Repair or remanufacture of liner panels for a gas turbine engine
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.
1. 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.
2. The method as recited in claim 1 , wherein the width WM of the main body is exclusive of a multiple of tabs.
3. 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.
4. The liner panel as recited in claim 3 , wherein the forward fan exit case liner panel includes a multiple of bushings, and the donor bushing is metallic.
5. The liner panel as recited in claim 4 , wherein at least one of the multiple of bushings is non-metallic.
6. The liner panel as recited in claim 3 , wherein the multiple of layers are each carbon fiber based.
7. 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.
8. The liner panel as recited in claim 7 , wherein the material charge is carbon fiber based.