Sound absorber, sound absorber assembly and an engine with a sound absorber assembly

Patent metadata

Field	Value
Publication number	US-9303588-B2
Application number	US-201414471561-A
Country	US
Kind code	B2
Filing date	Aug 28, 2014
Priority date	Aug 30, 2013
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A sound absorber comprising a base body and a tongue ( 24 ). The base body has a bottom plate, a wall enclosing the bottom plate and an opening enabling the entry of air into the base body. The tongue has a fixed end, a free end and a central portion disposed between the fixed and the free end. The free end of the tongue is spaced from the wall and the bottom plate, and the central portion of the tongue is disposed to extend at least partially straight along a width direction. Furthermore, a sound absorber assembly can include at least two sound absorbers, and an engine, in particular, for an aircraft, comprising such a sound absorber and/or such a sound absorber assembly.

First claim

What is claimed is:

1. A sound absorber for an engine of an aircraft, the sound absorber comprising:
a base body having a bottom plate, a wall enclosing the bottom plate and an opening enabling entry of air into the base body; and
a tongue having a fixed end connected to the wall, a free end and a central portion disposed between the fixed end and the free end;
the tongue further having a longitudinal direction extending from the fixed end towards the free end, a width direction extending substantially perpendicularly to the longitudinal direction, and a transverse direction extending substantially perpendicularly to the longitudinal direction and substantially perpendicularly to the width direction,
the central portion having a first free edge extending in the longitudinal direction from the fixed end towards the free end, and a second free edge opposite to the first free edge and extending in the longitudinal direction from the fixed end towards the free end,
the tongue dividing a space of the base body into a partial space adjacent to the bottom plate and a partial space adjacent to the opening, the two partial spaces being connected to each other via a gap,
the free end being disposed at a first distance from the wall in the transverse direction and at a second distance from the bottom plate in the longitudinal direction, such that the first and the second distances determine a size of the gap, and
the central portion being configured to extend at least partially straight along the width direction.

2. The sound absorber according to claim 1 , wherein the bottom plate is trapezoidal.

3. The sound absorber according to claim 1 , wherein the tongue has at least one of the following characteristics
the tongue is bent along the longitudinal direction in a shape of one of a parabola branch, an exponential function or a hyperbola;
the free end is curved in the longitudinal direction; and
the tongue includes at least one of metal, sheet metal, carbon fibers and ceramic composite materials.

4. The sound absorber according to claim 1 , wherein
at least the central portion has two lateral portions extending in the longitudinal direction, with the lateral portions being connected with the wall.

5. The sound absorber according to claim 1 , further comprising
a covering layer covering the opening, the covering layer including at least one of a perforated metal, a μ-perforated metal and a fabric.

6. A sound absorber assembly for an engine of an aircraft, the sound absorber assembly comprising at least two sound absorbers according to claim 1 .

7. The sound absorber assembly according to claim 6 , wherein
the at least two sound absorbers are disposed one behind the other in at least one of the transverse direction and the width direction; and
the wall preferably includes at least in some regions an angle unequal to 90° with the bottom plate.

8. The sound absorber assembly according to claim 6 , wherein
the tongue is connected to the wall by an attachment portion, with the opening defining a plane and the attachment portion extending in the plane of the opening over a surface area measuring less than 10% of an extent of the opening.

9. The sound absorber assembly according to claim 8 , wherein
at least two of the tongues, which protrude into at least two of the base bodies, are disposed on one attachment portion.

10. The sound absorber assembly according to claim 6 , wherein
regions of the walls of two of the sound absorbers that abut against each other are formed by a common wall.

11. The sound absorber assembly according to claim 10 , wherein
the tongues of the two sound absorbers are attached to the common wall, with the common wall having a cut-out.

12. The sound absorber assembly according to claim 11 , wherein
an area at which at least one of the tongues is attached to the common wall divides the common wall into a first portion adjacent to the opening and a second portion adjacent to the bottom plate, with the second portion having the cut-out which includes the entire second portion.

13. The sound absorber assembly according to claim 8 , wherein
the sound absorbers are disposed in the form of a pipe having a radial direction, a circumferential direction and an axial direction, with the openings of the sound absorbers pointing inwards in the radial direction, and the attachment portions of the sound absorbers being disposed in the circumferential direction or in the axial direction.

14. The sound absorber according to claim 13 , further comprising
a drain opening disposed between the base bodies along at least one of the attachment portion of the tongue and along the bottom plate.

15. An aircraft engine comprising:
a sound absorber according to claim 1 .

16. The sound absorber according to claim 1 , wherein the bottom plate is rectangular.

17. The sound absorber assembly according to claim 6 , wherein
the tongue is connected to the wall by an attachment portion, with the opening defining a plane and the attachment portion extending in the plane of the opening over a surface area measuring less than 5% of the extent of the opening.

18. The sound absorber according to claim 14 , wherein
the drain opening is disposed between the base bodies along at least one of the attachment portion of the tongue and along the bottom plate in the circumferential direction.

19. An aircraft engine comprising:
a sound absorber assembly according to claim 6 .

20. The sound absorber according to claim 2 , wherein the tongue has at least one of the following charactristics
the tongue is bent along the longitudinal direction in a shape of one of a parabola branch, an exponential function or a hyperbola;
the free end is curved in the longitudinal direction; and
the tongue includes at least one of metal, sheet metal, carbon fibers and ceramic composite materials.

Assignees

• Airbus Defence & Space Gmbh
• Rolls Royce Deutschland

Inventors

• Pongratz Reinhard
• Richter Christoph
• Kern Max
• Redmann Daniel

Classifications

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F02K1/827 Primary

  Sound absorbing structures or liners · CPC title

• F02C7/045

  having provisions for noise suppression · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F02K1/44

  Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction (F02K1/40 takes precedence) · CPC title