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Metallurgical Evaluation and Condition Assessment of FSX 414 Nozzle Segments in Gas Turbines by Metallographic Methods

[+] Author Affiliations
Girish M. Shejale

Masaood John Brown, Dubai, UAE

Paper No. GT2010-22542, pp. 969-977; 9 pages
doi:10.1115/GT2010-22542
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

Gas turbine components such as nozzle segments, buckets, transition pieces and combustion liners experience damages such as creep, fatigue, high temperature oxidation and corrosion. The reliability, availability and efficiency of high temperature gas turbine parts is based on condition assessment and remaining life analysis. These gas turbine components are normally repaired, refurbished after stipulated operating hours. The decision on the extent of repairs is based on various inspection stages. Among various methodologies of condition assessment, metallography followed by microscopic evaluation has gained wide acceptance since it is cost effective, quick and reliable. Extensive in-house efforts have been put forth in this field in the development of improved techniques of metallography for accurate determination of material degradation and condition assessment. Experimental studies on Frame 6, 1st Stage Nozzle Segment (FSX 414 – cobalt based alloy) were conducted to assess the condition of the nozzle segment by using laboratory electropolishing technique for metallographic preparation. Sections taken from the nozzle segment were electropolished and examined in Light Optical Microscope (LOM) and Scanning Electron Microscope (SEM). It is concluded that the improved electropolishing technique is effective in assessing creep-fatigue, thermal fatigue and hot corrosion damage. Based on this the condition of the nozzle segment is assessed. Typical results of Frame 6, 1st Stage Nozzle Segment are presented and discussed.

Copyright © 2010 by ASME
Topics: Gas turbines , Nozzles

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