TY - GEN
T1 - EFFECTS OF PART-TO-PART FLOW VARIATIONS ON OVERALL EFFECTIVENESS AND LIFE OF ROTATING TURBINE BLADES
AU - Knisely, Brian F.
AU - Berdanier, Reid A.
AU - Wagner, Joel H.
AU - Thole, Karen A.
AU - Arisi, Allan N.
AU - Haldeman, Charles W.
N1 - Funding Information:
The authors would like to thank Pratt & Whitney and the U.S. Department of Energy – National Energy Technology Laboratory for sponsoring research presented in this paper. This paper is based upon work supported by the Department of Energy under Award Number DE-FE0025011.
Publisher Copyright:
Copyright © 2022 by Raytheon Technologies Corporation.
PY - 2022
Y1 - 2022
N2 - As firing temperatures in gas turbine engines continue to increase to achieve high efficiencies, components in the main gas path must be protected with cooling flows to ensure lifing targets are met. Manufacturing variations, however, influence the performance and life characteristics of components with the same nominal design. This study presents blade flow and overall cooling effectiveness measurements for nine true-scale, aero engine turbine blades with realistic manufacturing variations. Flow measurements were made through each blade at a fixed pressure ratio to determine flow variability between holes and between blades. Infrared thermography was used to capture spatially-resolved temperature measurements reported as overall effectiveness on the same nine blades under high-speed rotating conditions at the Steady Thermal Aero Research Turbine Laboratory. Thermal performance was correlated with blade flow performance indicating substantial blade-to-blade variations resulting from manufacturing differences. Measurements also indicated wide variations in cooling jet trajectories as well as overall cooling effectiveness. Finally, the observed blade-to-blade variations in effectiveness were scaled to engine conditions with lifing estimates showing some blades would be expected to last only half as long as others due to manufacturing variability.
AB - As firing temperatures in gas turbine engines continue to increase to achieve high efficiencies, components in the main gas path must be protected with cooling flows to ensure lifing targets are met. Manufacturing variations, however, influence the performance and life characteristics of components with the same nominal design. This study presents blade flow and overall cooling effectiveness measurements for nine true-scale, aero engine turbine blades with realistic manufacturing variations. Flow measurements were made through each blade at a fixed pressure ratio to determine flow variability between holes and between blades. Infrared thermography was used to capture spatially-resolved temperature measurements reported as overall effectiveness on the same nine blades under high-speed rotating conditions at the Steady Thermal Aero Research Turbine Laboratory. Thermal performance was correlated with blade flow performance indicating substantial blade-to-blade variations resulting from manufacturing differences. Measurements also indicated wide variations in cooling jet trajectories as well as overall cooling effectiveness. Finally, the observed blade-to-blade variations in effectiveness were scaled to engine conditions with lifing estimates showing some blades would be expected to last only half as long as others due to manufacturing variability.
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U2 - 10.1115/GT2022-83216
DO - 10.1115/GT2022-83216
M3 - Conference contribution
AN - SCOPUS:85141544821
T3 - Proceedings of the ASME Turbo Expo
BT - Heat Transfer - Combustors; Film Cooling
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition, GT 2022
Y2 - 13 June 2022 through 17 June 2022
ER -