Abstract: The present application relates to compounds according to Formula (I), pharmaceutical compositions comprising at least one of said compounds, their use as a medicament, and their use in treating chronic hepatitis B virus (HBV) infection. The disclosure further pertains to methods for preparing compounds according to Formula (I).

Abstract: The invention relates to an assembly including a one-piece bladed disk (1), at least one low-pressure compressor rotor (2) and a low-pressure compressor shaft, characterized in that the bladed disk and the low-pressure compressor rotor (2) are both adapted to be shrunk onto the low-pressure compressor shaft and mechanically attached to it by sets of splines. At least one clamping member (16) blocks axially the different collars with respect to the shaft.

Abstract: A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

Abstract: A turbine engine including a power gear box shaft, a turbine shaft, a connecting part of annular shape by which one end of the power gear box shaft and one end of the turbine shaft are connected in a rotationally fixed manner, a structural housing, and a guide bearing for guiding the connecting part relative to the housing, is provided. The guide bearing is mounted between the connecting part and the housing and includes an external ring mounted on the housing, an internal ring mounted on the connecting part, and at least one rolling element configured to enable the external ring to roll around the internal ring. The guide bearing is configured to form a ball joint link enabling a relative angular displacement of its external ring with respect to its internal ring.

Abstract: The device is intended to supply a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller, according to separate operating states, from a rotary power assembly, the device being arranged so as to be located between the power assembly and the actuator, along a longitudinal axis, and being connected in rotation therewith. According to the invention, the device comprises supplies for supplying fluid interacting with the power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor to which the supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by a tubular equipment connected to the distributor.

Abstract: Lubrication system for a device (13) located between an internal shaft (12a) and an external shaft (12b) of an aircraft turbine (10), that are free to rotate, concentric and arranged at least partially one (12b) around the other (12b), comprising an annular element (30) provided with an external groove (31) and being configured so that it can be mounted integral with the external shaft (12b), the external groove (31) being designed to be supplied with lubricant from a fixed part of the turbine (10), a grooved element (25) configured to be mounted integral with the internal shaft (12a), the grooved element (25) having relief (70) designed to direct a lubricant in contact with its external surface along a longitudinal direction (A) when the internal shaft (12a) is rotating, the external groove (31) being in fluid communication with an external surface (70) of the grooved element (25) through at least two conduits (22) arranged through the external shaft (12b).

Abstract: Turbine engine (1), especially for aircraft, comprising a power gear box shaft (30), a turbine shaft (28), and a connecting part (38) of annular shape by which one end of the power gear box shaft (30) and one end of the turbine shaft (28) are connected in a rotationally fixed manner, the turbine engine also including a structural housing (3) and a guide bearing (44) for guiding the connecting part (38) relative to the housing (3), the guide bearing (44) being mounted between the connecting part (38) and the housing (3) and comprising an external ring (48) mounted on the housing (3), an internal ring (46) mounted on the connecting part (38) and at least one rolling element (50a, 50b) configured in order to enable the external ring (48) to roll around the internal ring (46), characterised in that the guide bearing (44) is configured in order to form a ball joint link (R) enabling a relative angular displacement of its external ring with respect to its internal ring.

Abstract: The device (18) is intended to supply a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller, according to separate operating states, from a rotary power assembly, the device being arranged so as to be located between the power assembly and the actuator, along a longitudinal axis (A), and being connected in rotation therewith. According to the invention, the device comprises means (20) for supplying fluid interacting with said power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor (21) to which said supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by means of tubular equipment (25) connected to the distributor.