TECHNICAL PAPERS: Gas Turbines: Manufacturing, Materials, and Metallurgy

Metallurgical Considerations for Life Assessment and the Safe Refurbishment and Requalification of Gas Turbine Blades

[+] Author and Article Information
J. A. Daleo, K. A. Ellison, D. H. Boone

BWD Turbines Ltd., 1-601 Tradewind Drive, Ancaster, Ontario L9G 4V5, Canada

J. Eng. Gas Turbines Power 124(3), 571-579 (Jun 19, 2002) (9 pages) doi:10.1115/1.1455638 History: Received November 01, 1999; Revised February 01, 2000; Online June 19, 2002
Copyright © 2002 by ASME
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A photomicrograph illustrating the microstructure of a service-run aluminized CoCrAlY coating applied to a directionally solidified GTD111 alloy component
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Metallurgical temperature estimates of a service exposed GE MS7001F first-stage turbine blade based on inter-diffusion rates between the aluminized CoCrAlY overlay coating and the directionally solidified GTD111 base alloy
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A photograph illustrating irreversible stripping damage caused to a pin fin array
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A scanning electron micrograph of DS GTD111 alloy in the standard heat-treated condition illustrating the duplex γ precipitate microstructure and the grain boundary carbide morphology
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A scanning electron micrograph of DS GTD111 alloy after 18,000 hours of service
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A scanning electron micrograph of an IN-738LC turbine blade processed through the standard reheat treatment cycle. Note that the microstructure was not restored to its original condition.
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A scanning electron micrograph of an IN-738LC turbine blade not correctly processed through the modified high-temperature reheat treatment cycle
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A photomicrograph illustrating melting of the inter-diffusion zone of an aluminide coated IN-738LC substrate
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Photomicrographs illustrating re-crystallization of the surface grains observed in the root form of a reheat treated DS GTD111 alloy blade
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A plot comparing strain rate data measured from polycrystalline GTD111 alloy samples in different conditions at 850°C and 0.8 percent total strain
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A plot illustrating the drop in creep rate properties measured in a polycrystalline GTD111 alloy blade airfoil in terms of temperature capability of “new” material in the standard heat treated condition
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A plot of stress versus estimated creep rupture life of polycrystalline GTD111 material in the standard heat treated condition based on 5 percent, 10 percent, and 15 percent failure elongation
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A plot comparing a Larson-Miller curve created from estimated creep rupture life based on strain rate to failure elongation, to published GTD111 creep rupture data
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A sampling of a series of transmission mode thermal inertia of images of a CF6 turbine blade
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A photomicrograph of a service-run aluminized CoCrAlY coating applied to a DS GTD111 alloy component illustrating data phase depletion and inter-diffusion with the base alloy



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