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US 8,950,069 B2Granted
Integrated compressor vane casing
AssigneeRolls-Royce North American Technologies Inc.
InventorRobert A. Ress, Jr.
Life of this patent
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Abstract
A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.
Claims4
A method of forming a gas turbine engine component,
- the method comprising:
- casting, as a single article, a circular shaped vane casing segment of a gas turbine engine case having an outer case wall, a plurality of airfoils extending from a lower surface of said outer case wall, and an inner shroud extending from a lower portion of said plurality of airfoils;
- plasma spraying an abradable surface on a lower surface of an extension of the outer case wall;
- and
- forming a feed through aperture and cavity in the outer case wall concurrent with the casting as a single article.
2 more elements
Dependencies are inferred from the claim text.