Condensation water drainage support equipped with a means of fixing to an insulation mattress
Patent Information
- Application Number
- FR2022004761
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2022-05-19
- Publication Date
- 2026-08-14
- Estimated Expiration
- 2042-05-19
AI Technical Summary
Existing condensation water drainage systems in aircraft require direct attachment to the fuselage wall, complicating installation and increasing installation time.
A drainage support system with an elbow conduit featuring removable fixing means, allowing it to be attached to an insulation mattress without direct attachment to the fuselage, using notches and washers for secure assembly.
Facilitates quick and easy installation of the drainage system by eliminating the need for direct fuselage attachment, maintaining a secure watertight connection while simplifying handling and manufacturing.
Smart Images
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Abstract
Description
Description Title of the invention: Condensation water drainage support equipped with a means for fixing to a INSULATION MATTRESS
[0001] — The present invention relates to a condensation water drainage support in an aircraft as well as the aircraft equipped with such a drainage support.
[0002] — In an aircraft such as a commercial airplane, the air in the passenger cabin is rela- Phytically humid. Passengers contribute significantly to this humidity by breathing. Furthermore, when the aircraft is at altitude, particularly at an altitude of During the cruise, the outside air temperature is very low and the aircraft structure is therefore very cold. When the aircraft descends, the water contained in the cabin air Passengers condense on the cold walls of the fuselage. A drainage system is then designed to convey the water that had condensed on the cabin walls passengers from this cabin to a low point on the fuselage. Thus, the water is first collected in gutters located in the upper part of the passenger cabin, then is conveyed via drainage pipes to the lower area. The pipes drainage points are spaced apart longitudinally along the aircraft. A thermal insulation mat is placed next to the fuselage to protect the passengers against the cold and extends from the passenger cabin to a lower area of the fuselage.
[0003] French patent FR2977568 describes such a drainage system using the mattress thermal insulation to drain condensation water to the lower area of the aircraft. The drainage system includes a mattress penetration device to guide the condensation water to the side of the mattress facing the wall of the fuselage: the condensation water is then guided between the fuselage wall and the side of the mattress facing him. The passage device needs to be fixed to the fuselage wall, directly or indirectly. However, given their large number, This complicates the implementation of the drainage system.
[0004] — Although this drainage system is satisfactory, it would be interesting to be able to to have a system that does not require attachment to the fuselage wall, facilitating its easy to set up and offering reduced installation time.
[0005] — The present invention aims to provide a drainage support for the drainage of condensation water including an angled conduit with an angled section featuring a part equipped with removable fastening means, a first washer of fixed maintenance of said conduit and separating said part equipped with fastening means removable from another part of the conduit having said angled part and a second removable retaining washer having an opening adapted to allow its removable assembly with said fixing means. The invention thus offers an alternative to fixing to the fuselage, thereby facilitating the installation of the aircraft's drainage network. The invention provides at least one of the following optional features, taken individually or in combination. The fastening means are in the form of notches. The angled section is such that the axes XX and Y-Ÿ of the conduit on either side of the angled section form an angle greater than 90 degrees. The faces of the washers, which face each other when the second washer is in the installed position, are in planes PI, P2 perpendicular to the axis XX of the part and are parallel to each other. The present invention also relates to an aircraft comprising a plurality of drainage channels for condensation water formed inside the fuselage, an insulation mat having two opposite faces and at least one through-hole, one face oriented towards the fuselage wall and one face oriented towards the interior of the aircraft, at least one of the channels extending partly along the fuselage inside the aircraft, characterized in that it comprises a drainage support including an angled conduit, provided with an angled portion, having a portion connected to said channel and having an opposite portion provided with removable fastening means passing through the mat via said through-hole,a first retaining washer fixed to said conduit between the part equipped with removable fixing means and the other part bearing against the face of the mattress, and a second removable retaining washer having an opening adapted to allow its removable assembly with said fixing means on the other side of the mattress, the second washer bearing against the face of the mattress. The invention provides at least one of the following optional features, taken individually or in combination. The part equipped with removable fixing means protrudes from the second retaining washer once it is placed against the mattress. The fastening means are in the form of notches. The angled part is such that once the support is connected to the pipe, it allows the axis XX of the part equipped with means for fixing the support to be perpendicular to the face of the mattress. Other objects, features and advantages will become apparent from the following description of the invention, given by way of non-limiting example only, with reference to the attached drawings in which: [Fig.1] is a side view of an aircraft equipped with a drainage support according to the presents the invention; [Fig.2] is a cross-sectional view along plane A-À of [Fig.1]; [Fig.3] is a schematic side view of the drainage support according to the present invention placed on an aircraft insulation mattress; [Fig.4] is a perspective view of the drainage support according to the present invention. Figures 1 and 2 depict an aircraft 2 comprising a drainage system 4. Aircraft 2 includes a fuselage 6, a cross-sectional view AA of which is shown in [Fig. 2]. In this cross-sectional view, the interior of the aircraft is divided into several zones according to the dimensions of the fuselage. According to the shape shown, a first passenger zone Z1 is delimited by the semi-circular upper part of the fuselage and by a horizontal partition or floor 8. Below this floor, a zone Z2 extends to the lowest part of the fuselage. Zone Z2 can be a cargo area containing containers and / or equipment of any type. Condensation water that forms in zone Z1 (passenger cabin) is collected in zone Z2. Other configurations are possible in which the definition and number of zones vary. A thermal insulation mat 10 is positioned opposite the fuselage wall 12 over almost its entire length, excluding a very low portion of the lower zone Z2 as shown in [Fig. 2]. The insulation mat 10 may be composed of several sections joined or overlapped, depending on the aircraft configuration. It is attached to the wall by known fastening systems 19, which will not be described further as they are not the subject of this application. The insulation mat 10 shown in Figures 2 and 3 has a first face 14 facing the fuselage wall 12 and a second, opposite face 16 facing the interior of the aircraft, specifically the passenger cabin. The condensate drainage system comprises several drainage pipes 4 spaced longitudinally along the length of the aircraft and on each of opposite sides of the fuselage wall 12, as shown in [Fig. 2] with the two pipes 18, 20. The number and arrangement of the pipes may vary from one aircraft configuration to another. As with the mattress 10, the pipe fastening systems 4 are of a known type and will not be described or illustrated as they are not part of the present invention. In the embodiment illustrated in [Fig. 2], a first drainage pipe 18 extends from a high point H located in the upper part of the upper zone Z1 towards the floor, substantially following the contour of the fuselage 6. At point H, condensation is collected by gutters to which drainage pipes such as pipe 18 are connected directly or indirectly. Another drainage pipe 20 is located near the fuselage wall 6. symmetrically opposite a central vertical longitudinal plane (considering the aircraft resting on a horizontal surface). Pipes 18 and 20 extend to floor 8, which they pass through to enter the intermediate zone Z2. Numerous other pipes are part of the network and have not been shown; some, for example, extend from the lower part of the aircraft doors where water that forms in their vicinity is collected. The pipes are made of a flexible material such as silicone. Versilic-type pipes (registered trademark) may be used, for example. A few centimeters vertically below the floor, as shown by the circled portion in [Fig. 2] and schematically represented in [Fig. 3], a drainage support 22 is sealed to a drainage pipe, specifically those illustrated 18 and 20, and passes through the insulation layer 10 to guide condensation water 24 between the layer 10 and the fuselage wall 12. The space between the layer 10 and the fuselage wall 12 acts as a drain and replaces the pipes provided in area Z2. As many drainage supports as the aircraft's pipe network requires are installed. In the present invention, the support 22 is positioned approximately 2 to 10 cm below the floor, but any other location is possible. The drainage support 22 comprises a bent conduit 25 having a portion 25' with removable fastening means 26 such as notches 26', a first retaining washer 28 fixed to said conduit 25 between the notched portion 25° and the unnotched portion 25' of the conduit 25, and a second removable retaining washer 30 having an orifice 32 whose diameter is adapted to allow the washer 30 to snap onto the notches 26' of the portion 25' and to allow its removable assembly with it. In the illustrated form, the portion 25° extends from one end 27 of the conduit to the washer 28, but it could extend beyond. The second removable washer 30 is shown not fixed to the conduit 25 in [Fig. 4], lying flat on any surface.In the illustrated embodiment, when the support 22 is in place, installed on the mattress, the end 27 of the conduit 25 of the support 22 is located at a distance from the face 14 of the mattress, protruding from the second washer 30, and the condensation water 24 does not flow onto the surface of the mattress but largely into the free space between the wall 12 of the fuselage and the mattress 10. The length of the part 25' is greater than the thickness of the mattress 10 and the second washer 30. When the support 22 is in place, installed on the mattress, the angled part 29 is located at a distance from the washer 28. In the illustrated embodiment, the angled portion 29 of the conduit 25 is such that the axes XX and YY of the conduit 25 on either side of the angled portion form an angle greater than 90 degrees. In this way, the conduit 25 is oriented in a Direction allowing connection to a flexible pipe 18, 20. Known fastening means allow a watertight connection between the pipe 18 shown in the figure and the support 22. For example, the conduit 25 of the support 22 has a diameter slightly smaller than that of the pipe 18: the unserrated portion 25' of the conduit 25 is inserted into the pipe 18, and a hose clamp 31, for example a ty-rap type, secures the pipe 18 around the conduit 25 of the support 22. The tightness of the ty-rap, combined with the flexibility of the pipe 18, ensures a watertight seal. When the second washer 30 is clicked onto the notched part 25°, the planes P1, P2 in which are respectively the two faces 28A, 30A of the washers 28, 30 intended to be in contact with the mattress 10 (in contact on the [Fig.3]) are parallel to each other and perpendicular to the axis XX of the notched part 25” of the conduit 25.In this embodiment, the 25" section of the duct 25 has a constant diameter. According to another particular embodiment, the first washer 28 is also removable. In this case, a locking system is provided to lock it in position between the 25° and 25°' parts of the conduit 25. The installation of the support 22 is carried out as follows: the unnotched portion 25° of the conduit 25 is fixed in a watertight manner to the end of a pipe 18, as previously described, for example, using the clamp 31. The notched portion 25' of the conduit 25 is inserted into a through hole 36 in the mat provided for this purpose until the first washer 28 comes into contact and rests against the face 16 of the mat. The angled portion 29 of the conduit 25 allows the notched portion to be inserted along an axis XX perpendicular to the face 16 of the mat. The second washer 30 is then snapped onto the notched portion 25' until it comes into contact and rests against the face 14 of the mat. The two washers 28 and 30, resting on the mat, hold the drainage support 22 in position. The notched portion extends in the XX direction of the second washer 30 and is protruding from it. The drainage support offers numerous advantages. It eliminates the need to modify the existing piping network in zone Z1. Given its simplicity and the fact that it doesn't require attachment to any aircraft structure, installation is quick and easy. The support is easy to handle and simple to manufacture.
Claims
Demands
1. Drainage support for the drainage of condensation limescale (24) in an aircraft comprising a bent conduit (25), provided with a part angled (29), having a part (25') equipped with fastening means removable (26), a first retaining washer (28) fixed to said conduit (25) and separating said part (25') from another part (25') of the conduit having said angled portion (29), and a second washer (30) removable retainer having an opening (32) adapted for to allow its removable assembly with said fastening means (26).
2. Drainage support according to claim 1, characterized in that the The fastening means (26) are in the form of notches (26°).
3. Drainage support according to claim 1 or 2, characterized in that the angled part (29) is such that the axes XX and YY of the conduit on either side of the angled part (29) form an angle greater than 90 degrees.
4. Support according to any one of claims 1 to 3, characterized in that the faces (28A, 30A) of the washers (28, 30) facing each other when the second washer (30) in installed position, are in planes P1, P2 perpendicular to the axis XX of the part (25') equipped with means of removable fixing (26) and are parallel to each other.
5. Aircraft comprising a plurality of drainage pipes (4) condensation water (24) formed inside the fuselage, a mattress insulation (10) having two opposite faces (14, 16) and at least one through opening (36), one face (14) oriented towards the fuselage wall and a face (16) oriented towards the interior of the aircraft, at least one of the ca- nalisations (18, 20) extending partly along the fuselage (6) to the interior of the aircraft, characterized in that it includes a support for drainage (22) comprising a bent conduit (25), provided with a part elbow (29), having a part (25'') linked to said pipeline (18, 20) and having an opposite part (25') equipped with fastening means removable (26) passing through the mattress by said orifice (36), a first retaining washer (28) fixed to said conduit between the part (25') equipped removable fastening means (26) and the part (25'') bearing on the face (16) of the mattress and a second retaining washer (30) removable having an opening (32) adapted to allow its as- removable assembly with said fastening means (26) on the other side of the mattress, the second washer (30) resting on the face (14) of the mattress.
6. Aircraft according to claim 5, characterized in that the part (25°) equipped with removable fixing means (26) is projecting from the second retaining washer once positioned against the mattress.
7. Aircraft according to claim 5 or 6, characterized in that the fastening means (26) are in the form of notches (26°).
8. Aircraft according to any one of claims 5 to 7, characterized in that the The angled part (29) is such that once the support is attached to the pipe (18, 20), it allows the XX axis of the part (25') of the support equipped with removable fixing means (26) to be perpendicular to the face (16) of the mattress.