Combustor resonator section with an internal thermal barrier coating and method of fabricating the same
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United States of America Patent
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Jul 19, 2016
Grant Date -
Mar 28, 2013
app pub date -
Sep 19, 2012
filing date -
Sep 23, 2011
priority date (Note) -
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Abstract
A combustor (100) for a gas turbine engine (30) has a circumferentially extending liner (109) defining at least a portion of an interior combustion chamber (107) and a hot gas path (115). The liner includes a resonator section (112) including at least one resonator (116A, 116B) having a resonator chamber (125A, 125B) formed on an exterior of the liner. A thermal barrier coating (118) is disposed along an inner surface of the liner including an inner surface (130) of the resonator section. The resonator further includes a plurality of apertures (117) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.
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