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US 2009/0047126 A1Published application
Integrated compressor vane casing
AssigneeRolls-Royce North American Technologies Inc.
InventorRobert A. Ress, JR.
Life of this patent
Estimating the term…
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.
Claims23
A vane casing segment, comprising:
- an outer case wall having a lower surface;
- a plurality of airfoils connected with said lower surface, said plurality of airfoils having a lower portion;
- an inner shroud connected with said lower portion of said plurality of airfoils;
- and
- wherein said outer case wall, said plurality of airfoils and said inner shroud are formed as one integral piece.
2 more elements
A gas turbine engine case, comprising:
- a plurality of integrated vane casing segments interconnected to one another above a plurality of blades;
- wherein each of said plurality of integrated vane casing segments includes an outer case wall, a plurality of airfoils connected with a lower surface of said outer case wall, and an inner shroud connected with a lower portion of said plurality of airfoils;
- and
- wherein the outer case walls of each of the plurality of integrated vane casing segments are connected.
1 more element
A method of forming a blade casing for a gas turbine engine, comprising:
- integrally forming a circular shaped vane casing segment having an outer case wall, a plurality of airfoils connected with a lower surface of said outer case wall, and an inner shroud connected with a lower portion of said plurality of airfoils.
A gas turbine engine compressor component, comprising:
- a plurality of compressor vanes integrally formed with a wall of a case, the case spanning a blade and vane row in the compressor.
Dependencies are inferred from the claim text.