System and method for coupling a component to a gas turbine engine blade
AssigneeROLLS-ROYCE plc
InventorMarius MONORANU
Life of this patent
Estimating the term…
Abstract
A system for coupling at least one component to a blade of a gas turbine engine includes a blade holder and an intensifier tool. The intensifier tool includes a plate configured to contact the component and a heating device coupled to the plate. The system further includes an adhesive layer disposed between the component and the blade, a pressure strip coupled to the plate and the blade that fully encloses the plate, and a pressure applicator coupled to the plate. The adhesive layer has a uniform bond thickness along a length of the component due to pressure applied by the pressure applicator. Upon being heated by the heating device, the adhesive layer is cured, thereby coupling the component to the blade.
Claims19
A system for coupling at least one component to a blade of a gas turbine engine, the system comprising:
- a blade holder including:
- a plurality of side walls;
- and
- a bottom wall connected to each of the plurality of side walls,
- wherein the bottom wall and the plurality of side walls together define a receiving space to receive at least a portion of the blade and the at least one component therein;
- an intensifier tool disposed on the at least one component, wherein the intensifier tool includes:
- a plate configured to contact the at least one component;
- and
- a heating device coupled to the plate and configured to heat the at least one component;
- an adhesive layer disposed between the at least one component and the blade;
- a pressure strip coupled to the plate of the intensifier tool and the blade, wherein the pressure strip fully encloses the plate;
- and
- a pressure applicator coupled to the pressure strip and configured to apply a pressure on the plate,
- wherein the adhesive layer has a uniform bond thickness along a length of the at least one component due to the pressure applied by the pressure applicator, and wherein, upon being heated by the heating device, the adhesive layer is cured, thereby coupling the at least one component to the blade.
A method of coupling at least one component to a blade of a gas turbine engine, the method comprising the steps of:
- providing a blade holder including a plurality of side walls and a bottom wall connected to each of the plurality of side walls, wherein the bottom wall and the plurality of side walls together define a receiving space;
- disposing an adhesive layer between the at least one component and the blade;
- placing the at least one component on the blade;
- receiving at least a portion of the blade and the at least one component within the receiving space of the blade holder;
- placing an intensifier tool on the at least one component, wherein the intensifier tool includes a plate configured to contact the at least one component, a pressure applicator coupled to the plate, and a heating device coupled to the plate;
- coupling a pressure strip to the plate of the intensifier tool and the blade, wherein the pressure strip fully encloses the plate;
- coupling a pressure applicator to the pressure strip;
- applying, via the pressure applicator, a pressure on the plate of the intensifier tool;
- providing a uniform bond thickness of the adhesive layer along a length of the at least one component based on the pressure applied by the pressure applicator;
- and
- heating, via the heating device of the intensifier tool, the at least one component to cure the adhesive layer, thereby coupling the at least one component to the blade.
Dependencies are inferred from the claim text.