Thrust reverser cascade with one or more flow disrupters

Patent metadata

Field	Value
Publication number	US-12270356-B2
Application number	US-202217878531-A
Country	US
Kind code	B2
Filing date	Aug 1, 2022
Priority date	Aug 1, 2022
Publication date	Apr 8, 2025
Grant date	Apr 8, 2025

Abstract

An apparatus is provided for an aircraft propulsion system. This apparatus includes a cascade structure including a thrust reverser cascade and a flow disruptor. The thrust reverser cascade extends longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between an inner face and an outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array along the inner face. The flow disruptor is arranged at the cascade inner face and forward of the vanes. The flow disruptor is configured to disrupt boundary layer air flowing towards the vanes.

First claim

What is claimed is:

1. An apparatus for an aircraft propulsion system, comprising:
a propulsion system structure including a flowpath and a pivoting door thrust reverser system;
the flowpath extending within the propulsion system structure to an exhaust nozzle;
the pivoting door thrust reverser system including a cascade structure and a thrust reverser door;
the cascade structure including a thrust reverser cascade and a flow disruptor;
the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, the thrust reverser cascade extending radially between an inner face and an outer face, and the thrust reverser cascade comprising a plurality of vanes arranged in a longitudinally extending array along the inner face;
the flow disruptor arranged at an inner aerodynamic flow surface of the inner face and forward of a bullnose for the plurality of vanes, the inner aerodynamic flow surface extending axially toward the cascade forward end, and the flow disruptor configured to disrupt boundary layer air flowing towards the plurality of vanes; and
the thrust reverser door configured to pivot outward into an environment external to the aircraft propulsion system and open an opening through the pivoting door thrust reverser system, and the thrust reverser door further configured to pivot inward into the flowpath to block the exhaust nozzle.

2. The apparatus of claim 1 , wherein the flow disruptor comprises a groove that extends radially into the cascade structure from the inner face.

3. The apparatus of claim 1 , wherein the flow disruptor comprises a protrusion that extends radially out from the inner face to a distal end.

4. The apparatus of claim 1 , wherein the flow disruptor is disposed at a leading edge of a ramp into the thrust reverser cascade.

5. The apparatus of claim 1 , wherein the flow disruptor is disposed at the cascade forward end.

6. The apparatus of claim 1 , wherein the flow disruptor extends laterally along the thrust reverser cascade.

7. The apparatus of claim 1 , wherein
the cascade structure further includes a second flow disruptor; and
the second flow disruptor is arranged at the inner face, forward of the plurality of vanes and laterally adjacent the flow disruptor.

8. The apparatus of claim 1 , wherein a longitudinal distance between the flow disruptor and a first of the plurality of vanes is constant as the flow disruptor extends laterally along the thrust reverser cascade.

9. The apparatus of claim 1 , wherein a longitudinal distance between the flow disruptor and a first of the plurality of vanes changes as the flow disruptor extends laterally along the thrust reverser cascade.

10. The apparatus of claim 1 , wherein
the plurality of vanes include a first vane, a second vane and a third vane;
the first vane is longitudinally spaced from the second vane by a first distance; and
the second vane is longitudinally between and neighbors the first vane and the third vane, and the second vane is longitudinally spaced from the third vane by a second distance that is different than the first distance.

11. The apparatus of claim 10 , wherein
the first vane is forward of the second vane;
the third vane is aft of the second vane; and
the second distance is less than the first distance.

12. The apparatus of claim 1 , wherein the inner face is angularly offset from the outer face.

13. The apparatus of claim 1 , wherein the thrust reverser cascade radially tapers as the thrust reverser cascade extends longitudinally between the cascade forward end and the cascade aft end.

14. The apparatus of claim 1 , wherein the thrust reverser cascade is exposed to the flowpath when the pivoting door thrust reverser system is stowed.

15. The apparatus of claim 1 , wherein
the thrust reverser door is configured to pivot outward from a stowed position into the environment external and to a deployed position; and
a first portion of the thrust reverser door is radially outboard of and axially overlaps the thrust reverser cascade when the thrust reverser door is in the stowed position.

16. An apparatus for an aircraft propulsion system, comprising:
a propulsion system structure including a flowpath and a thrust reverser system;
the flowpath extending within the propulsion system structure to an exhaust nozzle;
the thrust reverser system comprising a cascade structure and a thrust reverser door;
the cascade structure including a thrust reverser cascade and a groove;
the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, the thrust reverser cascade extending radially between an inner face and an outer face, the thrust reverser cascade comprising a plurality of vanes distributed along the inner face, and the plurality of vanes exposed to the flowpath when the thrust reverser door is in a stowed position;
the groove disposed forward of a ramp for the plurality of vanes, the groove extending radially into the cascade structure from the inner face, and the groove disposed at an axially extending portion of the cascade forward end; and
the thrust reverser door configured to pivot between the stowed position and a deployed position, a first portion of the thrust reverser door radially outboard of and axially covering the thrust reverser cascade when the thrust reverser door is in the stowed position, and a second portion of the thrust reverser door forming a radial outer peripheral boundary of the flowpath between the thrust reverser cascade and the exhaust nozzle when the thrust reverser door is in the stowed position.

17. The apparatus of claim 16 , wherein the groove extends laterally along an entire lateral length of the thrust reverser cascade.

18. The apparatus of claim 16 , wherein the groove is configured with a polygonal cross-sectional geometry.

19. An apparatus for an aircraft propulsion system, comprising:
a propulsion system structure including a flowpath and a thrust reverser system;
the flowpath extending within the propulsion system structure to an exhaust nozzle;
the thrust reverser system comprising a cascade structure and a thrust reverser door;
the cascade structure including a thrust reverser cascade and a fence;
the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, the thrust reverser cascade extending radially between an inner face and an outer face, the thrust reverser cascade comprising a plurality of vanes distributed along the inner face, and the plurality of vanes exposed to the flowpath when the thrust reverser door is in a stowed position;
the fence disposed at an axially extending portion of the cascade forward end, the fence disposed forward of a bullnose for the plurality of vanes, the fence extending radially out from the inner face to a distal end, and the fence extending laterally along the thrust reverser cascade; and
the thrust reverser door configured to pivot between the stowed position and a deployed position, a first portion of the thrust reverser door radially outboard of and axially covering the thrust reverser cascade when the thrust reverser door is in the stowed position, and a second portion of the thrust reverser door forming a r

Assignees

• Rohr Inc

Inventors

• Winkler Julian
• Chien Wentaur E
• Hu Xiaolan

Classifications

• F02K1/54

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

• F02K1/56

  Reversing jet main flow · CPC title

• F02K1/50

  Deflecting outwardly a portion of the jet by retractable scoop-like baffles · CPC title

• F02K1/70

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F02K1/64

  Reversing fan flow · CPC title