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CMC Combustor Liner Demonstration in a Small Helicopter Engine

[+] Author Affiliations
Tania Bhatia, David Jarmon, Jun Shi, Scott Kearney

United Technologies Research Center, East Hartford, CT

Aleksandar Kojovic, John Hu, Alexander Prociw

Pratt & Whitney, Canada, Mississauga, ON, Canada

Paper No. GT2010-23810, pp. 509-513; 5 pages
doi:10.1115/GT2010-23810
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 United Technologies Corporation

abstract

UTRC and P&W Canada partnered to demonstrate an advanced combustor configuration that was enabled by high temperature CMC materials, in a PW200 series combustor. The PW200 series have reverse-flow combustors and the program presented significant challenges in design and fabrication. The advanced CMC configuration was successfully tested in a PW206 combustor rig. At full power, a 40–50% reduction in pattern factor relative to the bill-of-material metal combustor was measured. The combustor exit plane temperatures were generally better mixed due to the combined effects of (1) eliminating the cold film layers near the combustor walls and (2) the increase in fuel injector count enabled by the increase in dilution air. The CMC combustor was also successfully tested in an engine configuration. Post test gas path surfaces of the EBC coated CMC combustor components were in good condition.

Copyright © 2010 by United Technologies Corporation

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