Importance

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Abstract

The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine (10) defines an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly (14) includes a gearbox (45). The turbine engine (10) includes a coupling shaft (100), a spacer (150), a sleeve (200), and a nut (250) in adjacent radial arrangement. The coupling shaft (100) is connected at a first end (97) to the engine core (20) and coupled at a second end (96) to the gearbox (45). The coupling shaft (100) defines an annular surface (103) extended along the axial direction and a groove (104) extended in a circumferential direction. The spacer (150) defines a first portion (151) extended inward in the radial direction and a second portion (152) extended in the axial direction. The first portion (151) is disposed in the groove (104) of the coupling shaft (100). The sleeve (200) defines a threaded portion (202) comprising a plurality of sleeve threads (204) defined outwardly in the radial direction. The threaded portion (202) extends along the axial direction and is disposed outward of the (spacer 150) in the radial direction. The nut (250) defines a plurality of nut threads (252) defined inwardly in the radial direction. The plurality of nut threads (252) of the nut (250) is configured to mate with the plurality of sleeve threads (204) of the sleeve (200). The (nut 250) defines a radial portion (254) extended inward in the radial direction. The radial portion (254) is adjacent to at least a portion of the sleeve (200) and at least a portion of the spacer (150) in the axial direction.

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First Claim