Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face

Patent metadata

Field	Value
Publication number	US-11274632-B2
Application number	US-201916381326-A
Country	US
Kind code	B2
Filing date	Apr 11, 2019
Priority date	Jul 18, 2013
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

In a cowl for a nozzle, an internal wall has a cross-section with a determined abscissa on the axis defining a neck line on the internal wall. The cowl has, downstream of the determined abscissa, indentations in the trailing edge which delimit chevrons distributed in the circumferential direction. The internal wall of the cowl diverges radially towards the interior, in a second axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in the second axial half-plane, and the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the determined abscissa of the neck line.

First claim

The invention claimed is:

1. A cowl for a nozzle having a longitudinal axis L-L, comprising:
an external wall and an internal wall, the cowl being delimited radially towards an exterior by the external wall and, radially towards an interior, by the internal wall,
the internal wall of the cowl having a cross-section with a determined abscissa on the axis L-L defining a neck line on the internal wall, said neck line being at the smallest cross sectional area of said nozzle, said internal wall converging towards the axis L-L upstream of said cross-section and having, in any axial half-plane, a defined upstream tangent at its intersection with the neck line,
said cowl having, downstream of said determined abscissa, indentations in a trailing edge of the cowl which delimit chevrons distributed in a circumferential direction,
wherein in a downstream direction from said determined abscissa,
the internal wall of the cowl diverges radially towards the exterior, in a first axial half-plane of any axial half-plane passing through the top of an indentation, from the upstream tangent on the tip of the neck line in said first axial half-plane of the any axial half-plane, from said neck line to said trailing edge of said first axial half-plane of the any axial half-lane,
the external wall of the cowl moves closer, in said first axial half-plane of, the any axial half-plane, to the upstream tangent on the tip of the neck line in said first axial half-plane of the any axial half-plane, from said neck line to said trailing edge of said first axial half-plane,
the internal wall of the cowl diverges radially towards the interior, in a second axial half-plane of the any axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in said second axial half-plane of hg any axial half-plane, from said neck line to said trailing edge of said second axial half-plane and
lines defining the internal wall of the cowl in the any axial half-plane do not have a turning point downstream of said determined abscissa of the neck line.

2. The cowl for the nozzle according to claim 1 , wherein the lines defining the internal wall, respectively the upstream and the downstream of the neck line in the any axial half-plane, have the same tangent on the neck line.

3. The cowl for the nozzle according to claim 1 , of which a first line, defining the internal wall of the cowl downstream of said determined abscissa in an axial half-plane of the any axial half-plane passing through the tip of a chevron, is concave when viewed from the axis L-L.

4. The cowl for the nozzle according to claim 1 , of which a second line, defining the internal wall of the cowl downstream of said determined abscissa in an axial half-plane of the any axial half-plane passing through the top of a chevron, is convex when viewed from the axis L-L.

5. The cowl for the nozzle according to claim 1 , of which a third line, defining the external wall of the cowl downstream of said determined abscissa in an axial half-plane of the any axial half-plane passing through the top of a chevron, is concave when viewed from the axis L-L.

6. The cowl for the nozzle according to claim 1 , of which the lines defining the external wall of the cowl in the any axial half-plane do not have a turning point downstream of said determined abscissa of the neck line.

7. The cowl for the nozzle according to claim 1 , of which a thickness of the cowl on its trailing edge is substantially constant.

8. A nozzle for a turbine engine having the longitudinal axis L-L comprising the cowl according to claim 1 .

9. The nozzle according to claim 8 , further comprising:
a central body of revolution about the axis L-L.

10. The nozzle according to claim 9 , in which a radial passage cross-section at a point on one of the internal wall and the external wall of the cowl is defined as the square of a radial distance of said point on the one of the internal wall and the external wall from the axis L-L minus the square of the radial distance of the axis L-L from a point of a wall of the central body situated on a radius on a same axial plane as the point on the one of the internal wall and the external wall of the cowl radius when said central body is present at the axial plane abscissa on the axis L-L of said point, and by the square of the radial distance of said point on the cowl from the axis L-L when this is not the case, said nozzle being characterized in that, in the downstream direction from said determined abscissa of the neck line, the radial passage cross-section of the internal wall of the cowl increases in an axial half-plane of the any axial half-plane passing through the top of an indentation.

Assignees

• Safran Aircraft Engines

Inventors

• Langridge Jonathan
• Szydlowski Julien

Classifications

• F02K1/34 Primary

  for attenuating noise · CPC title

• F05D2250/184

  sinusoidal · CPC title

• F05D2250/712

  concave · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2250/11

  triangular · CPC title