Gas turbine guide vane
AssigneeUnited Technologies Corporation
InventorsThomas J. Watson, Vincent C. Nardone, John A. Visoskis, Stuart A. Anderson
Life of this patent
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Abstract
A method for manufacturing an airfoil is provided which includes the steps of: a) providing a billet of discontinuously reinforced aluminum having at least 10 volume percent of silicon carbide as a reinforcing element, and no more than 30 volume percent of silicon carbide as the reinforcing element; 2) extruding the billet into an airfoil shaped geometry from a die, wherein the geometry includes a first wall, a second wall disposed opposite the first wall, a leading edge, a trailing edge disposed opposite the leading edge, and a first cavity disposed between the first and second walls, and the leading and trailing edges.
Claims10
A method for manufacturing an airfoil, comprising:
- providing a billet of discontinuously reinforced aluminum having at least 10 volume percent or silicon carbide as a reinforcing element, and no more than 30 volume percent of silicon carbide as said reinforcing element;
- extruding said billet into an airfoil shaped geometry from a die, said geometry including:
- a first wall;
- a second wall, disposed opposite said first wall;
- a leading edge;
- a trailing edge, disposed opposite said leading edge;
- and
- a first cavity, disposed between said first and second walls, and said leading and trailing edges;
- wherein said airfoil shaped geometry extends in a lengthwise direction exiting said die.
A method for manufacturing an airfoil, comprising:
- providing a billet of discontinuously reinforced aluminum having a reinforcing element selected from the group consisting of SiC, Al.sub.2 O.sub.3, and B.sub.4 C;
- extruding said billet into an airfoil shaped geometry from a die, said geometry including:
- a first wall;
- a second wall, disposed opposite said first wall;
- a leading edge;
- a trailing edge, disposed opposite said leading edge;
- and
- a first cavity, disposed between said first and second walls, and said leading and trailing edges;
- wherein said airfoil shaped geometry extends in a lengthwise direction exiting said die.
Dependencies are inferred from the claim text.