Combustion liner damper
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United States of America Patent
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Jan 31, 2012
Grant Date -
Apr 15, 2010
app pub date -
Oct 15, 2008
filing date -
Oct 15, 2008
priority date (Note) -
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Abstract
The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a combustion liner located radially within the flow sleeve. Spring dampers are positioned between the combustion liner and the flow sleeve to restrict the relative movement between the flow sleeve and the combustion liner and dampen vibrations at their assembly location. The spring dampers are capable of compressing to permit thermal growth between the combustion liner and flow sleeve.
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