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AssigneeGeneral Electric Company
InventorsDaniel Endecott Osgood, Gregory Terrence Garay, Ryan Christopher Jones, Tingfan Pang
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A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
A gas turbine engine component comprising:
A gas turbine engine component comprising:
Dependencies are inferred from the claim text.