Multi-airfoil split and rejoin method to produce enhanced durability coating
AssigneeUnited Technologies Corporation
InventorsEdward R. Bareiss, Russell J. Bergman, Bradley T. Duelm, Michael L. Miller, Paul M. Pellet
Life of this patent
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Abstract
A method for working an airfoil cluster is disclosed. The method may include attaching a first datum to a first portion of the airfoil cluster and a second datum to a second portion of the airfoil cluster; adding material to at least one of the first portion and the second portion; and joining the first portion to the second portion, the first and second datums substantially aligned in a common plane spaced away from the first and second portions.
Claims9
A method for working an airfoil cluster, comprising:
- attaching a first register block to a first portion of the airfoil cluster and a second register block to a second portion of the airfoil cluster wherein the first portion and the second portion each comprise a contoured end wall and a serpentine, cross-platform cooling passage having at least one trip strip;
- using a cutting process to separate the first portion from the second portion such that the serpentine passage of the airfoil cluster is preserved;
- separating the first portion from the second;
- adding material to at least one of the first separated portion and the second separated portion;
- applying a coating to the first separated portion and the second separated portion;
- and
- joining the first portion and the second portion, the first and second register blocks having a predefined arrangement with respect to one another which aligns the first and second separated portions, wherein an outer surface of the first register block and an outer surface of the second register block has a predefined contour arrangement with respect to one another, and further comprising aligning the first separated portion with the second separated portion by setting the outer surfaces of the first and second register blocks on a surface that matches the predefined contour arrangement, an endwall contouring and cross-platform cooling passages of the first and second separated portions being aligned through the use of the first and second register blocks.
A method for working an airfoil cluster of a gas turbine engine, the method comprising:
- providing the airfoil cluster with a first portion and a second portion, each of the first and second portions having a serpentine, cross-platform cooling passage having at least one trip strip;
- attaching a first register block to the first portion of the airfoil cluster;
- attaching a second register block to the second portion of the airfoil cluster;
- providing an attachment hole and a separate locating hole in each of the first and second register blocks for attaching and locating the first and second portions to a fixture during a cutting process;
- splitting and separating the airfoil cluster between the first portion and the second portion such that the passages of the first and second portions are preserved;
- adding an equal amount of material to at each of the first and second separated portions;
- applying a durability coating to each of the first and second separated portions;
- aligning the first separated portion with the second separated portion through surfaces of the first and second register blocks;
- joining the first and second separated portions together;
- using the attachment hole in the first register block for attachment of the first separated portion to a fixture during the joining process;
- and removing the first and second register blocks.
Dependencies are inferred from the claim text.