Profiled structure and associated turbomachine

Patent metadata

Field	Value
Publication number	US-11859534-B2
Application number	US-201916969738-A
Country	US
Kind code	B2
Filing date	Feb 15, 2019
Priority date	Feb 16, 2018
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

First claim

The invention claimed is:

1. A profiled air flow structure comprising:
a body having an upstream leading edge and/or a downstream trailing edge;
porous acoustically absorbent regions; and
along the upstream leading edge and/or the downstream trailing edge, a serrated profile line showing a succession of teeth and depressions,
wherein the porous acoustically absorbent regions locally form bottoms for the depressions where the porous acoustically absorbent regions occupy a part of the body to define, together with the body, the serrated profile line at the upstream leading edge and/or the downstream trailing edge, wherein each porous acoustically absorbent region has a geometric center located downstream of the bottom of the depressions in the upstream leading edge or upstream of the bottom of the depressions in the downstream trailing edge.

2. The profiled structure according to claim 1 , further comprising:
a chord in which:
along the chord, the serrated profile line has a maximum amplitude, “h”, and
the geometric center of each porous acoustically absorbent region is located at a distance “d” downstream of the upstream leading edge or upstream of the downstream trailing edge, at the bottom of the depressions such that:
d=h/ 10, within 30%.

3. The profiled air flow structure according to claim 1 , further comprising:
a chord in which:
along the upstream leading edge or the downstream trailing edge, the serrated profile line has a distance between two consecutive tooth tips,
along the chord, the serrated profile line has a maximum amplitude, “h”, and
the porous acoustically absorbent region has:
along the upstream leading edge and/or the downstream trailing edge, two limits separated by a distance “a” such that a is equal to one third of said distance between two consecutive tooth tips, to within 30%,
along the chord, two limits separated by a distance “b” such that b=h/3, within 30%.

4. The profiled air flow structure according to claim 2 , wherein:
along the upstream leading edge or the downstream trailing edge, the serrated profile line has a distance between two consecutive tooth tips, and

the porous acoustically absorbent region has:
along the upstream leading edge and/or the downstream trailing edge, two limits separated by a distance “a” such that a is equal to one third of said distance between two consecutive tooth tips, to within 30%,
along the chord, two limits separated by a distance “b ” such that b=h/3, within 30%.

5. The profiled air flow structure according to claim 1 , which is one of an aircraft structure and a front fan turbomachine structure.

6. The profiled air flow structure according to claim 1 , wherein the profiled air flow structure is one selected from the following:
an aircraft wing, an aircraft wing slat, an aircraft wing flap, an aircraft engine support pylon, a fin, an aircraft stabilizer, a helicopter blade, a propeller,
one of the following parts of a turbomachine adapted to power an aircraft:
a leading and/or trailing edge of an annular air flow separating wall, downstream of a front fan of the turbomachine, between a primary flow and a secondary flow,

inlet guide vanes extending in the primary flow,
outlet guide vanes extending in the secondary flow.

7. The profiled air flow structure according to claim 3 , wherein the porous acoustically absorbent region comprises a porous foam having pores with a cross-section smaller than a quarter of said distance “a” or a quarter of said distance “b”, on a surface of the profiled air flow structure at said upstream leading edge.

8. The profiled air flow structure according to claim 3 , wherein the porous acoustically absorbent region comprises, on a surface of the profiled air flow structure, one of a micro-perforated sheet material and a resonant cavity material covering a porous foam having pores with a cross-section smaller than a quarter of said distance “a” or a quarter of said distance “b”.

9. The profiled air flow structure according to claim 1 , wherein the porous acoustically absorbent region comprises a Helmholtz resonator.

10. The profiled air flow structure according to claim 1 , in which individually the teeth and depressions of the serrated profile have a wavy shape, with respective tops which are all rounded or all sharp.

11. The profiled air flow structure according to claim 1 , wherein individually the teeth and depressions of the serrated line profile have a shape with locally rectilinear side walls.

12. The profiled air flow structure according to claim 1 in which, along the upstream leading edge and/or the downstream trailing edge, the teeth of the serrated profile, which each have an apex, are individually non-symmetrical with respect to a perpendicular to the upstream leading edge passing through the corresponding tooth.

13. The profiled air flow structure according to claim 1 in which, along the upstream leading edge and/or the downstream trailing edge, from a first location to a second location, the teeth of the serrated profile, each having an apex, are individually inclined towards the second location.

14. The profiled air flow structure according to claim 13 , further comprising:
a span along the upstream leading edge and/or the downstream trailing edge between a first end and a second end,
wherein the inclinations of the teeth are each oriented towards one of said first end and second end.

15. A turbomachine for aircraft, the turbomachine comprising the profiled structure according to claim 1 .

16. A turbomachine for aircraft, said turbomachine being traversed by an air flow flowing from upstream to downstream, comprising the profiled air flow structure according to claim 13 and being such that:
the turbomachine comprises a front fan and has a general axis about which the front fan can rotate,
the front fan is adapted to rotate in a predetermined direction about said general axis, such that the airflow downstream of the front fan is generally obliquely oriented with respect to said general axis, and
the teeth are inclined circumferentially around said general axis towards the generally oblique orientation of the air flow downstream of the front fan, to face it.

17. A turbomachine for an aircraft, the turbomachine comprising the profiled air flow according to claim 6 , and wherein:
the turbomachine comprises a front fan and has a general axis about which the front fan can rotate, and
the teeth are, circumferentially around said general axis, individually inclined:
along an average camber of said inlet guide vanes, or
along a camber at an upstream leading edge of said inlet guide vanes.

18. The profiled structure according to claim 4 , wherein the porous acoustically absorbent region comprises a porous foam having pores with a cross-section smaller than a quarter of said distance “a” or a quarter of said distance “b”, on a surface of the profiled air flow structure at said upstream leading edge.

19. The profiled air flow structure according to claim 4 , wherein the porous acoustically absorbent region comprises, on a surface of the profiled air flow structure, one of a micro-perforated sheet material and a resonant cavity material covering a porous foam having pores with a cross-section smaller than a quarter of said distance “a” or a quarter of said distance “b”.

Assignees

• Safran Aircraft Engines

Inventors

• Gea Aguilera Fernando
• Gruber Mathieu Simon Paul
• Riou Georges Jean Xavier

Classifications

• F02C7/045 Primary

  having provisions for noise suppression · CPC title

• B64C3/10

  Shape of wings · CPC title

• B64C11/18

  Aerodynamic features · CPC title

• B64C21/10

  using other surface properties, e.g. roughness · CPC title

• B64D33/02

  of combustion air intakes · CPC title