Cooling patch for hot gas path components
AssigneeGeneral Electric Company
InventorJonathan Dwight Berry
Life of this patent
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Abstract
The present application provides a cooling patch for use with a hot gas path component of a gas turbine engine. The cooling patch may include a base layer with a number of cooling channels extending therethrough, and a cover layer positioned on the base layer. The base layer and the cover layer may include a pre-sintered preform material.
Claims18
A cooling patch configured to provide additional cooling to a hot gas path component of a gas turbine engine, the cooling patch comprising:
- a base layer attached to a cold side surface of the hot gas path component, the base layer having a first surface in contact with the cold side surface and a second surface opposite the first surface;
- a plurality of cooling channels formed in and extending along the second surface of the base layer;
- and
- a cover layer positioned on the second surface of the base layer, the cover layer comprising a filter at one end thereof;
- wherein the base layer and the cover layer comprise a pre-sintered preform material heat-treated in position on the hot gas path component;
- and wherein the hot gas path component is a combustor component larger than the cooling patch.
A method of providing additional cooling to a hot gas path component, the method comprising:
- aligning a cooling patch with a number of cooling holes on the hot gas path component, the cooling patch comprising a base layer having a first surface and a second surface, a plurality of cooling channels formed in and extending along the second surface of the base layer, a cover layer defining a top surface of the plurality of cooling channels, and a plurality of outlet holes in fluid communication with the plurality of cooling channels, the aligning of the cooling patch including aligning the plurality of outlet holes with the number of cooling holes;
- attaching the first surface of the base layer of the cooling patch to a cold side surface of the hot gas path component, wherein the hot gas path component is a combustor component larger than the cooling patch;
- heat treating the cooling patch in place;
- providing a flow of air through a filter attached at one end of the cover layer proximate to the plurality of cooling channels of the cooling patch, such that the flow of air flows through the plurality of cooling channels to cool the hot gas path component;
- and
- flowing the air through the number of cooling holes on the hot gas path component.
A hot gas path component for use with a gas turbine engine, the hot gas path component comprising:
- a combustor liner having a cold side surface and a hot side surface;
- a plurality of cooling holes extending through the combustor liner from the cold side surface to the hot side surface;
- and
- a cooling patch having a first surface positioned on and attached to the cold side surface of the combustor liner adjacent to the plurality of cooling holes, a second surface opposite the first surface, and a filter attached at one end of the cooling patch;
- wherein the second surface of the cooling patch comprises a plurality of cooling channels such that a flow of air passes through the plurality of cooling channels and through the plurality of cooling holes;
- and wherein the cooling patch is smaller than the combustor liner.
Dependencies are inferred from the claim text.