Turbine component crack repair using cathodic arc and/or low pressure plasma spraying and hip
AssigneeUnited Technologies Corporation
InventorsMichael Minor, Chris Bischof, Herbert Koven, Paul Pellet
Life of this patent
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Abstract
A method for repairing cracks in a metal part comprising the steps of providing a metal part having a crack, cleaning the crack to remove an oxide layer, depositing a repair alloy via at least one of cathodic arc deposition and low pressure plasma spraying to cover the crack, and heating the part at a temperature and pressure sufficient to close the crack.
Claims17
A method for repairing cracks in a metal part comprising the steps of:
- providing a metal part having a crack;
- cleaning said crack to remove an oxide layer;
- depositing a repair alloy via at least one of cathodic arc deposition and low pressure plasma spraying to cover said crack;
- and
- heating the part at a temperature and pressure sufficient to close the crack.
A method for repairing cracks in a gas turbine engine component comprising the steps of:
- providing a gas turbine engine component having a crack;
- cleaning said crack to remove an oxide layer;
- depositing a repair alloy via at least one of cathodic arc deposition and low pressure plasma spraying to cover said crack;
- and
- heating the gas turbine engine component at a temperature and pressure sufficient to close the crack.
A repaired metal part made according to the process comprising the steps of:
- providing a metal part having a crack to be repaired;
- cleaning said crack to remove an oxide layer;
- deposition and low pressure plasma spraying to cover said crack;
- and
- heating the part at a temperature and pressure sufficient to close and repair the crack.
Dependencies are inferred from the claim text.