Fluid scoop for a thrust reverser system

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.