Component repair system and method
AssigneesGeneral Electric Company, Oliver Crispin Robotics Limited
InventorsMichael Robert Millheam, Andrew Crispin Graham, Byron Andrew Pritchard, Jr., David Scott Diwinsky, Jeremy Clyde Bailey, Michael Edward Eriksen, Ambarish Jayant Kulkarni
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Abstract
A method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.
Claims14
A system for repairing a component of a gas turbine engine having a deposit, the gas turbine engine defining an interior and the component positioned at least partially within the interior, the system comprising:
- a controller;
- a pressurized gas source;
- a gas heater coupled to the controller and in airflow communication with the pressurized gas source;
- and
- an insertion tube defining a proximal end and a distal end, an output of the gas heater in airflow communication with the proximal end, the insertion tube configured to be inserted into the interior of the gas turbine engine such that the distal end is positioned proximate the component of the gas turbine engine;
- wherein the controller executes computer instructions that selectively control operation of the gas heater such that the gas heater heats a flow of gas from the pressurized gas source to a temperature greater than about 500 degrees Fahrenheit and less than about 1200 degrees Fahrenheit.
A system for repairing a component of a gas turbine engine having a deposit, the gas turbine engine defining an interior and the component positioned at least partially within the interior, the system comprising:
- a gas source;
- and
- an insertion tube in airflow communication with the gas source and defining a distal end, the insertion tube configured to be inserted into the interior of the gas turbine engine such that the distal end is positioned proximate to the exterior of the component of the gas turbine engine;
- wherein the gas source is a flammable gas source for providing a flammable gas to the insertion tube, and wherein the insertion tube is configured to ignite the flammable gas into a flame extending from the distal end to pyrolize the deposit on the exterior of the component;
- wherein the insertion tube is configured to be moved from a slacked position to a tensioned position.
Dependencies are inferred from the claim text.