Shrouded single crystal dual alloy turbine disk
AssigneeHoneywell International Inc.
InventorsJames S. Perron, William C. Baker, Derek A. Rice
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Abstract
A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.
Claims20
A method of manufacturing a turbine engine component, the method comprising the steps of:
- casting a plurality of blades, each blade including a blade root configured to be coupled to an inner disk;
- plating the blade roots at least in part with a noble metal;
- and
- diffusion bonding the blade roots to the inner disk.
A method of manufacturing a turbine engine component, the method comprising the steps of:
- casting a plurality of blades, each blade including a blade tip configured to be coupled to an outer shroud;
- plating the blade tips at least in part with a noble metal;
- and
- diffusion bonding the blade tips to the outer shroud.
A method of manufacturing a turbine engine component, the method comprising the steps of:
- casting a plurality of blades, each blade including:
- a blade root configured to be coupled to an inner disk;
- and
- a blade tip configured to be coupled to an outer shroud;
- plating the blade roots at least in part with a noble metal;
- plating the tips at least in part with the noble metal;
- diffusion bonding the blade roots to the inner disk;
- and
- diffusion bonding the blade tips to the outer shroud.
Dependencies are inferred from the claim text.