Device and method for treatment of high-pressure turbine blades of a gas turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsMatthias DUDECK, Juergen DUPRE, Eckart UHLMANN, Martin BILZ
Life of this patent
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Abstract
The present invention relates to a device and a method for in-situ treatment of turbine blades/vanes of a gas turbine, with the treatment device being insertable into a combustion chamber of the gas turbine via at least one access aperture and placeable on cooling-air recesses of the turbine blades, with the treatment device at its end including a tool head with at least one tool and at least one jet nozzle, with the jet nozzle being connected to a medium hose for externally supplying a treatment fluid, with the treatment device being provided with an actuating device for exactly guiding and/or placing and/or moving the tool head.
Claims15
Treatment device for in-situ treatment of turbine blades/vanes of a gas turbine, with the treatment device being insertable into a combustion chamber of the gas turbine via at least one access aperture and placeable on cooling-air recesses of the turbine blades, with the treatment device at its end including a tool head with at least one tool and at least one jet nozzle, with the jet nozzle being connected to a medium hose for externally supplying a treatment fluid, with the treatment device being provided with an actuating device for exactly guiding and/or placing and/or moving the tool head.
Method in accordance with Claimj 7, characterized in that after removal of deposits and/or foreign matter coatings these are rinsed out by means of a gas.
Dependencies are inferred from the claim text.