FR3101855A1 - Aircraft fluid discharge device, aircraft propellant assembly comprising such a fluid discharge device and aircraft comprising at least one such fluid discharge device - Google Patents

Abstract

Fluid discharge device for an aircraft, aircraft propellant assembly comprising such a fluid discharge device and aircraft comprising at least one such fluid discharge device The subject of the invention is a fluid discharge device for aircraft, configured to be connected to a support (42) and to pass through an orifice (44) at least one wall (46) separating an interior zone (ZI) and an exterior zone (ZE). This fluid discharge device comprises: at least one body (52), made of composite material or of plastic material, having first and second parts (54, 56) positioned respectively in operation in interior and exterior zones (ZI, ZE ), the first part (54) being connected directly or indirectly to the support (42), a bearing surface (66.2) made of a material capable of forming a fire barrier, spaced from the wall (46), at least one skirt (74) made of a material capable of forming a fire barrier, surrounding the orifice (44), which extends from the wall (46) to the bearing surface (66.2). The fluid evacuation device according to the invention forms an effective fire barrier, while limiting the risk of damage by lightning. Figure 4

Description

Fluid evacuation device for aircraft, aircraft propulsion assembly comprising such a fluid evacuation device and aircraft comprising at least one such fluid evacuation device

The present application relates to a fluid evacuation device for an aircraft, to an aircraft propulsion assembly comprising such a fluid evacuation device as well as to an aircraft comprising at least one such fluid evacuation device.

According to a configuration visible in FIG. 1, an aircraft 10 comprises several thruster assemblies 12 which are positioned under the wing 14 of the aircraft 10. A thruster assembly 12 comprises a nacelle 16, an engine 18 positioned inside the nacelle 16 as well as a fluid evacuation device 20 positioned in the lower part of the nacelle 16.

As illustrated in FIG. 3, the nacelle 16 comprises at least one wall 22, separating an interior zone ZI and an exterior zone ZE, comprising an orifice 24 through which the fluid evacuation device 20 passes. This wall 22 can be made of material composite. To fix the fluid evacuation device 20, the thruster assembly 12 comprises a support, metallic, positioned in the interior zone ZI and spaced from the wall 22.

According to one embodiment, the fluid evacuation device comprises a body 28, connected to the support and passing through the wall 22, as well as at least one drain 30, positioned inside the body 28, having an end 30.1 emerging via an escape hole 32 in the outer zone ZE. In the outer zone ZE, the body 28 has aerodynamic shapes configured to limit drag.

The body 28 has a section adapted to that of the orifice 24 of the wall 22 of the nacelle 16 to limit the clearance between the body 28 and the wall 22.

According to a first embodiment, the body 28 of the fluid evacuation device is made of composite material to remedy the problems related to lightning. However, in this case, the body 28 made of composite material does not constitute a fire barrier.

According to a second embodiment, the body 28 of the fluid evacuation device is metallic to form a fire barrier. However, in this case, it does not remedy the problems related to lightning.

The present invention aims to remedy all or part of the drawbacks of the prior art.

To this end, the subject of the invention is a fluid evacuation device for an aircraft, configured to be connected to a support and to pass through, via an orifice, at least one wall separating an interior zone and an exterior zone; the fluid evacuation device comprising at least one body, made of composite material or plastic material, having first and second parts positioned respectively in operation in the inner and outer zones, the first part being connected directly or indirectly to the support, the fluid evacuation device comprising at least one conduit channeling a fluid from the interior zone towards an exhaust hole positioned in the exterior zone.

According to the invention, the fluid evacuation device comprises, or is connected to in operation, a support surface, made of a material capable of forming a fire barrier, spaced from the wall. In addition, the fluid evacuation device comprises at least one skirt made of a material capable of forming a fire barrier, surrounding the orifice, which extends from the wall to the bearing surface.

The fluid evacuation device according to the invention forms an effective fire barrier, while limiting the risks of damage by lightning.

According to another characteristic, each skirt has a tubular shape and comprises a first end configured to be connected to the wall in operation and a second end slightly spaced from the support surface in operation.

According to another characteristic, the fluid evacuation device comprises a plate, made of a material capable of forming a fire barrier, having a first surface configured to be connected to the support and a second surface opposite the first surface, forming the bearing surface.

According to another characteristic, the fluid evacuation device comprises an insert positioned in the body, comprising a wall separated from the wall by a distance approximately equal to 20 mm in operation, concentric with the orifice, having a surface slightly lower to that of the orifice.

According to another characteristic, the body comprises a base having a first face oriented towards the support in operation and a second face opposite the first face, a trunk connected to the second face of the base having a peripheral face and an opposite end face to the base, as well as a recess in the trunk, opening at the level of the first face of the base, having a side face and a bottom spaced from the wall in operation.

According to another characteristic, the insert comprises a tubular wall, a bottom wall at a first end of the tubular wall as well as a flange at a second end of the tubular wall, the tubular wall, the bottom wall and the flange being pressed, respectively, against the side face, the bottom of the recess and the base of the body.

According to another characteristic, the body comprises at least one duct, configured to house a pipe and/or to channel a fluid, opening into the recess. In addition, the plate comprises at least one tube for each duct of the body, projecting with respect to the second surface emerging at the level of the first surface and positioned in the extension of each duct in operation, the insert comprising a through hole at the right of each duct of the body.

The invention also relates to an aircraft nacelle comprising at least one fluid evacuation device according to one of the preceding characteristics.

According to one configuration, the nacelle comprises first and second covers each having a lower longitudinal edge, the first and second covers being movable between an open position in which the lower longitudinal edges are spaced apart and a closed position in which the lower longitudinal edges are joined , the two lower longitudinal edges comprising cutouts delimiting the orifice when the first and second covers are in the closed position. In addition, the skirt comprises a first part secured to the first cowl and a second part secured to the second cowl.

The invention also relates to an aircraft comprising at least one fluid evacuation device according to one of the preceding characteristics.

Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with regard to the appended drawings, among which:

is a side view of an aircraft,

is a perspective view of a fluid evacuation device,

is a diagram of a fluid evacuation device which illustrates an embodiment of the prior art,

is a diagram of a fluid evacuation device which illustrates one embodiment of the invention,

is a longitudinal section of a fluid evacuation device which illustrates an embodiment of the invention,

is a perspective view of a fluid evacuation device which illustrates one embodiment of the invention, with a portion of a metal skirt removed,

is a top view of the fluid evacuation device visible in Figure 6, and

is an exploded perspective view of the fluid evacuation device visible in Figure 6.

In FIGS. 4 to 8, there is shown a fluid evacuation device 40 configured to be connected to a support 42 (visible in FIG. 4) of a thruster assembly and to pass through via an orifice 44 at least one wall 46 of a nacelle of the propulsion unit.

For the rest of the description, a longitudinal direction DL is parallel to the motor axis of the propulsion unit.

According to one configuration, the nacelle of the aircraft comprises two cowls 48, 50 each having a lower longitudinal edge 48.1, 50.1, the cowls being movable between an open position in which the lower longitudinal edges 48.1, 50.1 are spaced apart and a closed position, visible in Figures 6 to 8, in which the lower longitudinal edges 48.1, 50.1 are joined. The two lower longitudinal edges 48.1, 50.1 include cutouts delimiting the orifice 44 when the covers 48, 50 are in the closed position. According to this configuration, the fluid evacuation device 40 is positioned symmetrically with respect to a vertical median plane PMV of the propulsion unit which also corresponds to the junction plane of the cowls 48, 50.

Of course, the invention is not limited to this position for the fluid evacuation device. Thus, the latter can pass through any orifice 44 of at least one aerodynamic wall 46 of an aircraft separating an interior zone ZI and an exterior zone ZE. According to one embodiment, the wall 46 is made of composite material and includes a metallic coating for lightning.

According to one configuration, the support 42 is metallic, positioned in the interior zone ZI and spaced from the wall 46.

According to one embodiment, the fluid evacuation device 40 comprises a body 52, made of plastic or composite material, having a first part 54 positioned in the inner zone ZI and a second part 56 positioned in the outer zone ZE. The first part 54 is connected to the support 42 in operation. The second part 56 of the body 52 has aerodynamic shapes configured to limit drag. As a variant, the fluid evacuation device 40 comprises a cap, with aerodynamic shapes, capping the second part 56 and connected to the latter by any suitable connecting element.

The body 52 has a section adapted to that of the orifice 44 of the wall 46 to limit the play between the body 52 and the wall 46.

1. une embase 58, sous la forme d’une plaque, présentant une première face 58.1 orientée vers le support 42 et une deuxième face 58.2 opposée à la première face 58.1,
2. un tronc 60 relié à la deuxième face 58.2 de l’embase 58 qui présente une face périphérique 60.1 et une face terminale 60.2 opposée à l’embase 58.

According to one embodiment, the body 52 comprises:

1. a base 58, in the form of a plate, having a first face 58.1 oriented towards the support 42 and a second face 58.2 opposite the first face 58.1,
2. a trunk 60 connected to the second face 58.2 of the base 58 which has a peripheral face 60.1 and an end face 60.2 opposite the base 58.

The trunk 60 and the base 58 are made in one piece and form a single piece.

The body 52 is connected directly or indirectly to the support 42.

According to one embodiment, the body 52 comprises, in its first part 54, a recess 62 in the trunk 60, which crosses the base 58 and opens at the level of the first face 58.1 of the base 58. This recess 62 is substantially concentric with the peripheral face 60.1 and spaced from the latter by a small thickness.

This recess 62 comprises a side face 62.1 and a bottom 62.2 spaced from the wall 46 in operation, by a distance approximately equal to 20 mm.

The body 52 also includes at least one duct 64 configured to house a pipe and/or to channel a fluid. According to one configuration, the conduit 64 opens at a first end into the recess 62 and at a second end on the peripheral face 60.1 and/or the terminal face 60.2 of the trunk 60. Of course, the invention is not limited to this embodiment. Whatever the embodiment, the fluid evacuation device 40 comprises at least one duct channeling a fluid from the inner zone ZI to an exhaust hole positioned in the outer zone ZE.

According to one embodiment, the fluid evacuation device 40 comprises a metal plate 66 in the form of a plate which has a first surface 66.1 configured to be connected to the support 42 by connecting elements 68 and a second surface 66.2 opposite to the first surface 66.1, forming a bearing surface.

This metal plate 66 has a periphery 70 which delimits an area greater than that of the orifice 44 of the wall 46 so that in plan view, the orifice 44 is inscribed in the periphery 70 of the metal plate 66. configuration, the metal plate 66 has a rectangular perimeter with rounded corners. The base 58 of the body 52 has a circumference substantially identical to that of the metal plate 66. The body 52 is connected to the metal plate 66 by a connection by gluing, by welding or other or by means of connecting elements such as for example rivets, bolts, screws or the like.

According to one embodiment, the metal plate 66 comprises at least one tube 72, one for each conduit 64 of the body 52, projecting with respect to the second surface 66.2 opening out at the level of the first surface 66.1 and positioned in the extension of each conduit 64 in operation. The length of each tube 72 is determined so that each tube 72 is in contact with the bottom 62.2 of the recess 62 of the body 52 or very slightly spaced from the latter in operation.

According to another embodiment, the fluid evacuation device 40 does not include a metal plate. According to this embodiment, the support 42 is metallic and offers a support surface delimited by a circumference similar to the circumference 70. The support 42 can also comprise at least one tube, one for each conduit 64, identical to the tube 72, connected on the support surface.

Whatever the embodiment, the fluid evacuation device 40 comprises or is connected to a metal support surface 66.2, separated from the wall 46 by a sufficient distance to limit the risk of lightning strike.

The fluid evacuation device 40 comprises at least one metal skirt 74, surrounding the orifice 44, which extends from the wall 46 to the metal support surface 66.2.

According to one embodiment, the skirt 74 has a tubular shape and has a first end connected to the wall 46 by connecting elements 76 and a second end slightly spaced from the support surface 66.2, over its entire periphery 70. configuration, the skirt 74 has a rectangular section with rounded corners, greater than that of the periphery 70 of the support surface 66.2 so that there remains a small clearance, of the order of 3 to 5 mm, between the support surface 66.2 and the skirt 74 over the entire periphery 70 of the support surface 66.2. More generally, the skirt 74 has, in top view, a section corresponding to a homothety of the periphery 70 of the bearing surface 66.2

According to one embodiment, the skirt 74 has, at its first end, at least a first flange 78 pressed against the wall 46 and connected to the latter by the connecting elements 76 and, at its second end, to the least a second flange 80 spaced from the bearing surface 66.2.

According to one configuration, when the wall 46 comprises first and second covers 48, 50, the skirt 74 comprises two parts, a first part 74.1 secured to the first cover 48 and a second part 74.2 secured to the second cover 50.

Of course, the invention is not limited to this embodiment. Thus, the skirt 74 could be connected to the support 42 or to the metal plate 66 and be slightly spaced from the wall 46.

The metal skirt 74 and support surface 66.2 form an effective fire barrier.

To reinforce this fire barrier, the fluid evacuation device 40 comprises a metal insert 82, positioned in the body 52 which has a tubular wall 82.1, a bottom wall 82.2 at a first end of the tubular wall 82.1 as well as 'a flange 82.3 at a second end of the tubular wall 82.1. The tubular wall 82.1, the bottom wall 82.2 and the flange 82.3 are configured to be pressed in operation, respectively, against the side face 62.1, the bottom 62.2 of the recess 62 and the base 58. According to a configuration given as for example, the insert 82 has a thickness of the order of 0.4 mm. In operation, collar 82.3 of insert 82 is interposed between base 58 of body 52 and metal plate 66.

The insert 82 comprises at the level of the bottom wall 82.2 a through hole 84 in line with each duct 64 of the body 52. Of course, the invention is not limited to this embodiment for the insert 82 positioned in the body 52. According to a simplified embodiment, the insert 82 has a wall 82.2 remote from the wall 46 by a distance approximately greater than or equal to 20 mm, concentric with the orifice 44, having a surface slightly smaller than that of the orifice 44. Slightly lower means that in top view, the periphery of the wall 82.2 or the tubular wall 82.1 is separated from the orifice 44 by a distance of less than 10 mm.

The insert 82 is separated from the wall 46 by a distance limiting the risk of lightning strike, greater than or equal to 20 mm. However, the insert 82 is closer to the periphery of the orifice 44 than to the support surface 66.2 and reinforces the fire barrier formed by the fluid evacuation device 40.

According to another embodiment, the metal elements of the fluid evacuation device could be made of another material capable of forming a fire barrier.

The fluid evacuation device limits the risk of lightning strikes, the metal elements (or made of another material forming a fire barrier), such as the metal plate 66, the insert 82 or the skirt 74 being spaced the orifice 44 of the wall 46 by a distance greater than or equal to 20 mm. The metal skirt 74 and support surface 66.2 form a fire barrier which can be reinforced in the presence of a metal insert 82.

Thus, the invention makes it possible to obtain a fluid evacuation device which forms an effective fire barrier, while limiting the risks of damage by lightning.

Claims (10)

Fluid evacuation device for an aircraft, configured to be connected to a support (42) and to pass through, via an orifice (44), at least one wall (46) separating an interior zone (ZI) and an exterior zone (ZE), the fluid evacuation device comprising at least one body (52), made of composite material or plastic material, having first and second parts (54, 56) positioned respectively in operation in the inner and outer zones (ZI, ZE) , the first part (54) being connected directly or indirectly to the support (42), the fluid evacuation device comprising at least one conduit channeling a fluid from the interior zone (ZI) towards an exhaust hole positioned in the zone exterior (ZE), characterized in that the fluid evacuation device comprises, or is connected to in operation, a bearing surface (66.2) made of a material capable of forming a fire barrier, spaced from the wall ( 46), and in that the fluid evacuation device comprises at least one skirt (74) made of a material capable of forming a fire barrier, surrounding the orifice (44), which extends from the wall ( 46) up to the support surface (66.2). Aircraft fluid evacuation device according to claim 1, characterized in that each skirt (74) has a tubular shape and includes a first end configured to be connected to the wall (46) in operation and a second end slightly spaced from the bearing surface (66.2) in operation. Fluid evacuation device for aircraft according to claim 1 or 2, characterized in that the fluid evacuation device comprises a plate (66), made of a material capable of forming a fire barrier, having a first surface ( 66.1) configured to be connected to the support (42) and a second surface (66.2), opposite the first surface (66.1), forming the bearing surface. Aircraft fluid evacuation device according to one of the preceding claims, characterized in that the fluid evacuation device comprises an insert (82) positioned in the body (52), comprising a wall (82.2) remote from the wall (46) a distance of approximately 20 mm in operation, concentric with the orifice (44), having a surface slightly less than that of the orifice (44). Aircraft fluid evacuation device according to one of the preceding claims, characterized in that the body (52) comprises a base (58) having a first face (58.1) oriented towards the support (42) in operation and a second face (58.2) opposite the first face (58.1), a trunk (60) connected to the second face (58.2) of the base (58) having a peripheral face (60.1) and an end face (60.2) opposite the base (58), as well as a recess (62) in the trunk (60), opening at the level of the first face (58.1) of the base (58), having a lateral face (62.1) and a bottom ( 62.2) spaced from the wall (46) in operation. Aircraft fluid evacuation device according to claims 4 and 5, characterized in that the insert (82) comprises a tubular wall (82.1), a bottom wall (82.2) at a first end of the tubular wall (82.1 ) as well as a collar (82.3) at a second end of the tubular wall (82.1), the tubular wall (82.1), the bottom wall (82.2) and the collar (82.3) being pressed, respectively, against the side face (62.1), the bottom (62.2) of the recess (62) and the base (58) of the body (52). Aircraft fluid evacuation device according to claims 3 and 6, characterized in that the body (52) comprises at least one duct (64) configured to house a pipe and/or to channel a fluid emerging into the recess ( 62), in that the plate (66) comprises at least one tube (72) for each duct (64) of the body (52), projecting with respect to the second surface (66.2) opening out at the level of the first surface ( 66.1) and positioned in the extension of each duct (64) in operation and in that the insert (82) comprises a through hole (84) in line with each duct (64) of the body (52). Aircraft nacelle comprises at least one fluid evacuation device according to one of the preceding claims. Aircraft nacelle according to the preceding claim, said nacelle comprising first and second cowls (48, 50), each having a lower longitudinal edge (48.1, 50.1), the first and second cowls (48, 50) being movable between a position open in which the lower longitudinal edges (48.1, 50.1) are spaced apart and a closed position in which the lower longitudinal edges (48.1, 50.1) are joined, the two lower longitudinal edges (48.1, 50.1) comprising cutouts delimiting the orifice ( 44) when the first and second covers (48, 50) are in the closed position, characterized in that the skirt (74) comprises a first part (74.1) secured to the first cover (48) and a second part (74.2) secured to the second cover (50). Aircraft comprising at least one fluid evacuation device according to one of claims 1 to 7.