Gas turbine combustor endcover with adjustable flow restrictor and related method
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United States of America Patent
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Nov 17, 2015
Grant Date -
May 23, 2013
app pub date -
Nov 18, 2011
filing date -
Nov 18, 2011
priority date (Note) -
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status (Latency Note)
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Abstract
An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity.
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