experimental results are shown for a range of controlling variables to identify where streak accumulation and phantom cooling were most likely to be strongest. These variables include streak-to-free stream density ratio, streak injection location, and coolant-to-free stream density and velocity ratios. Experimental results are shown for the combined effects of hot streak and stator coolant on the adiabatic recovery temperature of the rotor.
Document ID
19930035329
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roback, Richard J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Dring, Robert P. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 92-GT-76
Meeting Information
Meeting: ASME, International Gas Turbine and Aeroengine Congress and Exposition