Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

Abstract: A gearbox comprising a main unit comprising a first casing and a first hollow shaft, and a secondary unit comprising a second casing and a second hollow shaft, and a drive shaft comprising a first clutch portion and a second clutch portion, which engage the first and second hollow shafts in an angularly fixed and axially sliding manner. The gearbox further including an axial retaining device comprising an axial shoulder supported in a fixed potion by an axial end on one of the first or second hollow shafts, and an external radial projection arranged in an intermediate position, and an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions.

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.

Abstract: A turbine engine defines an axial direction and a radial direction and includes a shaft assembly, a fan or propeller assembly, an engine core, a coupling shaft, a spacer, a sleeve, and a nut The coupling shaft defines an annular surface extended along the axial direction and a groove extended in a circumferential direction. The spacer defines a first portion disposed in the groove of the coupling shaft. The sleeve defines a threaded portion that extends along the axial direction and is disposed outward of the spacer in the radial direction. The nut defines a plurality of nut threads configured to mate with the plurality of sleeve threads of the sleeve. The nut defines a radial portion adjacent to at least a portion of the sleeve and at least a portion of the spacer in the axial direction.

Abstract: A system for feathering a propeller assembly disposed within a housing of the propeller assembly has a sleeve defining an outer wall and one or more sleeve tabs extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction, a retainer defining one or more retainer tabs extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall and the one or more sleeve tabs of the sleeve along the axial direction, and a beta tube assembly extended through the sleeve along the axial direction. The beta tube assembly defines one or more internal walls. The one or more internal walls defines a hydraulic fluid transfer cavity in fluid communication with one or more hydraulic fluid transfer orifices.

Abstract: A gearbox comprising a main unit comprising a first casing and a first hollow shaft, and a secondary unit comprising a second casing and a second hollow shaft, and a drive shaft comprising a first clutch portion and a second clutch portion, which engage the first and second hollow shafts in an angularly fixed and axially sliding manner. The gearbox further including an axial retaining device comprising an axial shoulder supported in a fixed portion by an axial end on one of the first or second hollow shafts, and an external radial projection arranged in an intermediate position, and an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions.

Abstract: A gearbox has a main unit and a secondary unit provided with respective casings of respective gear transmissions and with respective hollow shafts connected by means of a drive shaft; the secondary unit transfers motion between two axes forming an angle of less than 180° and which can be removed after having released the drive shaft; the drive shaft is engaged in an angularly fixed and axially sliding manner to the hollow shafts and is axially locked, at least in one direction, by means of an axial retaining device, which is releasable; the axial retaining device is coupled to one of the hollow shafts, at an axial end which is facing towards the other of the hollow shafts; at least one opening may be formed between the two casings, so as to access such an axial end and release the axial retaining device.

Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

Abstract: The present disclosure is directed to a system 100 for feathering a propeller assembly 14, wherein the system is disposed within a housing 47 of the propeller assembly. The system 100 includes a sleeve 110 defining an outer wall 111 and one or more sleeve tabs 115 extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction. The system 100 further includes a retainer 120 defining one or more retainer tabs 125 extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall 111 and the one or more sleeve tabs 115 of the sleeve 110 along the axial direction.

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).

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.

Abstract: A gearbox (1) has a main unit (22) and a secondary unit (2) provided with respective casings (23,3) of respective gear transmissions and with respective hollow shafts (24,10) connected by means of a drive shaft (25); the secondary unit transfers motion between two axes forming an angle of less than 180° and which can be removed after having released the drive shaft (25); the drive shaft (25) is engaged in an angularly fixed and axially sliding manner to the hollow shafts and is axially locked, at least in one direction, by means of an axial retaining device (57), which is releasable; the axial retaining device (57) is coupled to one (24) of the hollow shafts, at an axial end (32) which is facing towards the other (10) of the hollow shafts; at least one opening may be formed between the two casings (23,3), so as to access such an axial end (32) and release the axial retaining device.