Aircraft and air exchange systems for ventilated cavities of aircraft

Patent metadata

Field	Value
Publication number	US-2016101845-A1
Application number	US-201414513172-A
Country	US
Kind code	A1
Filing date	Oct 13, 2014
Priority date	Oct 13, 2014
Publication date	Apr 14, 2016
Grant date	—

Abstract

Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise.

First claim

What is claimed is:

1 . An aircraft, comprising:
a fuselage; a wing secured to the fuselage; an outer skin panel secured to at least one of the wing and the fuselage, wherein the outer skin panel at least partially defines a cavity; and an air exchange system secured to the outer skin panel and configured to exchange air between the cavity and an external environment outside of the aircraft, the air exchange system comprising:
an air inlet disposed in the outer skin panel and configured to permit an air flow between the cavity and the external environment,
a diffuser attached to the air inlet and having a varying cross sectional area configured to change a speed of the air flow, and
a silencer attached to the diffuser and configured to direct the air flow between the diffuser and the cavity and reduce noise.

2 . The aircraft of claim 1 , wherein the outer skin panel is a wing-to-body fairing, and wherein the cavity is further defined by the fuselage.

3 . The aircraft of claim 2 , wherein the varying cross sectional area of the diffuser increases in a direction of the air flow to reduce the speed of the air flow.

4 . The aircraft of claim 1 , wherein the air exchange system is oriented to direct the air flow away from the fuselage.

5 . The aircraft of claim 1 , wherein the air exchange system is configured to accommodate air flowing at a speed substantially similar to a maximum speed of the aircraft.

6 . The aircraft of claim 1 , wherein the diffuser defines an increasing cross-sectional area from the air inlet to the silencer.

7 . The aircraft of claim 1 , wherein the silencer includes a solid outer shell and a porous inner liner.

8 . The aircraft of claim 7 , wherein the porous inner liner is formed from a porous material.

9 . The aircraft of claim 7 , wherein the solid outer shell defines a drainage aperture at a gravitational low point of the silencer.

10 . The aircraft of claim 9 , further comprising a sound reducing component disposed between the solid outer shell and the porous inner liner.

11 . The aircraft of claim 10 , wherein a bottom of the interior of the solid outer shell is a flat plate configured to allow airflow to sweep fluids out of the silencer and into the cavity.

12 . A wing-to-body fairing assembly for an aircraft, the wing-to-body fairing assembly comprising:
an outer skin panel configured to be secured to a wing and a fuselage of the aircraft to define a wing-to-body fairing cavity; and an air exchange system secured to the outer skin panel and configured to exchange air between the wing-to-body fairing cavity and an external environment outside of the aircraft, the air exchange system comprising:
an air inlet disposed in the outer skin panel and configured to permit an air flow between the wing-to-body fairing cavity and the external environment at a speed substantially similar to a maximum speed of the aircraft,
a diffuser attached to the air inlet and having an increasing cross sectional area in a direction of the air flow to reduce a speed of the air flow, and
a silencer attached to the diffuser and configured to communicate the air flow between the diffuser and the wing-to-body fairing cavity to reduce noise.

13 . The wing-to-body fairing assembly of claim 12 , wherein the diffuser is configured to direct the air flow away from the fuselage when installed on the aircraft.

14 . The wing-to-body fairing assembly of claim 12 , wherein the silencer includes a solid outer shell and a porous inner liner.

15 . The wing-to-body fairing assembly of claim 14 , wherein the solid outer shell defines a drainage aperture at a gravitational low point of the silencer.

16 . The wing-to-body fairing assembly of claim 15 , further comprising a sound reducing component disposed between the solid outer shell and the porous inner liner.

17 . The wing-to-body fairing assembly of claim 16 , wherein a bottom of the interior of the solid outer shell is a flat plate configured to allow airflow to sweep fluids out of the silencer and into the wing-to-body fairing cavity.

18 . An air exchange system for a wing-to-body fairing cavity of an aircraft, the air exchange system comprising:
an air inlet configured to accommodate an air flow from an external environment to the wing-to-body fairing cavity at a speed substantially similar to a maximum speed of the aircraft; a diffuser attached to the air inlet and having an increasing cross sectional area in a direction of the air flow to reduce a speed of the air flow, wherein the diffuser is configured to direct the air flow away from a fuselage of the aircraft when installed in the aircraft; and a silencer attached to the diffuser and configured to communicate the air flow between the diffuser and the wing-to-body fairing cavity.

19 . The air exchange system of claim 18 , wherein the silencer includes a solid outer shell and a porous inner liner, and wherein the solid outer shell defines a drainage aperture at a gravitational low point of the silencer.

20 . The air exchange system of claim 19 , further comprising a sound reducing component disposed between the solid outer shell and the porous inner liner.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Wang Tongan
• Lucas Michael Eugene
• Lynch Kristopher P
• Relf Tyler
• Maxon Jr John Willett

Classifications

• B64D37/32

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64C1/40 Primary

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64D13/00

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• B64C1/14 Primary

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title