Aircraft cabin air distribution system, aircraft and method of feeding air into cabin of fuselage

Abstract

The invention relates to an aircraft cabin air distribution system, an aircraft and a method of feeding air into a cabin of a fuselage. An aircraft cabin air distribution system has a fuselage, a cabin in the fuselage, a supply duct, and a plurality of outlets configured to feed air into the cabin. The outlets include an upper outlet positioned at a higher level than the supply conduit and a lower outlet positioned at a lower level than the supply conduit. The aircraft cabin air distribution system also includes a plurality of branch ducts configured to feed air from the supply duct to the outlet, where each branch duct is in contact with the supply duct at a respective junction. The branch ducts include upper branch ducts each feeding air to one or more of the upper outlets and lower branch ducts each feeding air to one or more of the lower outlets.

Description

Technical Field

[0001] The invention relates to an aircraft cabin air distribution system and a method of feeding air into a cabin of a fuselage. Background Art

[0002] Conventional aircraft cabin air distribution systems supply air from a main supply duct to an outlet via a large number of riser ducts. This can result in significant pressure losses due to the large number of riser duct joints and friction pressure losses caused by the duct length. Therefore, large diameter supply ducts are required to provide high mass flow, and a high pressure air supply is required to overcome the pressure losses. Summary of the invention

[0003] A first aspect of the present invention provides an aircraft cabin air distribution system, which includes a fuselage; a cabin in the fuselage; a supply duct; a plurality of outlets, the plurality of outlets being configured to supply air into the cabin, the outlets including an upper outlet and a lower outlet, the upper outlet being positioned at a higher level than the supply duct, and the lower outlet being positioned at a lower level than the supply duct; and a plurality of branch ducts, the plurality of branch ducts being configured to supply air from the supply duct to the outlets, wherein each branch duct is connected to the supply duct at a corresponding joint, and the branch ducts include upper branch ducts and lower branch ducts, the upper branch ducts each supply air to one or more of the upper outlets, and the lower branch ducts each supply air to one or more of the lower outlets.

[0004] Optionally, each joint of the upper branch pipe is arranged to be opposite to a joint of the lower branch pipe.

[0005] Optionally, each branch pipe is connected to the supply pipe at a corresponding joint at an angle of 90°.

[0006] Optionally, each outlet comprises a plenum having a plurality of slots in fluid communication with the cabin to feed air into the cabin.

[0007] Optionally, the diameter of each branch conduit is smaller than the diameter of the supply conduit.

[0008] Optionally, the cabin comprises a plurality of overhead boxes, the upper outlets being positioned at a higher level than the overhead boxes, and the lower outlets being positioned at a lower level than the overhead boxes.

[0009] Optionally, the aircraft cabin air distribution system further comprises: an air supply unit; and one or more riser ducts for feeding air from the air supply unit to the supply duct. The (or each) riser duct may extend in a circumferential direction.

[0010] Optionally, the supply duct is fed with air from the air supply unit only via a single riser duct, or only via a pair of riser ducts, or only via three riser ducts.

[0011] Optionally, the supply duct is a first supply duct, and the system further includes: a second supply duct; a plurality of second outlets, the plurality of second outlets being configured to feed air into the cabin, the second outlets comprising an upper second outlet and a lower second outlet, the upper second outlet being positioned at a higher level than the second supply duct, and the lower second outlet being positioned at a lower level than the second supply duct; and a plurality of second branch ducts, the plurality of second branch ducts being configured to feed air from the second supply duct to the second outlet, wherein each second branch duct is connected to the second supply duct at a corresponding joint, and the second branch ducts comprising an upper second branch duct and a lower second branch duct, the upper second branch ducts each feeding air to one or more of the upper second outlets, and the lower second branch ducts each feeding air to one or more of the lower second outlets.

[0012] Optionally, the first supply duct is located on the port side of the fuselage and the second supply duct is located on the starboard side of the fuselage.

[0013] Optionally, the first supply duct and the second supply duct are located on the same side of the fuselage.

[0014] Optionally, the aircraft cabin air distribution system further comprises: an air supply unit; one or more first riser ducts for feeding air from the air supply unit to the first supply ducts; and one or more second riser ducts for feeding air from the air supply unit to the second supply ducts.

[0015] Optionally, the fuselage comprises a cabin floor; and the air supply unit is positioned outside the cabin and below the cabin floor.

[0016] Optionally, the cabin is pressurized; and the air supply unit is located in a non-pressurized part of the fuselage.

[0017] Optionally, the air supply unit comprises a mixer unit configured to receive and mix air from a plurality of sources.

[0018] Optionally, the (or each) supply duct extends in the longitudinal direction of the fuselage.

[0019] Another aspect of the invention provides an aircraft comprising the aircraft cabin air distribution system of the first aspect.

[0020] Another aspect of the invention provides a method of feeding air into a cabin of a fuselage, the method utilizing an aircraft cabin air distribution system according to the first aspect, the method comprising: feeding air from a supply duct via the supply duct and a respective junction of the supply duct to an outlet; and feeding air from the outlet into the cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Embodiments of the present invention will now be described with reference to the accompanying drawings, in which:

[0022] Figure 1 A plan view of the aircraft is shown;

[0023] Figure 2 Shows Figure 1 A cross-sectional view of the fuselage of an aircraft;

[0024] Figure 3 shows a schematic overview of an exemplary cabin air distribution system;

[0025] Figure 4 Shows Figure 1 A three-dimensional schematic diagram of the fuselage of an aircraft;

[0026] Figure 5 A schematic diagram showing an exemplary piping arrangement is shown;

[0027] Figure 6 The outlet is shown in detail; and

[0028] Figure 7 Shown is a multi-zone air distribution system Figure 1 A three-dimensional schematic diagram of the fuselage of an aircraft. DETAILED DESCRIPTION

[0029] Figure 1 An aircraft 1 is shown in FIG. 1 and comprises a fuselage 2 and a pair of port and starboard fixed wings 3, 4. The aircraft 1 has a nose end 5 at the front end of the aircraft and a tail end 6 at the rear end. An engine 7 is mounted to each wing 3, 4.

[0030] Figure 1 and Figure 2 The XYZ axes shown in represent the reference system of the aircraft 1. The X axis is the longitudinal axis defining the X direction of the aircraft; the Y axis is the transverse axis defining the Y direction of the aircraft, and the Z axis is the vertical axis defining the Z direction of the aircraft.

[0031] Figure 2 Shown along Figure 11 is a cross-sectional view of the fuselage 2 taken along line AA in FIG. The fuselage 2 is generally tubular and extends from a nose end 5 to a tail end 6 of the aircraft 1. The fuselage 2 includes a cabin 10. The cabin 10 is a pressurized enclosure within the fuselage 2 defined by a cabin floor 12.

[0032] The cabin 10 is a passenger cabin including seats 14 and overhead boxes 16. The overhead boxes 16 are positioned above the seats 14 and the cabin floor 12 and provide luggage storage. The seats 14 are positioned above and fixed to the cabin floor 12. The cabin floor 12 extends along the entire length of the cabin 10 and defines the lower boundary of the cabin 10. The cabin 10 has a height h extending from the cabin floor 12 to the vertex 9 located at the top of the cabin 10. In this example, only six seats 14 and two overhead boxes 16 are shown, however, it will be understood that there may be any number and / or arrangement of seats 14 and / or overhead boxes 16 in the cabin.

[0033] The aircraft 1 comprises a cabin air distribution system 40 which is arranged to feed air into the cabin 10 and to distribute air between the cabin 10 and the cabin air distribution system 40. Figure 3 It is schematically shown in FIG.

[0034] The air distribution system 40 includes a supply duct 30 arranged to receive air from a mixer unit 24 via a riser duct 32. The mixer unit 24 is configured to receive and mix air from a plurality of sources, including one or more of bleed air from the engines 7, recirculated air from the cabin 10, and atmospheric ram air received from outside the aircraft 1. In other embodiments, the supply duct 30 may be arranged to receive air from an air supply unit that is not a mixer unit.

[0035] The mixer unit 24 supplies air to the supply duct 30, and the air is then supplied to the cabin 10. Figure 2 As more clearly shown in FIG. 2 , the mixer unit 24 is located in the non-pressurized lower luggage compartment 11 below the cabin floor 12 .

[0036] Figure 4 1 shows a perspective schematic diagram of the fuselage 2 and the cabin air distribution system 40. As shown, the supply duct 30 extends along the fuselage 2 in the X direction and has a diameter D1 ( Figure 5 ). Figure 2 , the supply duct 30 is positioned adjacent to the overhead bin 16. In this position, the supply duct 30 does not take up a lot of space within the cabin 10 that may be needed by the seats 14 or other systems. In other examples, the supply duct 30 may be positioned below the overhead bin 16 or above the overhead bin 16. Preferably, the supply duct 30 is positioned in the upper half of the cabin (i.e., in the upper half of the height h of the cabin 10).

[0037] Figure 2 and Figure 4 As shown in FIG. 1 , the supply conduit 30 receives air from the mixer unit 24 through the riser conduit 32. The riser conduit 32 is coupled to the mixer unit 24 and the supply conduit 30 so that the air from the mixer unit 24 is delivered to the supply conduit 30 via the riser conduit 32. Figure 2 , the riser duct 32 extends circumferentially around the inside of the fuselage 2, the circumferential direction being conventionally referred to as the "frame" direction. In this example, only one riser duct 32 is shown in fluid communication with the supply duct 30. However, multiple riser ducts 32 may couple the mixer unit 24 to the supply duct 30.

[0038] Connecting multiple riser ducts 32 to the supply duct 30 helps to reduce the mass flow of air passing through the riser ducts 32 and into the supply duct 30. Therefore, this arrangement reduces the acoustic noise in each supply duct 30. On the other hand, minimizing the number of riser ducts is advantageous because it reduces the overall weight of the system. Preferably, the supply duct 30 is fed with air by less than five riser ducts.

[0039] exist Figure 2 and Figure 4 In the example of , the supply duct 30, the riser duct 32 and the associated outlets 62, 64 are arranged on the port side of the nacelle, and the same system with the supply duct 30c, the riser duct 32c and the associated outlets 62c, 64c is arranged on the starboard side of the nacelle. Each riser duct 32, 32c can be supplied by the same mixer unit 24.

[0040] Figure 5 1 is a schematic diagram of a cabin air distribution system 40 located on the port side of the cabin. The duct arrangement shown comprises a supply duct 30, a plurality of branch ducts 52, 54 and a plurality of outlets 62, 64. The supply duct 30 is arranged to deliver air to the cabin 10 via the branch ducts 52, 54 and the outlets 62, 64. The flow of air is indicated by arrows 13.

[0041] The outlets include an upper outlet 62 and a lower outlet 64. The terms "upper" and "lower" refer to the height level in the XYZ reference system of the aircraft. Therefore, in the reference system of the aircraft, the upper outlet 62 is located at a higher level (in the Z direction) than the lower outlet 64.

[0042] like Figure 2 As shown in , the upper outlet 62 is positioned at a higher level than the supply duct 30 and at a higher level than the overhead box 16 , while the lower outlet 64 is positioned at a lower level than the supply duct 40 and at a lower level than the overhead box 16 .

[0043] The branch duct includes an upper branch duct 52 and a lower branch duct 54. Likewise, the terms "upper" and "lower" represent the height levels in the XYZ reference system of the aircraft. Therefore, in the reference system of the aircraft, the upper branch duct 52 is located at a higher level (in the Z direction) than the lower branch duct 54.

[0044] The upper branch ducts 52 each feed air into one of the upper outlets 62. The lower branch ducts 54 each feed air into one of the lower outlets 64. Figure 5 In the example shown in , each branch duct feeds air into only a single outlet 62 , but in other embodiments each branch duct may feed air into multiple outlets.

[0045] Each branch pipe 52, 54 is connected to the supply pipe 30 at a corresponding joint. Figure 5 As shown in FIG. 1 , each junction is substantially T-shaped, wherein the branch pipes 52 , 54 meet the supply pipe 30 at a 90° angle at the junction.

[0046] In this example, each lower engaging portion of the upper branch pipe 52 is arranged to be opposite to the lower engaging portion of the lower branch pipe 54. In other embodiments, the upper engaging portions and the lower engaging portions may be offset from each other in the X direction so that they are not opposite to each other.

[0047] The diameter D2 of each branch duct is smaller than the diameter D1 of the supply duct 30. This helps to minimize any pressure loss of the gas flow 13 between the supply duct 30 and the branch ducts 52,54.

[0048] Figure 6 6. The outlets 62, 64 are shown in more detail in FIG. Each outlet 62, 64 includes a plenum 62a, 64a having a plurality of slots (not shown). The slots are in fluid communication with the nacelle 10 such that air flows from the plenum 62a, 64a into the nacelle 10 via the slots.

[0049] Conventional aircraft cabin air distribution systems supply air from a main supply duct located at floor level, requiring a large number of circumferentially extending riser ducts.

[0050] The cabin air distribution system 40 is advantageous because the supply duct 30 is positioned well above floor level and close to the outlets 62, 64, which can reduce the overall length of ducting required to connect the supply duct 30 to the outlets 62, 64. This reduces friction pressure losses, so the mixer unit 24 can operate at a lower pressure. It also reduces weight, thereby reducing fuel burn of the engine 7.

[0051] The diameter D1 of the supply conduit 30 may also be reduced compared to conventional systems, resulting in further weight savings.

[0052] This system has a large number of joints between the branch pipes and the supply pipes, but the advantages outlined above outweigh this disadvantage.

[0053] exist Figure 7 In the example of FIG. 1 , the cabin 10 has three air distribution zones: a front zone 90, a middle zone 92, and a rear zone 94. Each zone receives air from a dedicated cabin air distribution system having a plurality of air distribution zones. Figure 3 The air supplied to the zones 90, 92, 94 may have different flow rates and / or different temperatures.

[0054] Each dedicated cabin air distribution system comprises a supply duct 130, 230, 330, which supplies air to a respective set of outlets via upper branch ducts and lower branch ducts. The supply ducts 130, 230, 330 are each connected to the mixer unit 24 via a respective riser duct 132, 232, 332. The supply ducts 130, 230, 330 are all located on the same (port) side of the fuselage.

[0055] Figure 7 The cabin air distribution system located on the port side of the nacelle is most clearly shown. An identical set of cabin air distribution systems is provided on the starboard side of the nacelle.

[0056] although Figure 7 Three zones are shown in FIG. 2 , each having a port supply duct and a starboard supply duct, but it will be appreciated that any number of supply ducts may be used in the fuselage 2 .

[0057] When the word "or" appears, this will be interpreted as meaning "and / or" such that the referred items are not necessarily mutually exclusive and can be used in any appropriate combination.

[0058] Although the invention has been described above with reference to one or more preferred embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.

Claims

1. An aircraft cabin air distribution system, comprising: body; a nacelle in said fuselage; Supply pipelines; a plurality of outlets configured to feed air into the cabin, the outlets including an upper outlet positioned at a higher level than the supply duct and a lower outlet positioned at a lower level than the supply duct; as well as A plurality of branch ducts are configured to deliver air from the supply duct to the outlets, wherein each branch duct is connected to the supply duct at a corresponding joint, and the branch ducts include upper branch ducts and lower branch ducts, the upper branch ducts each deliver air to one or more of the upper outlets, and the lower branch ducts each deliver air to one or more of the lower outlets.

2. The aircraft cabin air distribution system according to claim 1, wherein: Each joint of the upper branch pipe is arranged opposite to the joint of the lower branch pipe.

3. An aircraft cabin air distribution system according to any preceding claim, wherein: Each branch pipe is connected to the supply pipe at a corresponding joint at an angle of 90°.

4. An aircraft cabin air distribution system according to any preceding claim, wherein: The cabin includes a plurality of overhead boxes, the upper outlet is positioned at a higher level than the overhead boxes, and the lower outlet is positioned at a lower level than the overhead boxes.

5. An aircraft cabin air distribution system according to any preceding claim, wherein: The supply conduit is a first supply conduit, and the system further comprises: a second supply pipeline; a plurality of second outlets configured to feed air into the cabin, the second outlets comprising an upper second outlet located at a higher level than the second supply duct and a lower second outlet located at a lower level than the second supply duct; and A plurality of second branch pipes, wherein the second branch pipes are configured to deliver air from the second supply pipe to the second outlet, wherein each second branch pipe is connected to the second supply pipe at a corresponding joint, and the second branch pipes include upper second branch pipes and lower second branch pipes, the upper second branch pipes each deliver air to one or more of the upper second outlets, and the lower second branch pipes each deliver air to one or more of the lower second outlets.

6. An aircraft cabin air distribution system according to claim 5, wherein: The first supply duct is located on the port side of the fuselage, and the second supply duct is located on the starboard side of the fuselage.

7. The aircraft cabin air distribution system according to claim 5, wherein: The first supply duct and the second supply duct are located on a same side of the fuselage.

8. An aircraft cabin air distribution system according to claim 5, 6 or 7, the system further comprising: Air supply unit; one or more first riser ducts for feeding air from the air supply unit to the first supply duct; and one or more second riser ducts for feeding air from the air supply unit to the second supply duct.

9. An aircraft cabin air distribution system according to any preceding claim, the system further comprising: Air supply unit; and one or more riser ducts for feeding air from the air supply unit to the supply duct.

10. An aircraft cabin air distribution system according to claim 8 or 9, wherein: The fuselage includes a cabin floor; and the air supply unit is positioned outside the cabin and below the cabin floor.

11. An aircraft cabin air distribution system according to claim 8, 9 or 10, wherein: The cabin is pressurized; and the air supply unit is positioned in a non-pressurized portion of the fuselage.

12. An aircraft cabin air distribution system according to any one of claims 8 to 11, wherein: The air supply unit includes a mixer unit configured to receive and mix air from a plurality of sources.

13. An aircraft cabin air distribution system according to any preceding claim, wherein: The (or each) supply duct extends in the longitudinal direction of the fuselage.

14. An aircraft comprising an aircraft cabin air distribution system according to any preceding claim.

15. A method of feeding air into a cabin of a fuselage, the method utilizing an aircraft cabin air distribution system according to any preceding claim, the method comprising: feeding air from the supply duct via the supply duct and respective junctions of the supply duct to the outlet; and feeding air from the outlet into the nacelle.

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