Repair or remanufacture of liner panels for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsBrian K. Holland, Michael A. Morden, Brandon A. Gates, William Bogue
Life of this patent
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Abstract
A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.
Claims8
A method of remanufacturing a liner panel for a gas turbine engine, comprising:
- removing a bushing from a damaged component;
- and
- molding the bushing with a material charge;
- wherein the material charge includes a multiple of layers, and at least one of the multiple of layers incudes a discontinuity;
- and
- wherein a main body of one of the multiple of layers defines a width (WM) and the discontinuity of one of the multiple of layers defines a width (WD), and wherein a ratio WD/WM is defined between 0.575-0.66.
A liner panel for a gas turbine engine, comprising:
- a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel;
- wherein the forward fan exit case liner panel is molded from a material charge that includes a multiple of layers, and at least one of the multiple of layers includes a discontinuity;
- and
- wherein a main body of one of the multiple of layers defines a width (WM) and the discontinuity of one of the multiple of layers defines a width (WD), a ratio WD/WM is defined between 0.575-0.66, and the width WM of the main body is exclusive of a multiple of tabs.
A liner panel for a gas turbine engine, comprising:
- a forward fan exit case liner panel molded from a material charge that includes a multiple of layers, wherein at least one of the multiple of layer includes a discontinuity;
- and
- wherein a main body of one of the multiple of layers defines a width (WM) and the discontinuity of one of the multiple of layers defines a width (WD), a ratio WD/WM is defined between 0.575-0.66, and the width WM of the main body is exclusive of a multiple of tabs.
Dependencies are inferred from the claim text.