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An Experimental System for Assessing Combustor Durability

[+] Author Affiliations
Nagaraja S. Rudrapatna, Benjamin H. Peterson, Daniel Greving

Honeywell Aerospace, Phoenix, AZ

Paper No. GT2010-22150, pp. 913-920; 8 pages
doi:10.1115/GT2010-22150
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Education; Electric Power; Manufacturing Materials and Metallurgy
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4396-3 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

Modern gas turbine combustors are made of high temperature alloys, employ effusion cooling and are protected by a Thermal Barrier Coating (TBC). Gas turbine combustor failure modes, such as TBC spallation, cracking and distortion resulting from oxidation, creep and thermal fatigue, are driven by hot spot peak temperature and the associated thermal gradient. Standard material characterization tests such as creep, oxidation and low cycle fatigue are indicators of a material’s potential performance but they neither fully represent the combustor geometric/material system nor fully represent the thermal fatigue conditions a combustor is subjected to during engine operation. Combustor rig tests and/or engine cyclic endurance tests to determine the suitability of new material systems for combustors are time consuming and costly. Therefore, a simple yet efficient test method for screening material systems under representative combustor conditions is needed. An experimental system has been developed to fill this gap. This paper discusses the configured specimen geometry, test methodology, observed test results and a comparison with typical failure modes observed in combustors.

Copyright © 2010 by ASME

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