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US 9,809,886 B2Granted
Method of machining a gas turbine engine component
AssigneeROLLS-ROYCE plc
InventorsDaniel Clark, Andrew Robert Walpole
Life of this patent
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Abstract
A method of machining a nickel containing alloy gas turbine engine component (34) comprises applying a material removal gas comprising gaseous carbon monoxide at a nickel carbonyl gas forming temperature such as 50 to 60° C. to a surface of the component to form a nickel carbonyl gas, and thereby remove a surface layer from at least part of the component.
Claims11
A method of flow testing cooling holes of a nickel alloy component of a gas turbine engine comprising:
- providing a gas turbine engine component comprising a nickel alloy;
- applying a material removal gas comprising gaseous carbon monoxide at a temperature of between 50° and 60° Celsius to a surface of the component to form a nickel carbonyl gas and thereby remove a surface layer from at least part of the component, wherein the component comprises one or more cooling holes, and the surface from which a surface layer is removed comprises an internal surface of the one or more cooling holes, and
- wherein the method further comprises at least one testing cycle, each testing cycle comprising applying a testing fluid through the cooling holes of the component and measuring the flow of the fluid.
Dependencies are inferred from the claim text.