Fluid scoop for a thrust reverser system

Patent metadata

Field	Value
Publication number	US-11566583-B2
Application number	US-202217667888-A
Country	US
Kind code	B2
Filing date	Feb 9, 2022
Priority date	Feb 9, 2021
Publication date	Jan 31, 2023
Grant date	Jan 31, 2023

Abstract

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.

First claim

What is claimed is:

1. An assembly for an aircraft propulsion system, comprising:
a thrust reverser system comprising a cascade structure and a scoop;
the cascade structure configured with a plurality of flow passages, each of the plurality of flow passages extending through the cascade structure, and the plurality of flow passages comprising a first flow passage; and
the scoop configured to direct fluid into at least the first flow passage, the scoop comprising a serrated leading edge.

2. The assembly of claim 1 , wherein
the scoop includes a base and a plurality of protrusions;
the plurality of protrusions are arranged along an upstream end of the base, and each of the plurality of protrusions projects out from the base; and
the serrated leading edge is formed at least by the plurality of protrusions.

3. The assembly of claim 2 , wherein
the plurality of protrusions include a first protrusion and a second protrusion;
the first protrusion laterally neighbors the second protrusion; and
the first protrusion is laterally spaced from the second protrusion by a lateral inter-protrusion distance.

4. The assembly of claim 3 , wherein
the first protrusion has a chord length that extends from the upstream end of the base to a distal end of the first protrusion; and
the lateral inter-protrusion distance is between two-third times the chord length and one and one-half times the chord length.

5. The assembly of claim 2 , wherein the serrated leading edge is further formed by the base at the upstream end of the base.

6. The assembly of claim 2 , wherein the plurality of protrusions have common configurations.

7. The assembly of claim 2 , wherein
the plurality of protrusions include a first protrusion; and
the first protrusion has a triangular geometry.

8. The assembly of claim 2 , wherein
the plurality of protrusions include a first protrusion;
the first protrusion has a chord length and a span length, and an aspect ratio of two times the span length to the chord length is between 1 and 2.5;
the chord length extends from the upstream end of the base to a distal end of the first protrusion; and
the span length extends laterally along the base between opposing sides of the first protrusion at the upstream end of the base.

9. The assembly of claim 2 , wherein
the plurality of protrusions include a first protrusion;
the first protrusion has a tip, a first protrusion side and a second protrusion side that meets the first protrusion side at the tip; and
the first protrusion side is angularly offset from the second protrusion side by an angle between twenty degrees and sixty degrees.

10. The assembly of claim 2 , wherein
the base has a base length that extends longitudinally along a camber line from the cascade structure to the upstream end of the base, and the base length is between two times and four times a variable X; and
the plurality of protrusions include a first protrusion, the first protrusion has a chord length that extends longitudinally along the camber line from the upstream end of the base to a distal end of the first protrusion, and the chord length is between one-third times and one times the variable X.

11. The assembly of claim 2 , wherein
the plurality of protrusions include a first protrusion and a second protrusion;
the first protrusion is laterally aligned with the first flow passage; and
the second protrusion is laterally aligned with the first flow passage.

12. The assembly of claim 2 , wherein
the plurality of flow passages further comprise a second flow passage laterally next to the first flow passage;
the plurality of protrusions include a first protrusion and a second protrusion;
the first protrusion is laterally aligned with the first flow passage; and
the second protrusion is laterally aligned with the second flow passage.

13. The assembly of claim 2 , wherein
the plurality of flow passages further comprise a second flow passage; and
the first protrusion laterally overlaps the first flow passage and the second flow passage.

14. The assembly of claim 1 , wherein
the cascade structure includes a plurality of cascade vanes;
a boundary of each of the plurality of flow passages is formed by a respective one of the plurality of cascade vanes; and
the scoop is integral with and forms an extension of a first of the plurality of cascade vanes.

15. The assembly of claim 1 , further comprising:
a forward thrust duct;
the thrust reverser system further comprising a thrust reverser duct and a bullnose ramp;
the cascade structure arranged within the thrust reverser duct;
the bullnose ramp adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration; and
the scoop connected to the bullnose ramp by one or more supports.

16. The assembly of claim 1 , wherein
the cascade structure extends axially along a centerline from a cascade structure upstream end to a cascade structure downstream end; and
the first flow passage is an axially upstream-most one of the plurality of flow passages.

17. The assembly of claim 1 , wherein the serrated leading edge extends laterally along an entirety of a lateral length of the first flow passage.

18. An assembly for an aircraft propulsion system, comprising:
a thrust reverser system comprising a cascade structure and a scoop;
the cascade structure comprising a plurality of flow passages and a plurality of cascade vanes, a side boundary of each of the plurality of flow passages formed by a respective one of the plurality of cascade vanes, and the plurality of flow passages comprising a first flow passage; and
the scoop configured to direct fluid into at least the first flow passage, the scoop including a base and a plurality of protrusions, the plurality of protrusions arranged along an upstream end of the base, and each of the plurality of protrusions having a tip and projecting out from the upstream end of the base and laterally tapering to the tip.

19. An assembly for an aircraft propulsion system, comprising:
a thrust reverser cascade structure extending axially along a centerline from an upstream end to a downstream end, the thrust reverser cascade structure configured with a plurality of flow passages and a plurality of vanes;
a side boundary of each of the plurality of flow passages formed by a respective one of the plurality of vanes; and
the plurality of vanes comprising a first vane that is configured with a serrated leading edge.

20. The assembly of claim 19 , further comprising:
a scoop configured with the first vane;
the scoop projecting out from an upstream end of the first vane to the serrated leading edge.

Assignees

• Rohr Inc

Inventors

• Chilukuri Radhakrishna
• Saya Ashok Babu
• Tapadar Hussain Mahamed Javed

Classifications

• F05D2220/323

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

• F02K1/56 Primary

  Reversing jet main flow · CPC title

• Y02T50/60

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

• F05D2250/182

  crenellated, notched · CPC title

• F05D2240/129

  Cascades, i.e. assemblies of similar profiles acting in parallel · CPC title