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US 8,127,442 B2Granted
Compressor blade flow form technique for repair
AssigneeUnited Technologies Corporation
InventorsJohn F. Mullooly, William M. Rose, David R. Malley, Monika D. Kinstler
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Abstract
A method for repairing a turbine engine component is provided. The method broadly comprises the steps of providing a turbine engine component having an airfoil portion, applying a coating to the airfoil portion, and restoring a tip portion, a chord, and surfaces of the airfoil portion to original dimensions in a single operation. A system for repairing the turbine engine component is also described.
Claims8
A method for repairing a turbine engine component comprising the steps of:
- providing a turbine engine component having an airfoil portion with a coating, a tip portion and two surfaces;
- removing said coating on the airfoil portion of said turbine engine component;
- applying a restoration coating to said two surfaces of said airfoil portion;
- said restoration coating applying step comprises applying said restoration coating to said two surfaces of said airfoil portion only from the tip portion to a mid-span portion of said airfoil portion;
- placing said turbine engine component with said applied restoration coating into a die set and simultaneously restoring the tip portion, a chord, and said two surfaces of said airfoil portion to original dimensions in a single flow forming operation and removing flash from said airfoil portion after said restoring step.
2 more elements
Dependencies are inferred from the claim text.