A passive cooling device

Abstract

A passive cooling device for an electrical apparatus located in the cabin of an aircraft. The passive cooling device comprises a housing arranged to house an electrical apparatus; an inlet in the housing arranged to cooperate with an opening formed in the boundary between the cabin and cargo hold of an aircraft to allow the flow of air between the cargo hold and the interior of the housing; and an outlet in the housing above the inlet arranged to allow the flow of air between the interior of the housing and the aircraft cabin. The housing is shaped and configured such that, when an electrical apparatus is housed within the housing, air can flow through the interior of the housing past the electrical apparatus from the inlet and the outlet. Figure 1 to accompany abstract on publication.

Description

[0001] P040472GB

[0002] - 1 - A passive cooling device

[0003] Field of the Invention

[0004] The present invention concerns a passive cooling device for an electrical apparatus located in the cabin of an aircraft.

[0005] Background of the Invention

[0006] Electrical apparatuses are provided in the cabins of aircraft for various reasons, including providing power to in-flight entertainment systems and actuating seat movement. Such electrical apparatuses can overheat, especially when multiple electrical apparatuses are provided in close proximity, if methods to cool the electrical apparatus are not used.

[0007] It is known to use active cooling systems to cool electrical apparatuses located in an aircraft cabin. For example, in an electrical apparatus cooling system of the prior art, air cooled in a cabin air conditioning system is directed over the electrical apparatus to cool the apparatus. These active cooling systems require electrical power and are themselves at risk of failure.

[0008] Additionally, active cooling systems for aircraft cabin electrical apparatuses are often bulky, and occupy space in the cabin that could otherwise be used for other purposes. Electrical apparatuses with active cooling systems are often located under aircraft seats, in space that would preferably be used for storage of passenger belongings.

[0009] The present invention seeks to mitigate the above-mentioned problems. Alternatively, or additionally, the present invention seeks to provide an improved device for cooling an electrical apparatus of an aircraft cabin.P040472GB

[0010] -2- Summary of the Invention

[0011] The present invention provides, according to a first aspect, a passive cooling device for an electrical apparatus located in the cabin of an aircraft, the passive cooling device comprising:

[0012] a housing arranged to house the electrical apparatus;

[0013] an inlet in the housing arranged to cooperate with an opening formed in the boundary between the cabin and cargo hold of the aircraft to allow the flow of air between the cargo hold and the interior of the housing; and

[0014] an outlet in the housing above the inlet arranged to allow the flow of air between the interior of the housing and the aircraft cabin,

[0015] wherein the housing is shaped and configured such that, when an electrical apparatus is housed within the housing, air can flowthrough the interior of the housing past the electrical apparatus from the inlet and the outlet.

[0016] In flight, the air of an aircraft cabin and the air of the aircraft cargo hold are pressurised to the same pressure. The air of the cabin is typically heated for passenger comfort, while the air of the cargo hold is typically unheated and so colder than the air of the cabin. By providing a device with an inlet arranged to cooperate with an opening in the boundary between the cabin and the cargo hold, and an air passage in the interior of the housing of the device between the inlet and an outlet formed in the housing, air from the cargo hold is able to flow through the device and into the aircraft cabin. As the cargo hold air is cooler than the air of the cabin, this flow of air acts to cool an electrical apparatus positioned within the air passage. Further, in use, the electrical apparatus produces heat. This heats the air surrounding the electrical apparatus, causing it to rise and flowthrough the outlet of the housing into the cabin. This causes cooler airfrom the cargo hold to be drawn into the housing of the device to replace the heated air flowing out of the housing. In this way, the passive cooling device acts as a chimney, drawing cooler air from theP040472GB

[0017] -3-cargo hold past the electrical apparatus to cool it, with the electrical apparatus itself driving the cooling process.

[0018] In addition, in a rapid decompression event the openings in the boundary between the cabin and cargo hold will contribute to the alleviation of floor pressure. As a consequence, less air will need to flowthrough side wall decompression vents, meaning that nearby space could be used for example to allow additional seat width.

[0019] The device may be free of any active cooling mechanisms.

[0020] The electrical apparatus may be part of an in-flight entertainment system, an actuator, or any other electrical apparatus present within the aircraft cabin. The electrical apparatus may be connected to a further electrical apparatus, such as a screen or charging dock, by wiring.

[0021] The boundary may be the floor of the cabin, or a wall of a cabin through which airfrom the cargo hold can be accessed, for example.

[0022] The housing may be enclosed by a top wall, a base wall and at least one side wall connecting the top wall and the base wall, and the inlet may be formed in the base wall of the housing. By providing the inlet in the base wall of the housing, the inlet may provided at the lowest part of the device when the device is installed in an aircraft.

[0023] The housing may be enclosed by a top wall, a base wall and at least one side wall connecting the top wall and the base wall, and the outlet may be formed in the at least one side wall. By providing the outlet in a side wall of the housing, the risk of items being dropped into the device from the cabin is reduced. It is desirable to prevent items being dropped into the device, as such items may block the air passage in the housing, which may reduce the ability of the device to cool the electrical apparatus. Items dropped into the device may also fall though into the cargo hold, where they would be difficult to retrieve. Additionally, by providing theP040472GB

[0024] -4-outlet in the side wall of the housing, air flowing out of the device may be more effectively directed away from the device.

[0025] The housing may be enclosed by a top wall, a base wall and at least one side wall connecting the top wall and the base wall, and the at least one side wall may be formed of flexible material. When installed, the device may be located adjacent to a support structure such as the wall of a passenger accommodation orto an aircraft seat. The device may be supported by the support structure. By providing a device in which the at least one side wall is formed of flexible material, load sharing between the device and the support structure may be reduced, reducing the risk of warping and damage of the housing.

[0026] The passive cooling device may be formed entirely or partially of flexible material.

[0027] The passive cooling device may further comprise a cover at least partially covering the outlet. The cover can allow the flow of air through the outlet. The cover can help prevent items from being dropped through the outlet into the device.

[0028] The cover may comprise an inlet arranged to cooperate with the outlet of the housing, and an outlet provided above the inlet of the cover.

[0029] The passive cooling device may comprise an electrical apparatus housed within the passive cooling device.

[0030] The present invention provides, according to a second aspect, an aircraft seat comprising an electrical apparatus and a passive cooling device havingthe features described above, wherein the electrical apparatus is housed within the passive cooling device.

[0031] By providing an aircraft seat comprising a passive cooling device, the device may be supported by the aircraft seat. The device may be integral to the seat, and so the riskof the device becoming a trip hazard is reduced.P040472GB

[0032] -5- The present invention provides, according to a third aspect, an aircraft passenger accommodation unit comprising an aircraft seat, a wall at least partially surroundingthe seat, an electrical apparatus, and the passive cooling device having the features described above, wherein the electrical apparatus is housed within the passive cooling device and the passive cooling device is adjacent to the wall.

[0033] By providing a passive cooling device adjacent to the wall of a passenger accommodation unit, the device can be supported by the wall. The device may also be provided in an otherwise unutilised portion of the passenger accommodation unit, or in a part of the passenger accommodation unit that is inaccessible to an aircraft passenger. This may reduce wasted space within the passenger accommodation unit and reduce the risk of the device becoming a trip hazard.

[0034] The passenger accommodation unit may further comprise a vent for venting air from the cabin of the aircraft to the cargo hold of the aircraft. By providing a passenger accommodation unit with a vent for venting air from the cabin to the cargo hold of the aircraft, air that flows through the air passage of the device from the cargo hold to the cabin may be replaced by air flowing through the vent from the cabin to the cargo hold. This may allowthe air pressure in the cabin to be maintained at the air pressure of the cargo hold, allowing the passive cooling device to function more effectively.

[0035] The present invention provides, according to a fourth aspect, an aircraft comprising:

[0036] a cabin;

[0037] a cargo hold positioned beneath the cabin;

[0038] a boundary between the cabin and the cargo hold, wherein the boundary has formed in it an opening to allow the flow of air between the cargo hold and the cabin;P040472GB

[0039] -6- a passive cooling device having the features described above located in the cabin of the aircraft, wherein the inlet of the passive cooling device cooperates with the opening formed in the boundary to allow the flow of air between the cargo hold and the interior of the housing of the passive cooling device; and

[0040] an electrical apparatus housed within the passive cooling device.

[0041] It will of course be appreciated that features described in relation to one aspect of the present invention may be incorporated into other aspects of the present invention.

[0042] Description of the Drawings

[0043] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:

[0044] Figure 1 shows a cross-section of a passive cooling device according to an embodiment of the present invention;

[0045] Figure 2 shows the passive cooling device of Figure 1 installed on the floor of an aircraft;

[0046] Figure 3 shows the passive cooling device of another embodiment of the invention installed in an aircraft passenger accommodation unit; and

[0047] Figure 4 shows a passive cooling device according to another embodiment of the present invention.

[0048] Detailed Description

[0049] A passive cooling device in accordance with an embodiment of the invention is now described with reference to Figures 1 and 2.

[0050] Figure 1 shows a cross section of the passive cooling device 100. The device 100 comprises a hollow housing 101. The housing 101 comprises a base portion 103 with vertically extending side walls 103a, 103b, which are open at the bottomP040472GB

[0051] -7 -forming an inlet 105 to the housing 101. The side walls 103a, 103b meet at theirtops a body portion 104 of the housing 101 , which is slightly wider than the base portion 103, and similarly has vertically extending side walls 104a, 104b. However, rather than extending directly vertically upwards, the side walls 104a, 104b of the body portion 104 are angled approximately 100from vertical, in the direction of the top of the side wall 104a. A top wall 102 extends across the top of the body portion 104 of the housing 101 between the side walls 104a, 104b.

[0052] An outlet 106 from the housing 101 is formed by a gap in the upper part of the side wall 104b. The device 100 further comprises a cover 107, which is mounted on the exterior of the housing 101 over the outlet 106. The cover 107 has a base wall 108 which is fixed to the side wall 104b below the outlet 106 and extends horizontally outwards from the side wall 104b, a side wall 109 that extends vertically from the side wall 109 to a position above the top wall 102 of the body portion 104 of the housing 101, and a top wall 110 which horizontally from the side wall 109 in the direction of the body portion 104 of the housing 101. As the top wall 110 is vertically above the body portion 104 of the housing 101 , an outlet 111 is formed between the cover 107 and the body portion 104 of the housing 101. In this way, air is able to flow between the interior of the housing 101 and its exterior via the outlet 106 and outlet 111 , as described in more detail below.

[0053] An electrical apparatus 200 is housed within the housing 101. There is a gap between the outside of the electrical apparatus 200 and the side walls 104a, 104b and top wall 102 of the body portion 104 of the housing 101. In this way, air is able to flow within the housing 101 around the electrical apparatus 200, again as described in more detail below.

[0054] Figure 2 shows the device 100 installed on the floor of an aircraft. The floor 304 is the floor of the cabin 301 of the aircraft, where passengers are located during a flight of the aircraft, and separates the cabin 301 from the cargo hold 302. The device 100 is installed on the floor 304 so that the inlet 105 of the device 100 isP040472GB

[0055] -8-positioned over a corresponding opening 303 in the floor 304. The device 100 is secured to the floor by bolts. In other embodiments, the device 100 is secured to the floor by clips, or the inlet extends through the floor to the cargo hold 302 to secure the device 100, or any other suitable method of fixing the device 302 to the floor 304 is used. In this way, air is able to flow between the interior of the housing 101 and the cargo hold 302 via the inlet 105 and the opening 303 in the floor 304, again as described in more detail below.

[0056] During a flight of the aircraft, the air in the cargo hold 302 will be pressurised to the same pressure as the air in the cabin 301. However, the air in the cabin 301 will be warmer than the air in the cargo hold 302. This will be because the air in the cabin 301 is heated, but also passengers and electrical apparatus present in the cabin 301 will generate heat.

[0057] When the electrical apparatus 200 within the housing 101 of the device 100 is used, it will generate heat. This will cause it to heat the surrounding air within the housing 101. Due to convection, the heated air will rise, and will flow out of the outlet 106 of the housing 101 into the cover 107, and then through the outlet 111 of the cover 107 into the cabin 301 generally. This is particularly the case as the side walls 104a, 104b of the body portion 104 are angled towards the top of the side wall 104a, so making it easier for rising air to pass through the outlet 106 towards the top of the side wall 104b. As there is a path for air within the housing 101 between the outlet 106 and the inlet 105, this will in turn draw cooler air from the cargo hold 302 through the inlet 105 into the housing 101, and past the electrical apparatus 200, cooling the electrical apparatus 200. In this way, the heat generated by the electrical apparatus 200 creates a chimney effect within the device 100, drawing cool air past the electrical apparatus 200 to cool it.

[0058] A passive cooling device in accordance with another embodiment of the invention is now described with reference to Figure 3.P040472GB

[0059] -9- The passive cooling device 200 of the present embodiment is similar to that of the above embodiment, except as described below. The device 200 is installed in an aircraft passenger accommodation unit 400 of an aircraft. The aircraft again comprises a cabin 301 and a cargo hold 302 separated from one another by a floor 304, with an opening 303. The aircraft passenger accommodation unit 400 comprises an aircraft seat (not shown in Figure 3) and a privacy wall 401 at least partially surrounding the aircraft seat. Both the aircraft seat and privacy wall are mounted to the floor 304.

[0060] The device 200 is located adjacent to the privacy wall 401 , with the side wall 104a of the device 100 supported by the privacy wall 401. In contrast to the device 100 of the above embodiment, the side walls 112a and 112b of the base portion 112 of the device 200 are formed of a flexible material. Thus, the side walls 112a and 112b of the device 200 do not load-share, i.e. do not transmit any of the load of the aircraft passenger accommodation unit 400 on the floor 304, so preventing them from becoming warped or damaged.

[0061] A passive cooling device in accordance with another embodiment of the invention is now described with reference to Figure 4.

[0062] The passive cooling device 500 comprises two hollow housings 501 a, 501 b, each of which is on the top of either side of a base portion 503, and which have housed within them electrical apparatuses 200a and 200b respectively. The housing 501 a is formed of a top wall 502a, and side walls 504a and 504b. The outer side wall 504a has an opening 505a towards its top.

[0063] The housing 501b is identical to the housing 501a, but reflected around a vertical plane through the middle of the device 500. Thus, the housing 501b again has a top wall 502b, side walls 504c and 504d, and the opposite outer side wall 504d again has an opening 505b towards its top.P040472GB

[0064] - 10- The base portion 503 has a top wall 503a that extends between the inner side wall 504b of the housing 501 a and the inner side wall 504c of the housing 501 b. The base portion 503 further has a base wall 506 that extends between the outer side wall 504a of the housing 501 a and the outer side wall 504d of the housing 501 b, and has in its middle, i.e. between the housing 501 a and the housing 501 b, an inlet 507.

[0065] In use, the inlet 507 can be positioned over an opening in the floor of an aircraft cabin, to allow air to pass from the cargo hold into the interior of the device 500. In particular, heat generated by the electrical apparatus 200a will cause heated air to flow out of the outlet 505a, drawing cooler air from the cargo into the interior of the housing 501a over the electrical apparatus 200a, to cool it. Similarly, heat generated bythe electrical apparatus 200b will cause heated airto flow out of the outlet 505b, drawing cooler air from the cargo into the interior of the housing 501b over the electrical apparatus 200b. In this way, the single device 500 can provide cooling for both electrical apparatuses 200a, 200b from a single opening to the cargo hold.

[0066] While the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. By way of example only, certain possible variations will now be described.

[0067] In alternative embodiments, the passive cooling device may comprise three or more housings for electrical apparatuses. In embodiments in which the device comprises a plurality of housings, the inlet of each housing may be connected to a single opening which itself includes an inlet arranged to cooperate with an opening in the boundary between the cabin and cargo hold of the aircraft. In such embodiments, the device can provide a branching air passage between the inlet of the duct to through each of the housings to the outlets of the housings.P040472GB

[0068] - 11 - In other embodiments, the housing of the passive cooling device may be configured to house a plurality of electrical apparatuses within the interior of a single housing.

[0069] Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.

Claims

P040472GB- 12- Claims1. A passive cooling device for an electrical apparatus located in the cabin of an aircraft, the passive cooling device comprising:a housing arranged to house an electrical apparatus;an inlet in the housing arranged to cooperate with an opening formed in the boundary between the cabin and cargo hold of an aircraft to allow the flow of air between the cargo hold and the interior of the housing; andan outlet in the housing above the inlet arranged to allow the flow of air between the interior of the housing and the aircraft cabin;wherein the housing is shaped and configured such that, when an electrical apparatus is housed within the housing, air can flowthrough the interior of the housing past the electrical apparatus from the inlet and the outlet.

2. The passive cooling device of claim 1 , wherein the housing is enclosed by a top wall, a base wall and at least one side wall connecting the top wall and the base wall, and the inlet is formed in the base wall.

3. The passive cooling device of claim 1 or claim 2, wherein the housing is enclosed by a top wall, a base wall and at least one side wall connecting the top wall and the base wall, and the outlet is formed in the at least one side wall.

4. The passive cooling device of any preceding claim, wherein the housing is enclosed by a top wall, a base wall and at least one side wall connecting the top wall and base wall, and the at least one side wall is formed of flexible material.

5. The passive cooling device of any preceding claim, further comprising a cover at least partially covering the outlet.P040472GB- 13-6. The passive cooling device of claim 5, wherein the cover comprises an inlet arranged to cooperate with the outlet of the housing, and an outlet provided above the inlet of the cover.

7. An aircraft seat comprising an electrical apparatus and the passive cooling device of any preceding claim, wherein the electrical apparatus is housed within the passive cooling device.

8. An aircraft passenger accommodation unit comprising an aircraft seat, a wall at least partially surrounding the seat, an electrical apparatus, and the passive cooling device of any of claims 1 to 6, wherein the electrical apparatus is housed within the passive cooling device and the passive cooling device is adjacent to the wall.

9. The aircraft passenger accommodation unit of claim 8, further comprising a vent for venting air from the cabin of the aircraft to the cargo hold of the aircraft.

10. An aircraft comprising:a cabin;a cargo hold positioned beneath the cabin;a boundary between the cabin and the cargo hold, wherein the boundary has formed in it an opening to allow the flow of air between the cargo hold and the cabin;a passive cooling device as claimed in any of claims 1 to 6 located in the cabin of the aircraft, wherein the inlet of the passive cooling device cooperates with the opening formed in the boundary to allow the flow of air between the cargo hold and the interior of the housing of the passive cooling device; andan electrical apparatus housed within the passive cooling device.

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