Nacelle for an aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and of a variable-section nozzle

Patent metadata

Field	Value
Publication number	US-10190605-B2
Application number	US-201816010750-A
Country	US
Kind code	B2
Filing date	Jun 18, 2018
Priority date	Dec 17, 2015
Publication date	Jan 29, 2019
Grant date	Jan 29, 2019

Abstract

The present disclosure concerns a nacelle for an aircraft turbojet engine that includes a thrust reverser having a cowl displaceable between a deployed position and a stowed position, a fixed structure, and a secondary nozzle. The nozzle includes panels movable in rotation, and hydraulic actuators for sequenced actuation of the cowl and panels. The actuators include a body mounted on the fixed structure, and a rod mounted in the body and is linked to the cowl and panels via a device for transmitting movement of the actuator to the panel. An actuation system having a hydraulic control device controls the displacement of the rod of the actuator. The actuator further includes a device for alternately displacing the rod in translation relative to the body to cause translation of the cowl, or in rotation relative to the body to cause rotation of the nozzle panel.

First claim

What is claimed is:

1. A nacelle for an aircraft turbojet engine comprising:
a thrust reverser including a cowl displaceable between a deployed position which opens a passage in the nacelle for diverting air flow, and a stowed position which closes the passage;
a fixed structure relative to said cowl; and
a variable-section secondary nozzle comprising a plurality of panels or flaps movable in rotation;
a plurality of hydraulic actuators operable to sequentially actuate said cowl and said panels or flaps, each hydraulic actuator comprising a body mounted on said fixed structure, and a rod mounted in said body, and linked to said cowl and said panels or flaps via a movement transmission device, wherein the movement transmission device transmits movement of said hydraulic actuator to said panels or flaps; and
at least one actuation system for powering said hydraulic actuators, the at least one actuation system comprising a hydraulic control device connected to said hydraulic actuators and adapted to control displacement of the rods of the hydraulic actuators,
wherein said hydraulic actuators each comprise a displacement device which alternately displaces the rod in translation relative to said body to cause translation of the thrust reverser cowl or in rotation relative to said body to cause rotation of said panels or flaps of the variable-section secondary nozzle.

2. The nacelle according to claim 1 , wherein each of the plurality of hydraulic actuators comprise the movement transmission device adapted to transmit translational and rotational movement of the rod of said hydraulic actuator to an external actuator external to said hydraulic actuators in a synchronized manner.

3. The nacelle according to claim 1 , wherein each displacement device comprises:
a longitudinal groove arranged inside the rod;
a rotary inner axis, blocked in translation relative to the body, and comprising a slide engaging the longitudinal groove; and
an inner axis driving system to drive the rotary inner axis in rotation.

4. The nacelle according to claim 3 , wherein the inner axis driving system comprises: a rotary piston adapted to mesh with the rotary inner axis; and a piston driving system to drive the rotary piston in rotation.

5. The nacelle according to claim 4 , wherein the inner axis driving system comprises:
a set of teeth arranged outside the rotary piston;
a set of teeth arranged inside the body, and adapted to mesh with the set of teeth outside the rotary piston; and
a plurality of orifices for introducing a fluid, and arranged in said body on either side of said rotary piston, wherein said body meshes with said rotary inner axis via a set of teeth arranged inside the rotary piston, the set of teeth inside the rotary piston meshing with a set of teeth arranged outside the rotary inner axis.

6. The nacelle according to claim 5 , wherein the set of teeth outside the rotary piston are simple- or multi-pitch helical teeth.

7. The nacelle according to claim 5 , wherein the set of teeth outside the rotary piston are reverse-pitch helical teeth.

8. The nacelle according to claim 5 , wherein each of the plurality of hydraulic actuators further comprise a spring configured to resist displacement of the rotary piston according to a direction of displacement of said rotary piston.

9. The nacelle according to claim 2 , wherein the movement transmission device comprises:
a synchronization screw including a set of teeth arranged outside said synchronization screw;
a nut mounted inside the rod, the nut configured to mesh with the set of teeth of said synchronization screw;
a worm gear system adapted to receive a flexible shaft system, the flexible shaft system operable to link the worm gear system of the hydraulic actuator to the worm gear system of the external actuator external to said hydraulic actuator; and
a set of rotary bearings for supporting said synchronization screw, said bearings arranged on either side of said worm gear system to block translation of the synchronization screw relative to the body of the hydraulic actuator.

10. The nacelle according to claim 1 , wherein the at least one actuation system comprises:
a hydraulic supply doubled with hydraulic supply circuits; and
control units supplying adjacent actuators of the plurality of hydraulic actuators of the thrust reverser cowl, the control units configured to cause the rods of the plurality of hydraulic actuators to rotate.

11. The nacelle according to claim 10 , wherein the control units of the at least one actuation system each comprise a three-way servovalve supplying the bodies of the plurality of hydraulic actuators via a first orifice and an isolation valve supplying the bodies of the plurality of hydraulic actuators via a second orifice.

12. The nacelle according to claim 10 , wherein the control units of the at least one actuation system are equipped with four-way servovalves.

13. The nacelle according to claim 11 , wherein the control units of the at least one actuation system are equipped with switch type solenoid-valves capable of pressurizing the plurality of hydraulic actuators via the first orifice or the second orifice.

14. The nacelle according to claim 1 , wherein the at least one actuation system comprises at least one anti-shock relief valve operable to release pressure induced by undesirable forces of the variable-section secondary nozzle panels or flaps.

15. The nacelle according to claim 1 further comprising a flexible shaft linked between a first actuator of the plurality of hydraulic actuators of the thrust reverser cowl, and a second actuator of the plurality of hydraulic actuators of the thrust reverser cowl, wherein the second actuator is adjacent to the first actuator such that translational and rotational movement of the rod of the first actuator synchronizes with translational and rotational movement of the rod of the second actuator.

16. The nacelle according to claim 15 further comprising a complementary flexible shaft linking:
the movement transmission device for transmitting movement of the first actuator to at least one of the plurality of panels or flaps of the variable-section secondary nozzle, and
the movement transmission device for transmitting movement of the second actuator to at least one of the plurality of panels or flaps of the variable-section secondary nozzle,
wherein the complementary flexible shaft is configured to synchronize the movement of the movement transmission device of the first and second actuators.

Assignees

• Safran Nacelles

Inventors

• Le Coq Vincent

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F15B11/22

  Synchronisation of the movement of two or more servomotors · CPC title

• F15B15/261

  using positive interengagement, e.g. balls and grooves, for locking in the end positions · CPC title

• F15B2211/72

  having locking means · CPC title