Exhaust nozzle of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11215140-B2
Application number	US-201916719001-A
Country	US
Kind code	B2
Filing date	Dec 18, 2019
Priority date	Dec 18, 2019
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems.

First claim

The invention claimed is:

1. An exhaust nozzle of a gas turbine engine, wherein the exhaust nozzle comprises:
a nozzle wall, the nozzle wall comprising an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure,
a flow channel which is limited radially outwards by the nozzle wall,
a centerbody arranged in the flow channel,
at least one strut connecting the centerbody to the nozzle wall,
a thrust reverser unit that comprises blocking doors,
a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and
a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position,
wherein the at least one strut is connected to the fixed structure,
wherein the blocking doors are connected to the translatable structure, and
wherein the first actuation system and the second actuation system are independent actuation systems;
wherein the first actuation system comprises a motor, a profiled feed shaft driven by the motor, and a slider element that is both axially displaceable along a length of the profiled feed shaft and rotatable by rotation of the profiled feed shaft, and wherein the slider element is coupled to at least one element that transfers the rotation of the slider element to at least one of the blocking doors.

2. The exhaust nozzle of claim 1 , wherein the nozzle wall comprises cascades which are configured to receive air from an interior of the nozzle and deflect the air towards an exterior front of the nozzle, wherein the cascades are fixed to the fixed structure of the nozzle wall.

3. The exhaust nozzle of claim 2 , wherein, when the translatable structure of the nozzle wall is in the upstream position, the cascades are covered by the translatable structure, and when the translatable structure of the nozzle wall is in the downstream position, the cascades are free to receive the air from the interior of the nozzle.

4. The exhaust nozzle of claim 3 , wherein the translatable structure of the nozzle wall comprises an outer extending wall element and an inner extending wall element, wherein, when the translatable structure is in the upstream position, the outer extending wall element is adjacent to the cascades to the exterior and the inner extending wall element is adjacent to the cascades to the interior.

5. The exhaust nozzle of claim 3 , wherein, when the translatable structure of the nozzle wall is in the downstream position, and when the first actuation system has been actuated to deploy the blocking doors, the cascades are free to receive the air turned by the deployed blocking doors.

6. The exhaust nozzle of claim 1 , wherein the first actuation system is configured to deploy the blocking doors only when the translatable structure is in the downstream position.

7. The exhaust nozzle of claim 1 , wherein the blocking doors are located at the interior of the translatable structure of the nozzle wall in the non-deployed position, and are pivotable by the first actuation system into the deployed position in which the blocking doors point towards a centerline of the nozzle, wherein pivot points of the blocking doors are located in the translatable structure.

8. The exhaust nozzle of claim 7 , wherein, when the blocking doors are deployed, inner ends of the blocking doors lie next to the centerbody.

9. The exhaust nozzle of claim 1 , wherein the slider element has a same interior profile as the profiled feed shaft to cause the slider element to be both axially displaceable along the length of the profiled feed shaft and rotatable by the rotation of the profiled feed shaft.

10. The exhaust nozzle of claim 1 , wherein the slider element is coupled to two coupling shafts whose axes are inclined to an axis of the profiled feed shaft and to each other, wherein each coupling shaft transfers the rotation of the profiled feed shaft to the at least one of the blocking doors.

11. The exhaust nozzle of claim 10 , wherein the slider element comprises a worm screw which interacts with a toothing formed around a circumference of the coupling shafts.

12. The exhaust nozzle of claim 10 , wherein the coupling between the slider element and the two coupling shafts integrates a reduction function such that the coupling shafts rotate slower than the profiled feed shaft.

13. The exhaust nozzle of claim 10 , wherein the blocking doors of the thrust reverser unit comprises more than two blocking doors, where the at least one of the blocking doors is coupled to a further one of the blocking doors by a joint to transfer the rotation of the profiled feed shaft to the further one of the blocking doors.

14. The exhaust nozzle of claim 13 , wherein the blocking doors are coupled to each other to form two half-circular arrangements, wherein each of the two half-circular arrangements of the blocking doors is coupled to the slider element.

15. The exhaust nozzle of claim 1 , wherein the translatable structure of the nozzle wall and the fixed structure of the nozzle wall comprise elements which, when the translatable structure is in the upstream position, overlap in an axial, circumferential and/or radial direction.

16. The exhaust nozzle of claim 1 , wherein the first actuation system is positioned in an inboard area of the nozzle.

17. The exhaust nozzle of claim 1 , wherein the at least one strut that connects the centerbody to the nozzle wall is connected in a fixed manner to the fixed structure of the nozzle wall.

18. The exhaust nozzle of claim 1 , wherein the second actuation system comprises a plurality of actuators, each actuator comprising a shaft or piston that is axially displaceable to move the translatable structure of the nozzle wall relative to the fixed structure of the nozzle wall.

19. The exhaust nozzle of claim 1 , wherein the second actuation system is configured to move the translatable structure into the stowed position when the aircraft speed surpasses a defined value.

20. The exhaust nozzle of claim 1 , wherein the slider element rotates with the profiled feed shaft as the slider element axially displaces along the profiled feed shaft.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag

Classifications

• F02K1/54 Primary

  Nozzles having means for reversing jet thrust (reversing jet thrust using fluid jets F02K1/32) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title