A mechanism for driving a first member for adjusting the orientation of the blades of a first stage of a turbine engine diffuser and a second member for adjusting the orientation of the blades of a second stage of the turbine engine diffuser, including a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and a set of gears which is arranged between the drive wheel and the two adjustment members, wherein the set of gears includes a first gearwheel which is directly coupled with the drive wheel and with the first adjustment member and which is coupled with the second adjustment member with a secondary gearwheel which is directly coupled with the second adjustment member.

A device for driving an integrated generator from an accessories relay box of a turbomachine. The device includes first and second electric motors arranged to transfer electric power from one to the other, one or more controllers configured for controlling said electric motors, and an epicyclic reduction gear train. The gear train includes a first element intended to be coupled to the accessories relay box, a second element intended to be coupled to the generator, and a third element driven to rotate by said first electric motor. The control means are configured to modify the speed of rotation of the third element in such a way that the second element is driven to rotate at a constant speed.

A turbofan engine with a nacelle including a runner translationally mobile between advanced and back-off positions to open a window between a stream and an outside, a plurality of blades, each rotatable on the runner between retracted and deployed positions, and a maneuvering system displacing each blade and comprising, for each blade, a shaft rotatable on the runner and to which the blade is fixed, and a toothed segment on the shaft, and a toothed arc rotatable on the runner about a longitudinal axis, the tooth arc teeth meshing with the toothed segment teeth, a slip translationally mobile on the runner in a plane at right angles to the longitudinal axis between first and second positions, a connecting rod mounted articulated between the slip and the toothed arc, a rib integral to the fixed structure, and a guiding U integral to the slip and which straddles the rib.

An aeronautical propulsion device including a fan and a plurality of variable guide vanes is provided. The fan includes a plurality of fan blades for providing a flow of air and the plurality of variable guide vanes are configured for directing air to or from the fan in a desired direction. Each of the plurality of guide vanes defines an inner end along the radial direction and is attached to a housing of the portion device at the inner end in a rotatable manner. The propulsion device further includes a pitch change mechanism positioned in the housing and mechanically coupled to at least one of the plurality of guide vanes for changing a pitch of the at least one of the plurality of guide vanes.

An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

The subject matter of this specification can be embodied in, among other things, an actuator that includes a worm drive assembly having a worm shaft, and a worm wheel configured as a ring having a radially outer perimeter comprising a first collection of gear teeth extending radially outward from the radially outer perimeter and at least partly engaged with the worm shaft, and a coaxial radially inner perimeter comprising a second collection of gear teeth extending radially inward from the inner perimeter, and an epicyclic gear assembly having a sun gear and a planet gear engaged with the sun gear and the second collection of gear teeth.

A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

An assembly is provided for an aircraft propulsion system. This assembly includes a first actuator, a second actuator and a linkage system. The linkage system is configured to transfer torque between the first actuator and the second actuator. The linkage system includes a first linkage shaft, a second linkage shaft and a gearbox. The first linkage shaft has a first centerline. The second linkage shaft has a second centerline offset from the first centerline. The gearbox is coupled to and is between the first linkage shaft and the second linkage shaft.

A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.

A bypass turbofan engine comprising a nacelle surrounding a flow path for a secondary flow and comprising a fixed structure, a mobile assembly with a slide capable of translational movement on the fixed structure and bearing a mobile cowl and a frame capable of translational movement on the fixed structure and bearing deflectors. The mobile assembly is able to move between a forward position and a retreated position making it possible to open a passage between the flow path and the outside through the deflectors. A differentiation mechanism ensures a length of travel of the slide that is different from the length of travel of the frame, and actuators providing a translational travel of the slide. Fitting a differentiation mechanism means that the length of travel of the deflectors with respect to the length of travel of the mobile cowl can be regulated.