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AssigneeGeneral Electric Company
InventorsGilbert Farmer, David Bruce Patterson, Steven Allen Stiverson, James Michael Caldwell, Edward John Emilianowicz, Jeffrey Michael Martini
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A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor.
A method for replacing a gas turbine engine combustor liner panel, the combustor having a combustion zone formed by inner and outer liners, the inner and outer liners each including a series of panels and a plurality of cooling features, the cooling features formed by overhanging portions of the inner and outer liner panels, the cooling featuress between adjacent panels, said method comprising the steps of:
A method for replacing a portion of a combustor liner within a gas turbine engine combustor, the combustor having a combustion zone formed by an inner and outer liner, the inner and outer liners each including a series of panels and a plurality of nuggets, the nuggets formed by adjacent panels, said method comprising the steps of:
A method for replacing at least one deteriorated combustor liner panel within a gas turbine engine combustor including an annular liner including a multinugget region, a mulithole region, and an inner surface, the multihole region extending downstream from the multinugget region, said method comprising the steps of:
Dependencies are inferred from the claim text.