| Patent application number | Description | Published |
|---|
| 20080247877 | TURBOPROP HAVING A PROPELLER MADE UP OF VARIABLE-PITCH BLADES - A turboprop having a set of variable-pitch rotary blades constrained to rotate with a rotary support. In order to vary its pitch, each blade of said set is coupled to a specific hydraulic actuator carried by the rotary support. | 10-09-2008 |
| 20090311100 | TURBOPROP INCLUDING A SET OF ADJUSTABLE-PITCH BLADES - A turboprop including a rotary casing fitted with adjustable-pitch blades enabling thrust to be managed. Each blade is coupled, for the purpose of adjusting its pitch, to a control member of an annular actuator carried by the rotary casing. | 12-17-2009 |
| 20100104438 | DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP - The invention relates to a device for controlling the pitch of fan blades of a turboprop. The device includes at least at least one set of adjustable pitch fan blades secured to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor. Each blade of the set is coupled for pitch-adjustment purposes with a synchronization ring centered on the longitudinal axis, the synchronization ring being suitable for pivoting about the longitudinal axis relative to the rotary ring under drive from actuators carried by the rotary ring and each having a respective axis extending in a direction that is substantially tangential to the synchronization ring. | 04-29-2010 |
| 20100205934 | BYPASS ENGINE WITH CONTRAROTATING TURBINE WHEELS - Bypass aeronautical engine comprising a fan ( | 08-19-2010 |
| 20110014046 | SYSTEM OF COUNTER-ROTATING PROPELLERS WITH A FEATHERING DEVICE FOR PROPELLER BLADES - A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering. | 01-20-2011 |
| 20110070086 | SIMPLIFIED SYSTEM FOR CONTROLLING PROPELLER BLADE PITCH IN AN AIRCRAFT TURBOSHAFT ENGINE - A system for controlling propeller blade pitch in a turboshaft engine, including: a first track connected to a propeller blade, of which the rotation provides for the setting of the incidence of this blade; a second track; a member actuating the first track, arranged between the first and second tracks, and having a recessed angular portion; and at least one locking member provided between the first and second tracks, housed in the recessed angular portion and in the notch. The locking member can occupy a normal over-center position rendering the first and second tracks integral in rotation, and a release position authorizing the displacement in rotation of a unit including the first track, the locking member, and the actuating member. | 03-24-2011 |
| 20110076143 | SIMPLIFIED SYSTEM FOR CONTROLLING PROPELLER BLADE PITCH IN AN AIRCRAFT TURBOSHAFT ENGINE - A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions. | 03-31-2011 |
