Pylon with noise attenuating fairing

Patent metadata

Field	Value
Publication number	US-9725183-B2
Application number	US-201514746439-A
Country	US
Kind code	B2
Filing date	Jun 22, 2015
Priority date	Jun 22, 2015
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A pylon is provided for connecting a propulsion system to an aircraft. The pylon includes a structure configured to structurally tie the propulsion system to the aircraft. The pylon also includes a pylon fairing configured to house and provide an aerodynamic cover for the structure. A lower aft fairing segment of the pylon fairing includes a plurality of apertures. The apertures are fluidly coupled with a sealed, sound attenuating chamber within the pylon.

First claim

I claim:

1. A pylon for connecting a propulsion system to an aircraft, the pylon comprising:
a structure configured to structurally tie the propulsion system to the aircraft;
a pylon fairing configured to house and provide an aerodynamic cover for the structure, the pylon fairing including a fairing wall and a lower aft fairing segment of the pylon fairing including a plurality of apertures extending through the fairing wall; and
one or more baffles disposed within the pylon fairing;
wherein the fairing wall and one or more baffles define a sealed, sound attenuating chamber within the pylon.

2. The pylon of claim 1 , wherein the pylon is configured such that the chamber is operable to attenuate sound having a frequency between about four-hundred Hertz and about eight hundred Hertz.

3. The pylon of claim 1 , wherein
the lower aft fairing segment extends laterally between opposing fairing sides and vertically to a fairing bottom end which extends laterally between the fairing sides; and
at least some of the apertures are disposed on a first of the fairing sides.

4. The pylon of claim 3 , wherein some of the apertures are disposed on a second of the fairing sides.

5. The pylon of claim 3 , wherein some of the apertures are disposed on the fairing bottom end.

6. The pylon of claim 1 , wherein
the lower aft fairing segment extends laterally between opposing fairing sides and vertically to a fairing bottom end which extends laterally between the fairing sides; and
at least some of the apertures are disposed on the fairing bottom end.

7. The pylon of claim 1 , wherein
the lower aft fairing segment comprises metal; and
another fairing segment of the pylon fairing, which is adjacent to the lower aft fairing segment, comprises composite material.

8. The pylon of claim 1 , wherein the lower aft fairing segment is configured to guide core gas exhausted from a core gas path of the propulsion system.

9. The pylon of claim 1 , wherein
the lower aft fairing segment comprises a core between a first face sheet and a second face sheet;
a plurality of pores in the core are fluidly coupled between a plurality of first perforations in the first face sheet and a plurality of second perforations in the second face sheet; and
the pores, the first perforations and the second perforations form the apertures.

10. A pylon for connecting a propulsion system to an aircraft, the pylon comprising:
a structure configured to structurally tie the propulsion system to the aircraft;
a pylon fairing configured to house and provide an aerodynamic cover for the structure, a lower aft fairing segment of the pylon fairing including a plurality of apertures, wherein the apertures are fluidly coupled with a sealed, sound attenuating chamber within the pylon; and
at least one baffle disposed within the chamber that divides the chamber into a plurality of cavities;
wherein the pylon fairing comprises a fairing wall;
wherein the apertures extend through the fairing wall;
wherein an exterior side of the fairing wall partially forms an exterior surface of the pylon fairing; and
wherein an interior side of the fairing wall, which opposes the exterior side, partially defines the sound attenuating chamber.

11. The pylon of claim 1 , wherein the pylon fairing is configured such that
first sound waves are capable of traveling through the apertures and into the sound attenuating chamber; and
the sound attenuating chamber is operable to resonate in response to receiving the first sound waves and thereby produce second sound waves that travel out of the sound attenuating chamber through the apertures to destructively interfere with other sound waves outside of the pylon fairing.

12. An aircraft system, comprising:
an aircraft propulsion system including a core gas path;
a pylon connected to the aircraft propulsion system, the pylon including a pylon fairing with a lower aft fairing segment configured to guide core gas exhausted from the core gas path, wherein the lower aft fairing segment includes a plurality of apertures which are fluidly coupled with a sealed, sound attenuating chamber within the pylon; and
at least one baffle disposed within the chamber that divides the chamber into a plurality of cavities;
wherein the pylon fairing comprises a fairing wall;
wherein the apertures extend through the fairing wall;
wherein an exterior side of the fairing wall partially forms an exterior surface of the pylon fairing; and
wherein an interior side of the fairing wall, which opposes the exterior side, partially defines the sound attenuating chamber.

13. The aircraft system of claim 12 , wherein another fairing segment of the pylon fairing is configured to guide air flowing around the aircraft propulsion system.

14. The aircraft system of claim 13 , wherein the lower aft fairing segment comprises metal and the other fairing segment comprises composite material.

15. The aircraft system of claim 12 , wherein
the lower aft fairing segment extends laterally between opposing fairing sides and vertically to a fairing bottom end which extends laterally between the fairing sides; and
at least some of the apertures are disposed on a first of the fairing sides.

16. The aircraft system of claim 12 , wherein
the lower aft fairing segment extends laterally between opposing fairing sides and vertically to a fairing bottom end which extends laterally between the fairing sides; and
at least some of the apertures are disposed on the fairing bottom end.

17. The aircraft system of claim 12 , wherein the pylon is configured such that the sound attenuating chamber passively attenuates noise.

18. The aircraft system of claim 12 , wherein the pylon is configured such that
first sound waves are capable of traveling through the apertures and into the sound attenuating chamber; and
the sound attenuating chamber is operable to resonate in response to receiving the first sound waves and thereby produce second sound waves that travel out of the sound attenuating chamber through the apertures to destructively interfere with other sound waves outside of the pylon.

Assignees

• Rohr Inc

Inventors

• Aten Michael

Classifications

• B64D33/06 Primary

  Silencing exhaust or propulsion jets · CPC title

• B64D29/02

  associated with wings · CPC title

• B64C7/02

  Nacelles · CPC title