US-12618380-B2 - Variable area nozzle for an aircraft engine

Abstract

A variable area nozzle for an aircraft engine includes a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath. The nozzle inner structure includes a nozzle wall and a nozzle sleeve. The nozzle wall includes a plurality of slots arranged circumferentially about the axis. Each of the slots projects radially through the nozzle wall. The nozzle sleeve axially overlaps and circumscribes the nozzle wall. The actuation system includes a carriage and an actuator. The carriage includes a hub and a plurality of struts arranged circumferentially about and connected to the hub. Each of the struts projects radially through a respective slot where the nozzle sleeve is attached to the carriage at an outer end of the carriage. The actuator is disposed radially within the inner nozzle wall and is coupled to the hub. The actuation system moves the nozzle sleeve axially along the nozzle wall.

Inventors

• Michael G. McCaffrey

Assignees

• RTX CORPORATION

Dates

Publication Date

20260505

Application Date

20240112

Claims (20)

1. 1 . An apparatus for an aircraft engine, comprising: a variable area nozzle including a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath extending axially along an axis through the variable area nozzle and radially between the nozzle inner structure and the nozzle outer structure; the nozzle inner structure including a nozzle wall and a nozzle sleeve, the nozzle wall extending axially along and circumferentially around the axis, the nozzle wall comprising a plurality of slots arranged circumferentially about the axis, each of the plurality of slots projecting radially through the nozzle wall, and the nozzle sleeve axially overlapping and circumscribing the nozzle wall; and the actuation system including a carriage and an actuator, the carriage including a hub, a plurality of struts, an outer platform, and an outer bearing, the plurality of struts arranged circumferentially about and connected to the hub, each of the plurality of struts projecting radially through a respective one of the plurality of slots wherein the nozzle sleeve is attached to the carriage at an outer end of the carriage, the outer platform radially outboard of the nozzle wall with each of the plurality of struts projecting radially in from the outer platform, the outer bearing radially between and engaged with the outer platform and the nozzle wall, the actuator disposed radially within the inner nozzle wall and coupled to the hub, and the actuation system configured to move the nozzle sleeve axially along the nozzle wall.
2. 2 . The apparatus of claim 1 , wherein the carriage further includes a rim forming the outer end of the carriage, and the nozzle sleeve is attached to the rim; and each of the plurality of struts extends radially across the nozzle wall between the hub and the rim.
3. 3 . The apparatus of claim 1 , wherein the outer bearing comprises a bushing.
4. 4 . The apparatus of claim 1 , wherein the carriage is attached to a portion of the nozzle sleeve with a frustoconical geometry.
5. 5 . The apparatus of claim 1 , wherein the carriage is attached to a portion of the nozzle sleeve with a cylindrical geometry.
6. 6 . The apparatus of claim 1 , wherein the nozzle sleeve extends axially between an upstream end and a downstream end; and the carriage is attached to the nozzle sleeve at a location axially closer to the downstream end than the upstream end.
7. 7 . The apparatus of claim 6 , wherein the downstream end is radially spaced from the nozzle wall by an annular gap.
8. 8 . The apparatus of claim 6 , wherein a portion of the nozzle sleeve at the upstream end abuts radially against and is configured to slide along the nozzle wall.
9. 9 . The apparatus of claim 1 , wherein the nozzle sleeve extends axially between an upstream end and a downstream end; and an outer surface of the nozzle sleeve radially tapers inward towards the axis as the nozzle sleeve extends axially towards the downstream end.
10. 10 . The apparatus of claim 1 , wherein the nozzle inner structure further includes a mount; the nozzle wall circumscribes and is connected to the mount; and the actuator is coupled to the mount, and the actuator extends axially between the mount and the carriage.
11. 11 . The apparatus of claim 1 , wherein the actuator comprises a linear actuator.
12. 12 . The apparatus of claim 1 , wherein the variable area nozzle is configured as a convergent-divergent nozzle.
13. 13 . An apparatus for an aircraft engine, comprising: a variable area nozzle including a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath extending axially along an axis through the variable area nozzle and radially between the nozzle inner structure and the nozzle outer structure; the nozzle inner structure including a nozzle wall and a nozzle sleeve, the nozzle wall extending axially along and circumferentially around the axis, the nozzle wall comprising a plurality of slots arranged circumferentially about the axis, each of the plurality of slots projecting radially through the nozzle wall, and the nozzle sleeve axially overlapping and circumscribing the nozzle wall; and the actuation system including a carriage and an actuator, the carriage including a hub, a plurality of struts, an inner platform, and an inner bearing, the plurality of struts arranged circumferentially about and connected to the hub, each of the plurality of struts projecting radially through a respective one of the plurality of slots wherein the nozzle sleeve is attached to the carriage at an outer end of the carriage, the actuator disposed radially within the inner nozzle wall and coupled to the hub, and the actuation system configured to move the nozzle sleeve axially along the nozzle wall; wherein the inner platform is radially inboard of the nozzle wall with each of the plurality of struts projecting radially out from the inner platform; and wherein the inner bearing is radially between and engaged with the inner platform and the nozzle wall.
14. 14 . The apparatus of claim 13 , wherein the inner bearing comprises a bushing.
15. 15 . The apparatus of claim 13 , wherein the carriage is attached to a portion of the nozzle sleeve with a frustoconical geometry.
16. 16 . The apparatus of claim 13 , wherein the carriage is attached to a portion of the nozzle sleeve with a cylindrical geometry.
17. 17 . The apparatus of claim 13 , wherein the nozzle sleeve extends axially between an upstream end and a downstream end; and the carriage is attached to the nozzle sleeve at a location axially closer to the downstream end than the upstream end.
18. 18 . The apparatus of claim 13 , wherein the nozzle sleeve extends axially between an upstream end and a downstream end; and an outer surface of the nozzle sleeve radially tapers inward towards the axis as the nozzle sleeve extends axially towards the downstream end.
19. 19 . The apparatus of claim 13 , wherein the nozzle inner structure further includes a mount; the nozzle wall circumscribes and is connected to the mount; and the actuator is coupled to the mount, and the actuator extends axially between the mount and the carriage.
20. 20 . The apparatus of claim 13 , wherein the actuator comprises a linear actuator.

Description

BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to an aircraft engine and, more particularly, to a variable area nozzle for the aircraft engine. 2. Background Information An aircraft engine may include a variable area nozzle. Various types and configurations of variable area nozzles are known in the art. While these known variable area nozzles have various benefits, there is still room in the art for improvement. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, an apparatus is provided for an aircraft engine. This apparatus includes a variable area nozzle. The variable area nozzle includes a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath extending axially along an axis through the variable area nozzle and radially between the nozzle inner structure and the nozzle outer structure. The nozzle inner structure includes a nozzle wall and a nozzle sleeve. The nozzle wall extends axially along and circumferentially around the axis. The nozzle wall includes a plurality of slots arranged circumferentially about the axis. Each of the slots projects radially through the nozzle wall. The nozzle sleeve axially overlaps and circumscribes the nozzle wall. The actuation system includes a carriage and an actuator. The carriage includes a hub and a plurality of struts arranged circumferentially about and connected to the hub. Each of the struts projects radially through a respective one of the slots where the nozzle sleeve is attached to the carriage at an outer end of the carriage. The actuator is disposed radially within the inner nozzle wall and is coupled to the hub. The actuation system is configured to move the nozzle sleeve axially along the nozzle wall. According to another aspect of the present disclosure, another apparatus is provided for an aircraft engine. This apparatus includes a variable area nozzle. The variable area nozzle includes a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath extending axially through the variable area nozzle. The nozzle inner structure includes a nozzle wall and a nozzle sleeve. The nozzle wall extends axially along and circumferentially around an axis. The nozzle wall is configured to radially locate and support the nozzle sleeve. The nozzle sleeve extends axially along and circumferentially around the nozzle wall. The nozzle wall and the nozzle sleeve collectively form an inner peripheral boundary of the flowpath through the variable area nozzle. The nozzle outer structure forms an outer peripheral boundary of the flowpath through the variable area nozzle. The actuation system includes an actuator located radially within the nozzle wall. The actuator is operatively coupled to the nozzle sleeve radially across the nozzle wall. The actuation system is configured to translate the nozzle sleeve axially along the nozzle wall using the actuator. According to still another aspect of the present disclosure, another apparatus is provided for an aircraft engine. This apparatus includes an inner structure, an outer structure and an actuation system. The inner structure includes a wall and a sleeve. The wall extends axially along and circumferentially around an axis. The wall is configured to radially locate and support the sleeve. The sleeve extends axially along and circumferentially around the wall. The wall and the sleeve collectively form an inner peripheral boundary of a flowpath. The outer structure extends axially along and circumferentially about the inner structure. The outer structure forms an outer peripheral boundary of the flowpath. The actuation system includes an actuator and a carriage operatively coupling the actuator to the sleeve radially across the wall. The actuator is arranged within an internal volume of the inner structure radially inboard of the wall. The actuation system is configured to translate the sleeve axially along the wall between a first position and a second position. The actuation system may also include a carriage operatively coupling the actuator to the nozzle sleeve. The carriage may be radially engaged with and may be configured to translate axially along the nozzle wall. The actuation system may also include a carriage operatively coupling the actuator to the nozzle sleeve. The carriage may be configured to transfer radial loads between the nozzle sleeve and the nozzle wall. The actuation system may also include a carriage operatively coupling the actuator to the nozzle sleeve. A portion of the carriage may project radially through an aperture in the nozzle wall. The carriage may also include a rim forming the outer end of the carriage. The nozzle sleeve may be attached to the rim. Each of the struts may extend radially across the nozzle wall between the hub and the rim. The carriage may also include an inner platform and an inner bearing. The inner platform may be radially inboard of the nozzle wall with each of the st