US 9,809,886 B2
Method of machining a gas turbine engine component
Daniel Clark, Derby (GB); and Andrew Robert Walpole, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Sep. 2, 2015, as Appl. No. 14/843,304.
Claims priority of application No. 1416483.4 (GB), filed on Sep. 18, 2014.
Prior Publication US 2016/0083852 A1, Mar. 24, 2016
Int. Cl. C23F 1/00 (2006.01); C23F 1/12 (2006.01); F01D 5/28 (2006.01); F01D 9/02 (2006.01); F23R 3/00 (2006.01); F01D 5/00 (2006.01); F01D 5/18 (2006.01); G01N 21/956 (2006.01)
CPC C23F 1/00 (2013.01) [C23F 1/12 (2013.01); F01D 5/28 (2013.01); F01D 9/02 (2013.01); F23R 3/002 (2013.01); B23P 2700/06 (2013.01); F01D 5/005 (2013.01); F01D 5/186 (2013.01); F05D 2230/10 (2013.01); G01N 21/95692 (2013.01)] 11 Claims
OG exemplary drawing
 
1. 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.