Back to results
US 2019/0040749 A1Published application
Method of fabricating a turbine blade
AssigneeUnited Technologies Corporation
InventorsBRIAN CRAIG, RUSSELL J. BERGMAN
Life of this patent
Estimating the term…
Abstract
A method of manufacturing a blade includes forming a first segment of a blade using a first alloy, forming a second segment of a blade using a second alloy, determining a joint location of the first segment of the blade, and joining the first segment and the second segment at the joint location of the first segment.
Claims20
A method of manufacturing a blade comprising:
- forming a first segment of a blade using a first alloy;
- forming a second segment of a blade using a second alloy;
- determining a joint location of said first segment of said blade;
- and
- joining said first segment and said second segment at said joint location of said first segment.
2 more elements
A segmented portion of a gas turbine engine, comprising:
- a first segment;
- a second segment coupled to said first segment, wherein said first segment is made of a first alloy and said second segment is a second alloy, and wherein the first alloy is different from the second alloy;
- and
- a joint region, wherein the joint region includes a location where the first segment and the second segment meet.
1 more element
A blade for a gas turbine engine comprising:
- a first segment including an attachment section, a platform section, wherein said first segment is made of a first alloy;
- and
- a second segment including a airfoil section, a tip shroud, and an airfoil root joint, wherein said second segment is made of a second alloy distinct from said first alloy, and wherein said second segment is coupled to said first segment at said airfoil root joint.
Dependencies are inferred from the claim text.