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A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support

A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support frame. The mounting joint includes a joint inner race and a joint outer race. At least one of the joint inner race and the joint outer race includes a spherical surface. The mounting joint is configured to reduce dynamic loads to the gas turbine engine structure and static bending to the rotor. The plurality of mechanical fuses extend through at least one of the joint inner race and the joint outer race.

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1. A method for reducing dynamic loading of a gas turbine engine, the engine including a rotor shaft assembly including a rotor shaft, a bearing assembly, a mounting joint, a support frame, and a plurality of circumferentially spaced mechanical fuses, said method comprising:supporting the rotor shaf

1. A method for reducing dynamic loading of a gas turbine engine, the engine including a rotor shaft assembly including a rotor shaft, a bearing assembly, a mounting joint, a support frame, and a plurality of circumferentially spaced mechanical fuses, said method comprising:supporting the rotor shaft on the gas turbine engine support frame with the bearing assembly, wherein the bearing assembly includes an inner race, an outer race, and a rolling element, such that a cone shaft, including a conical cross-section, extends between the rotor shaft and the bearing assembly;coupling the mounting joint including a spherical surface to the bearing assembly;removably coupling each of the plurality of circumferentially spaced mechanical fuses to the mounting joint spherical surface, such that each of the plurality of mechanical fuses extends at least partially into the cone shaft spherical surface, and such that a position of each of the plurality of mechanical fuses is offset axially from a centerplane of the bearing assembly; andoperating the gas turbine engine. 2. A method in accordance with claim 1 wherein the mounting joint includes a joint inner race and a joint outer race, wherein coupling the mounting joint to the bearing assembly further comprises:mounting the mounting joint to the rotor shaft such that the mounting joint is between the bearing assembly and the rotor shaft; andcoupling the joint inner race to the joint outer race with the plurality of mechanical fuses that each fail at a predetermined moment load. 3. A method in accordance with claim 1 wherein the mounting joint includes a joint inner race and a joint outer race, coupling the mounting joint to the bearing assembly further comprises:mounting the mounting joint to the support frame such that the mounting joint is between the cone shaft and the rotor shaft; andcoupling the joint inner race to the joint outer race with the plurality of mechanical fuses that each fail at a predetermined moment load. 4. A method in accordance with claim 1 wherein removably coupling each of the plurality of mechanical fuses further comprises coupling each of the plurality of mechanical fuses to the mounting joint such that each fuse fails in shear at a predetermined load. 5. A bearing assembly for a gas turbine engine rotor, said bearing assembly comprising:a paired race comprising an outer race and an inner race;a bearing between said inner and outer races, said bearing configured to support the rotor on a support frame, such that a cone shaft, having a conical cross-sectional profile, extends between said paired race and an engine rotor shaft;a mounting joint comprising a joint inner race and a joint outer race, at least one of said joint inner race and said joint outer race comprising a spherical surface, said mounting joint configured to reduce dynamic loads to the gas turbine engine and static bending to the rotor; anda plurality of circumferentially spaced mechanical fuses extending through at least one of said joint inner race and said joint outer race such that a position of each said mechanical fuse is offset axially from a centerplane of said bearing races. 6. A bearing assembly in accordance with claim 5 further comprising a spacer configured to maintain said mounting joint in alignment with respect the rotor. 7. A bearing assembly in accordance with claim 5 wherein said mechanical fuses secure said joint inner race to said joint outer race. 8. A bearing assembly in accordance with claim 7 wherein said mounting joint is between said inner race and the gas turbine engine rotor. 9. A bearing assembly in accordance with claim 7 wherein each said mechanical fuse comprises a pin configured to shear at a predetermined moment load. 10. A bearing assembly in accordance with claim 7 wherein at least one of said inner race and said outer race is between said mounting joint and said support frame. 11. A bearing assembly in accordance with claim 7 wherein said inner race comprises a split race mating. 12. A bearing assembly in accordance with claim 7 wherein said outer race comprises a split race mating. 13. A rotor assembly comprising:a rotor shaft;a cone shaft, including a conical cross-section;a support frame; anda bearing assembly supporting said rotor shaft to said support frame and configured to reduce dynamic loads to said support frame, said cone shaft extending between said bearing assembly and said rotor shaft, said bearing assembly comprising a paired race, a rolling element, and a mounting joint, said paired race comprising an outer race and an inner race, said rolling element between said outer and inner races, said mounting joint comprising a spherical surface; anda plurality of circumferentially spaced mechanical fuses extending through said mounting joint at least partially into said cone shaft such that a position of each said mechanical fuse is offset axially from a centerplane of said paired race. 14. A rotor assembly in accordance with claim 13 wherein said mounting joint comprises a joint inner race and a joint outer race, at least one of said joint inner race and said joint outer race comprises said spherical surface. 15. A rotor assembly in accordance with claim 14 wherein at least one of said plurality of mechanical fuses is configured to fail at a predetermined moment load. 16. A rotor assembly in accordance with claim 14 wherein at least one of said plurality of mechanical fuses couples said mounting joint inner race to said mounting joint outer race. 17. A rotor assembly in accordance with claim 14 wherein said bearing assembly mounting joint is between said bearing assembly inner race and said rotor shaft. 18. A rotor assembly in accordance with claim 14 wherein said mounting joint is between said cone shaft and said rotor shaft. 19. A rotor assembly in accordance with claim 14 wherein said bearing assembly is configured to maintain rotor assembly frequency above a windmill frequency. 20. A rotor assembly in accordance with claim 14 wherein said mounting joint is configured to reduce dynamic loads to said support frame and static bending to said rotor shaft.