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Development of Temperature Estimation Method for a Gas Turbine Transition Piece

[+] Author Affiliations
Mitsutoshi Okada, Toshihiko Takahashi, Susumu Yamada, Takayuki Ozeki, Tomoharu Fujii

Central Research Institute of Electric Power Industry, Yokosuka, Japan

Paper No. GT2016-56182, pp. V05CT18A002; 10 pages
doi:10.1115/GT2016-56182
From:
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 5C: Heat Transfer
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4980-4
  • Copyright © 2016 by ASME

abstract

Temperature estimation methods for a transition piece of a gas turbine are developed in terms of microstructural changes and computational fluid dynamics (CFD) for life assessment. Temperature is estimated to be low around the center of the component where thermal barrier coating (TBC) is deposited on the Ni-base superalloy and a combination of internal cooling and film cooling is also applied. Test specimens are prepared from the above area for a high-temperature heating test in air. The microstructure in the superalloy and TBC is investigated after the test. The thermally grown oxide (TGO) formed on the bondcoat surface increases with the square root of the test time, and on the basis of this relation, a temperature-estimation equation is obtained. The estimated temperature distribution is compared with a numerical heat transfer simulation by means of CFD. The geometry of the transition piece with internal cooling structure is acquired using an X-ray computerized radiography and a laser digitizer, and it is modeled for the numerical simulation. The heat conduction analysis is applied to the transition piece, and the convection and radiation heat transfer analyses are applied to the gas path and internal cooling flow. These analyses are conjugated to estimate the temperature distribution. The simulation result agrees well with the estimation using TGO thickness.

Copyright © 2016 by ASME

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