Abstract: The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

Abstract: A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

Abstract: The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

Abstract: A double flow turbojet including: a low pressure compressor; a series of casings downstream of this low pressure compressor to delimit a primary flow path for circulating a primary stream, and including an upstream edge delimiting an inlet opening; a high pressure compressor in the primary flow path; a shroud surrounding the series of casings to delimit a flow path for circulating an intermediate stream, and having an upstream edge delimiting a circular inlet opening situated upstream of the high pressure compressor; a secondary flow path casing surrounding the shroud to delimit a secondary flow path for circulating a secondary stream; an exhaust casing including radial arms collecting the air coming from the intermediate flow path.

Abstract: A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-balance appears. Because it is positioned a long way from the bearing, the decoupler (15) can be designed with a greater degree of freedom at a location where there is more space available and where layout constraints are less of an issue. More specifically, it is housed in a cavity (30) of the external casing (13) which opens onto the flow path (5).

Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Abstract: A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

Abstract: A turbojet includes an inlet casing, a low pressure compressor, a high pressure spool, a low pressure turbine, and an exhaust casing. The inlet casing and the low pressure compressor define an air inlet channel that divides downstream into a primary flow channel and a secondary flow channel. A low pressure shaft is supported by a first roller bearing, borne by the inlet casing, a second bearing borne by the intermediate casing, a third bearing borne by the exhaust casing, and an additional ball bearing borne by the intermediate casing and arranged between the first bearing and the second bearing. Such a configuration of bearings makes it possible to withstand an increased level of load and to be compatible with an increase in the rate of dilution.

Abstract: The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY?) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

Abstract: An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Abstract: An aircraft includes a wing having a first upstream spar and a second downstream spar extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream spar via at least one first and second fastener.

Abstract: The invention relates to a turbomachine (1), such as an aircraft turbojet or turboprop, extending along an axis (X), comprising a primary flow jet (2) comprising at least one compressor (4, 5), at least one combustion chamber (6) and at least one turbine (7, 8), and a secondary flow jet (3) located radially outside the primary flow jet (2), at least one duct (18) for the flow of cooling air, said duct (18) comprising an air inlet opening into the primary flow jet (2), at the compressor (4, 5), and an air outlet opening into the primary flow jet (2), at the turbine (7, 8).

Abstract: A turbojet includes an inlet casing, a low pressure compressor, a high pressure spool, a low pressure turbine, and an exhaust casing. The inlet casing and the low pressure compressor define an air inlet channel that divides downstream into a primary flow channel and a secondary flow channel. A low pressure shaft is supported by a first roller bearing, borne by the inlet casing, a second bearing borne by the intermediate casing, a third bearing borne by the exhaust casing, and an additional ball bearing borne by the intermediate casing and arranged between the first bearing and the second bearing. Such a configuration of bearings makes it possible to withstand an increased level of load and to be compatible with an increase in the rate of dilution.

Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

Abstract: A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.

Abstract: The invention relates to a double flow turbojet including: a low pressure compressor; a series of casings downstream of this low pressure compressor to delimit a primary flow path for circulating a primary stream, and including an upstream edge delimiting an inlet opening; a high pressure compressor in the primary flow path; a shroud surrounding the series of casings to delimit a flow path for circulating an intermediate stream, and having an upstream edge delimiting a circular inlet opening situated upstream of the high pressure compressor; a secondary flow path casing surrounding the shroud to delimit a secondary flow path for circulating a secondary stream; an exhaust casing including radial arms collecting the air coming from the intermediate flow path.

Abstract: A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-balance appears. Because it is positioned a long way from the bearing, the decoupler (15) can be designed with a greater degree of freedom at a location where there is more space available and where layout constraints are less of an issue. More specifically, it is housed in a cavity (30) of the external casing (13) which opens onto the flow path (5).

Abstract: An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Abstract: A device for lubricating a turbomachine rolling bearing includes a rolling bearing mounted between an internal component and an external component. The bearing has rolling elements mounted between an outer ring secured to the external component and an inner ring secured to the internal component. The internal component includes at least one first duct for the passage of oil for supplying the internal ring of the bearing with oil, wherein the internal component is a stator component and at least one first duct is connected to an oil supply source configured to deliver the oil at a pressure high enough that this oil can be conveyed as far as the rolling elements of the bearing.

Abstract: An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.