Coating fixtures for gas turbine engine compressor disks
AssigneeSolar Turbines Incorporated
InventorYuchin Kang
Life of this patent
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Abstract
A method for coating a gas turbine engine compressor rotor having a compressor disk with axial slots includes inserting masking fixtures into the axial slots. Each masking fixture includes a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into. The method also includes applying a coating to the compressor rotor after inserting the masking fixtures into the axial slots followed by drying the coating on the compressor rotor at a predetermined temperature. The method further includes removing the masking fixtures from the axial slots after drying the coating on the compressor rotor followed by curing the coating on the compressor rotor.
Claims19
A method for coating a gas turbine engine compressor rotor including a compressor disk having axial slots, the method comprising:
- inserting masking fixtures into the axial slots, each masking fixture including a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into;
- applying a coating to the compressor rotor after inserting the masking fixtures into the axial slots;
- drying the coating on the compressor rotor at a predetermined temperature after applying th coating to the compressor rotor and before curing the coating on the compressor rotor;
- removing the masking fixtures from the axial slots after drying the coating on the compressor rotor and before curing the coating on the compressor rotor;
- and
- curing the coating on the compressor rotor.
A method for coating a gas turbine engine rotor with a rotor disk having axial slots, the method comprising:
- grit blasting the gas turbine engine rotor prior to applying the coating to the gas turbine engine rotor;
- sliding masking fixtures into the axial slots, each masking fixture including a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into;
- applying a coating to the gas turbine engine rotor after sliding the masking fixtures into the axial slots;
- drying the coating on the gas turbine engine rotor at a predetermined temperature after applying the coating to the gas turbine engine rotor and before curing the coating on the gas turbine engine rotor;
- sliding the masking fixtures out of the axial slots after drying the coating on the gas turbine engine rotor and before curing the coating on the gas turbine engine rotor;
- and
- curing the coating on the gas turbine engine rotor.
A masking fixture for inserting into a gas turbine engine compressor disk axial slot during a coating process, the masking fixture comprising:
- a masking root having a shape that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into;
- and
- a material having a heat deflection temperature greater than 93.3 degrees Celsius;
- wherein the masking root is configured, to cover all portions of the axial slot that contact the axial blade.
Dependencies are inferred from the claim text.