Combustion chamber for a gas turbine engine
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United States of America Patent
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Dec 28, 2010
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N/A
app pub date -
May 31, 2007
filing date -
Jun 1, 2006
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Abstract
A combustion chamber for a gas turbine engine comprising at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the interior of the combustion chamber. The cavity extends around at least part of the neck and is spaced apart therefrom to define a cooling chamber therebetween. The cooling chamber allows the neck and the cavity to be cooled with a flow of cooling air. The sunken neck allows the resonator to be located within enclosures with minimal volume without compromising on the damping properties afforded.
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