Aircraft air inlet and aircraft comprising same

Abstract

The invention relates to an aircraft air inlet comprising:-a lip (44); an inner panel (48) comprising a front edge (48.1) connected to the lip (44); a front frame (50) comprising an outer edge (50.1) and an inner edge (50.2) connected to the lip (44) and / or the inner panel (48); a rear frame (52) comprising an outer edge connected directly or indirectly to the lip (44) and an inner edge (52.2) connected to the rear edge (48.2) of the inner panel (48); -at least one connecting piece (64) connecting the outer edges (50.1, 52.1) of the front frame (50) and the rear frame (52). In contrast to the prior art, the front frame (50) is not connected to the lip (44), such that the air inlet does not include any connection flush with the lip (44) in alignment with the front frame (50).

Description

Technical Field

[0001] The present application relates to an aircraft air inlet comprising an outer wall and front and rear frames connected by at least one distinct connection separated (arranged) relative to the outer wall, and also to an aircraft comprising at least one propulsion assembly including such an air inlet. Background Art

[0002] according to Figure 1 In the embodiment shown, the aircraft 10 comprises a plurality of propulsion assemblies 12 , each of which comprises a motor means (engine) 14 and a pod 16 surrounding the motor means 14 and allowing in particular to direct the air flow in the direction of the motor means 14 .

[0003] The motorized device 14 has a rotation (symmetry) axis A14. In the following description, the longitudinal direction is a direction parallel to the rotation axis A14. The longitudinal plane is a plane containing the rotation axis A14. Finally, the transverse plane is a plane perpendicular to the rotation axis A14. The concepts of front and rear refer to the flow direction of the air flow in the motorized device during operation (work), and the air flow flows from the front to the rear.

[0004] like Figure 2 As shown, each pod 16 comprises an air inlet 18 at the front, which is configured to separate a laminar air flow 20 into a laminar inner air flow 20 . 1 entering the pod 16 in the direction of the motor 14 and a laminar outer air flow 20 . 2 flowing to the outside of the pod 16 .

[0005] according to Figure 2 and Figure 3 In the embodiment shown, the air inlet 18 includes a lip 22, which has a C-shaped cross section in a longitudinal plane. The lip 22 includes: a leading edge 24.1 that divides the air flow 20 into an inner (layer) air flow 20.1 and an outer (layer) air flow 20.2; an outer portion 24.2 that extends from the leading edge 24.1 to the outer rear edge 22.1 of the lip 22 and on which the outer air flow 20.2 flows; and an inner portion 24.3 that extends from the leading edge 24.1 of the lip 22 to the inner rear edge 22.2 of the lip 22 and on which the inner air flow 20.1 flows.

[0006] The air inlet 18 also includes:

[0007] - an inner panel 26 positioned in extension of the inner portion 24.3 of the lip 22, having a front edge 26.1 connected to the inner rear edge 22.2 of the lip 22, and a rear edge 26.2;

[0008] - an annular front frame 28 having an outer periphery 28 . 1 connected to the outer portion 24 . 2 of the lip 22 and an inner periphery 28 . 2 connected to the inner portion 24 . 3 of the lip 22 and / or to the inner panel 26 ;

[0009] A rear frame 30 of annular shape having an outer periphery 30 . 1 connected to the outer rear edge 22 . 1 of the lip 22 and an inner periphery 30 . 2 connected to the rear edge 26 . 2 of the inner panel 26 .

[0010] The front frame 28 and the lip 22 define a D-shaped annular conduit 32 , referred to as a D-tube.

[0011] According to one embodiment, the front frame 28 and the rear frame 30 are positioned substantially in two transverse planes. As a variant, the front frame may be slightly (slightly) frustoconical and form an angle of about 10° with the transverse planes.

[0012] According to one configuration, the inner panel 26 is equipped with an acoustic attenuation structure.

[0013] like Figure 2 and Figure 3 As shown, according to one arrangement, the outer periphery 28.1 of the front frame 28 has a flange 34 which abuts against the outer portion 24.2 of the lip 22 and is connected to the lip by a series of connections 36 distributed over the entire circumference of the nacelle.

[0014] According to another embodiment, the outer rear edge of the lip 22 is connected to the front frame 28 by a first series of connections. Furthermore, the air intake comprises an outer panel positioned in the extension of the outer portion 24.2 of the lip 22, having a front edge connected to the front frame and a rear edge connected to the rear frame.

[0015] like Figure 2 and Figure 3 As shown, the fact that the lip and the outer panel are implemented in a single piece allows the absence of discontinuities at the surface in contact with the external air flow (the entire surface has continuity) and therefore limits aerodynamic disturbances. However, when the lip extends to the rear frame 30, its replacement requires the disassembly of a large number of connections, namely the connection connecting the lip 22, the inner panel 26 and the inner periphery 28.2 of the front frame 28, the connection connecting the lip 22 and the outer periphery 28.1 of the front frame 28, and (finally) the connection connecting the lip 22 and the rear frame 30.

[0016] According to another disadvantage, whatever the embodiment, the air inlet 18 comprises at least one series of connections positioned in alignment with the front frame 28 , these connections being flush with the wall of the air inlet (lip 22 and / or outer panel) in contact with the external air flow 20 . 2 .

[0017] During operation, the outer air flow 20.2 is laminar over a certain length starting from the leading edge 24.1 (also called the aerodynamic stop point), which should be as long as possible to reduce the drag generated by the air inlet 18 of the pod 16. In the absence of connecting parts (such as screws, rivets, etc.), the theoretical length characterized by the laminar air zone can reach about 400 to 950 mm depending on the size of the pod. Figure 2 and Figure 3 In the embodiment shown, the air intake 18 comprises connections 36 which are spaced apart from the leading edge 24 . 1 by a distance of less than 500 mm (a distance of approximately 300 mm), which create interferences (disturbances) which lead to an increase in the drag of the air intake 18 of the pod 16 and ultimately to an increase in the energy consumption of the aircraft 10 . Summary of the invention

[0018] The object of the present invention is to remedy all or part of the disadvantages of the prior art.

[0019] To this end, the present invention relates to an aircraft air inlet, comprising:

[0020] - a lip portion comprising a leading edge, an outer rear edge and an inner rear edge;

[0021] - an inner panel comprising a front edge connected to an inner rear edge of the lip and a rear edge;

[0022] - a front frame comprising a front outer periphery and a front inner periphery connected to the lip and / or the inner panel;

[0023] - A rear frame comprising a rear outer periphery connected directly or indirectly to the outer rear edge of the lip and a rear inner periphery connected to the rear edge of the inner panel.

[0024] According to the present invention, the air inlet includes at least one connecting member connecting the front and rear outer peripheries of the front frame and the rear frame.

[0025] Since the front frame is not connected to the lip, the air inlet does not have any connection aligned with the front frame and flush with the outside of the lip. Therefore, the air flow in contact with the air inlet maintains its laminar characteristics over as long a length as possible.

[0026] According to one embodiment, the air inlet comprises a single tubular connection substantially coaxial with the inner panel.

[0027] According to another embodiment, the air inlet comprises a plurality of connectors distributed around the inner panel and spaced apart from each other.

[0028] According to another feature, each connecting element has a front end, and the air intake comprises a front coupling system connecting the front end of each connecting element to the front outer periphery of the front frame.

[0029] According to another feature, the front periphery of the front frame is curved to be substantially cylindrical in shape. In addition, the front coupling system comprises at least one series of coupling elements distributed on at least one circle and passing through the front periphery of the front frame and the front end of each connector.

[0030] According to another feature, each connecting element has a rear end, and the air intake comprises a rear coupling system connecting the rear end of each connecting element and the rear outer periphery of the rear frame.

[0031] According to another feature, the rear end of each connector is bent and pressed against (pressed against) the rear periphery of the rear frame. In addition, the rear coupling system comprises at least one series of coupling elements, which are distributed on at least one circle, passing through the rear end of each connector and the rear periphery of the rear frame.

[0032] According to another feature, the lip and each connecting piece are connected by a coupling system located near the outer rear edge of the lip.

[0033] According to another feature, each connection element comprises a rib aligned with the coupling system and configured to space the lip from each connection element at a location or region outside the rib.

[0034] According to another feature, for each connector, the rib has: a generally cylindrical central portion which is spaced farther from the inner panel than the rest of the connector; and two frustoconical portions connecting the central portion to the rest of the connector.

[0035] The invention also relates to an aircraft comprising at least one propulsion assembly comprising an air inlet according to any of the preceding features. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Other features and advantages will become apparent from the following description of the invention, which is given by way of example and with reference to the following drawings, in which:

[0037] - Figure 1 This is a perspective view of the vehicle and propulsion assembly.

[0038] - Figure 2 is a longitudinal cross-sectional view of an air intake of an aircraft pod showing an embodiment of the prior art,

[0039] - Figure 3 yes Figure 2 A longitudinal section of the air inlet shown, with the lip in a disassembled state (unassembled state),

[0040] - Figure 4 is a longitudinal cross-sectional view showing an air inlet of an aircraft pod according to an embodiment of the present invention,

[0041] - Figure 5 is a longitudinal cross-sectional view of an air inlet of an aircraft pod showing an embodiment of the present invention, wherein the lip is in a disassembled state,

[0042] - Figure 6 yes Figure 5 A longitudinal section through the air inlet, with the lip in the installed state (assembled state),

[0043] - Figure 7 is a perspective view showing a portion of an air inlet without a lip according to an embodiment of the present invention, and

[0044] - Figure 8 1 is a perspective view showing a portion of an air intake port according to an embodiment of the present invention. DETAILED DESCRIPTION

[0045] According to one embodiment, the aircraft comprises at least one propulsion assembly including an air inlet 40 to direct an air flow 42 in a direction towards the motorized device.

[0046] Except for the air inlet 40, the other components of the propulsion assembly are not Figures 4 to 8 These elements are well known to those skilled in the art and may be the same as in the prior art. When the air inlet 40 is connected to a motorized device, the longitudinal axis of the air inlet 40 coincides with the axis of the motorized device.

[0047] The air inlet 40 comprises a lip 44 which has a C-shaped cross section in a longitudinal plane. The lip 44 comprises: a leading edge 46.1 which divides the air flow 42 into an inner (layer) air flow 42.1 and an outer (layer) air flow 42.2; an outer portion 46.2 which extends from the leading edge 46.1 to an outer rear edge 44.1 of the lip 44 and over which the outer air flow 42.2 flows; and an inner portion 46.3 which extends from the leading edge 46.1 to an inner rear edge 44.2 of the lip 44 and over which the inner air flow 42.1 flows.

[0048] The lip 44 has an outer face F44 in contact with the inner air flow 42.1 and the outer air flow 42.2, and an inner face F44'.

[0049] The air inlet 40 also includes:

[0050] an inner panel 48 positioned in the extension of the inner portion 46.3 of the lip 44, substantially coaxial with the longitudinal axis of the air inlet and having a front edge 48.1 and a rear edge 48.2, wherein the front edge 48.1 is connected to the inner rear edge 44.2 of the lip 44;

[0051] a front frame 50 of annular shape having a front outer periphery 50 . 1 and a front inner periphery 50 . 2 connected to the inner portion 46 . 3 of the lip 44 and / or to the inner panel 48 ;

[0052] A rear frame 52 of annular shape having a rear outer periphery 52 . 1 connected to the outer rear edge 44 . 1 of the lip 44 and a rear inner periphery 52 . 2 connected to the rear edge 48 . 2 of the inner panel 48 .

[0053] According to an embodiment, the front frame 50 and the rear frame 52 lie substantially in two transverse planes. As a variant, the front frame or the rear frame may be slightly (slightly) frustoconical and form an angle of about 10° with the transverse plane.

[0054] According to one configuration, the inner panel 48 is provided with an acoustic attenuation structure.

[0055] The air inlet 40 comprises a first coupling system 54 connecting the front edge 48.1 of the inner panel 48 and the inner rear edge 44.2 of the lip 44. According to one arrangement, the front edge 48.1 of the inner panel 48 abuts against the inner face F44' of the lip 44 at the inner rear edge 44.2 of the lip 44. Furthermore, the first coupling system 54 comprises a series of coupling elements 54.1 distributed on at least one circle around the longitudinal axis of the air inlet 40 and passing through the overlapping portions of the lip 44 and the inner panel 48.

[0056] according to Figure 4 In the embodiment visible in FIG. 4 , the first coupling system 54 allows connecting the front edge 48.1 of the inner panel 48, the inner rear edge 44.2 of the lip 44 and the front inner periphery 50.2 of the front frame 50. In this case, the front inner periphery 50.2 of the front frame 50 is of curved shape (with curved portions) and abuts against the front edge 48.1 of the inner panel 48. Furthermore, the first coupling system 54 comprises a series of coupling elements 54.1 distributed on at least one circle around the longitudinal axis of the air inlet 40 and passing through the overlapping portions in the lip 44, the inner panel 48 and the front frame 50.

[0057] according to Figure 6 In another embodiment, which can be seen in FIG. 4 , the air inlet 40 comprises, in addition to the first coupling system 54, a second coupling system 56 connecting the front inner periphery 50.2 of the front frame 50 and the inner panel 48. In this case, the front inner periphery 50.2 of the front frame 50 is of curved shape and abuts against the inner panel 48 in a region spaced apart from the front edge 48.1 of the inner panel 48. Furthermore, the second coupling system 56 comprises a series of coupling elements 56.1 distributed on at least one circle around the longitudinal axis of the air inlet 40, passing through the front inner periphery 50.2 of the front frame 50 and being housed (covered) in the inner panel 48.

[0058] Of course, the present invention is not limited to these embodiments. Therefore, the front inner peripheral edge 50 . 2 of the front frame 50 may be in a curved shape, pressed against the lip 44 , and connected to the lip 44 in a region spaced apart from the inner panel 48 .

[0059] The air inlet 40 further comprises a third connection system 58 connecting the rear inner periphery 52.2 of the rear frame 52 and the rear edge 48.2 of the inner panel 48. According to one arrangement, the rear inner periphery 52.2 of the rear frame 52 is curved, pressed against the rear edge 48.2 of the inner panel 48 (or pressed against an element connected to the inner panel 48) and connected to the inner panel. Furthermore, the third connection system 58 comprises a series of connection elements 58.1 distributed on at least one circle around the longitudinal axis of the air inlet 40, passing through the rear inner periphery 52.2 of the rear frame 52 and being accommodated (covered) in the inner panel 48.

[0060] According to an embodiment, the air intake 40 comprises a rear connection system 60 configured to connect the air intake 40 to a motorized device of the propulsion assembly, in particular a fan housing of the motorized device. According to an embodiment, the rear connection system 60 comprises at least one horn having a first wing 60.1 connected to the inner panel 48 and a second wing 60.2 located in a transverse plane and intended to be connected to the fan housing.

[0061] According to one construction, the rear inner periphery 52.2 of the rear frame 52 is curved and pressed against the first wing 60.1 of the rear connection system 60 which itself also presses against the inner panel 48, and the connecting element 58.1 passes through the rear inner periphery 52.2 of the rear frame 52, the first wing 60.1, and is accommodated in the inner panel 48.

[0062] Of course, the present invention is not limited to this embodiment of connecting the inner panel 48, the rear frame 52 and / or the rear connection system 60.

[0063] The air inlet 40 comprises a coupling system 62 which directly or indirectly connects the rear outer peripheral edge 52 . 1 of the rear frame 52 and the outer rear edge 44 . 1 of the lip 44 .

[0064] According to a feature of the present invention, the air inlet 40 includes a connection piece 64 connecting the front outer periphery 50 . 1 and the rear outer periphery 52 . 1 of the front frame 50 and the rear frame 52 .

[0065] According to one configuration, the air inlet 40 includes a tubular connector 64, substantially coaxial with the inner panel 48, which extends over the entire circumference of the air inlet 40. According to one arrangement, the connector 64 includes a plurality of parts connected to each other to form a single piece.

[0066] According to another configuration, the air intake 40 includes a plurality of connectors 64 distributed around the inner panel 48 and spaced apart from one another.

[0067] According to an embodiment, each connecting member 64 has a front end 64.1 connected to the front frame 50 and a rear end 64.2 connected to the rear frame 52. In addition, the air intake 40 further includes a front connection system 66 and a rear connection system 68, wherein the front connection system 66 connects the front end 64.1 of each connecting member 64 and the front outer periphery 50.1 of the front frame 50, and the rear connection system 68 connects the rear end 64.2 of each connecting member 64 and the rear outer periphery 52.1 of the rear frame 52.

[0068] According to one embodiment, the front outer periphery 50.1 of the front frame 50 is curved to have a substantially cylindrical shape, which is coaxial with and overlaps the front end 64.1 of the connecting member 64. In addition, the front connection system 66 also includes at least one series of connecting elements 66.1, which are distributed on at least one circle around the longitudinal axis of the air inlet 40 and pass through the front outer periphery 50.1 of the front frame 50 and the front end 64.1 of each connecting member 64. Of course, the present invention is not limited to this embodiment of such a connection (mode) between the front frame 50 and each connecting member 64.

[0069] According to one embodiment, the rear end 64.2 of each connecting member 64 is bent (is curved) and abuts against the rear outer periphery 52.1 of the rear frame 52. In addition, the rear connection system 68 includes at least one series of connection elements 68.1, which are distributed on at least one circle around the longitudinal axis of the air inlet 40 and pass through the rear end 64.2 of each connecting member 64 and the rear outer periphery 52.1 of the rear frame 52. Of course, the present invention is not limited to this embodiment of such a connection (mode) between the rear frame 52 and each connecting member 64.

[0070] According to one embodiment, the lip 44 is connected to each (individual) connecting member 64 by a connecting system 70, which is located near the rear outer edge 44.1 of the lip 44 (i.e. close to the rear outer edge 44.1), and includes at least one series of connecting elements 70.1, which are distributed on at least one circle around the longitudinal axis of the air inlet 40 and pass through the lip 44 and each connecting member 64.

[0071] The connector 64 is positioned between the lip 44 and the inner panel 48. Each connector 64 has a rib 72 in alignment with the coupling system 70, which is configured to separate the lip 44 and each connector 64 at (all areas or positions) outside the rib 72. One or more ribs 72 are positioned in a transverse plane. According to one configuration, for each connector 64, the rib 72 has an Ω-shaped ("omega"-shaped) cross-section in the plane through which the longitudinal axis of the air inlet 40 passes. Thus, the rib 72 has: a generally cylindrical central portion 72.1, which is spaced farther from the inner panel 48 than the rest of the connector 64; and two truncated cone portions 72.2, 72.3, which connect the central portion 72.1 to the rest of the connector 64. Of course, the present invention is not limited to this Ω-shaped shape of the rib 72. Since the connection element 64 is spaced apart from the lip 44 outside the rib 72 , this rib is configured to be able to press at least one area of ​​the connection element 64 against the inner face F44 ′ of the lip 44 to connect the at least one area to the lip by the coupling system 70 .

[0072] Of course, the invention is not limited to this embodiment of the connection between the connecting lip 44 and one or more connecting members 64 .

[0073] According to an embodiment, the different coupling elements (connectors) 54.1, 56.1, 58.1, 66.1, 68.1, 70.1 may be screws, bolts or rivets.

[0074] According to the invention, the front outer periphery 50.1 of the front frame 50 is spaced apart from and not connected to the lip 44. Therefore, the air inlet does not have any connection elements in alignment with the front frame 50, these connection elements being flush with the outer face F44 of the lip 44 where it comes into contact with the external air flow 42.2. In this way, the external air flow maintains its laminar characteristics over as long a length as possible.

[0075] according to Figure 4 and 6 Another advantage represented is that the lip 44 is connected to the rest of the air inlet by only two coupling systems, which allows reducing the number of connections to be removed or reinstalled when removing or reinstalling the lip 44 .

[0076] Furthermore, the frame 52 can remain in place after the components are disassembled, thus ensuring the overall stability of the geometry of the air inlet.

[0077] Ultimately, the inner panel 48 , the front and rear frames 50 , 52 , and the one or more connectors 64 form a rigid box structure that reinforces the air intake 40 , which may provide better stress absorption in the event of a bird strike.

Claims

1. An aircraft air inlet, comprising: - a lip (44) comprising a leading edge (46.1), an outer rear edge (44.1) and an inner rear edge (44.2); - an inner panel (48) comprising a front edge (48.1) connected to the inner rear edge (44.2) of the lip (44) and a rear edge (48.2); - a front frame (50) comprising a front outer periphery (50.1) and a front inner periphery (50.2) connected to the lip (44) and / or the inner panel (48); - a rear frame (52) comprising a rear outer peripheral edge (52.1) connected directly or indirectly to the outer rear edge (44.1) of the lip (44) and a rear inner peripheral edge (52.2) connected to the rear edge (48.2) of the inner panel (48), It is characterized in that the air inlet (40) further comprises at least one connecting member (64) connecting the front outer periphery (50.1) of the front frame (50) and the rear outer periphery (52.1) of the rear frame (52).

2. The aircraft air inlet according to claim 1, characterized in that: The air inlet (40) includes a single tubular connector (64) substantially coaxial with the inner panel (48).

3. The aircraft air inlet according to claim 1, characterized in that: The air inlet (40) includes a plurality of connectors (64) distributed around the inner panel (48) and spaced apart from each other.

4. Aircraft air inlet according to any one of the preceding claims, characterised in that Each connecting member (64) has a front end (64.1), and the air intake (40) includes a front connection system (66) connecting the front end (64.1) of each connecting member (64) and the front outer periphery (50.1) of the front frame (50).

5. The aircraft air inlet according to claim 4, characterized in that: The front outer periphery (50.1) of the front frame (50) has a curved portion and is substantially cylindrical in shape, and wherein the front connection system (66) comprises at least one series of connection elements (66.1) distributed on at least one circle, the connection elements (66.1) passing through the front outer periphery (50.1) of the front frame (50) and the front end (64.1) of each connecting member (64).

6. Aircraft air inlet according to any one of the preceding claims, characterised in that Each connecting member (64) has a rear end (64.2), and wherein the air intake (40) includes a rear connection system (68) connecting the rear end (64.2) of each connecting member (64) and the rear outer periphery (52.1) of the rear frame (52).

7. The aircraft air inlet according to claim 6, characterized in that: The rear end (64.2) of each connecting member (64) is bent and abuts against the rear outer periphery (52.1) of the rear frame (52), and wherein the rear connection system (68) comprises at least one series of connection elements (68.1) distributed on at least one circle, the connection elements (68.1) passing through the rear end (64.2) of each connecting member (64) and the rear outer periphery (52.1) of the rear frame (52).

8. An aircraft air inlet according to any one of the preceding claims, characterised in that The lip (44) and each connecting piece (64) are connected by a coupling system (70) located near the outer rear edge (44.1) of the lip (44).

9. The aircraft air inlet according to claim 8, characterized in that: Each connector (64) has a rib (72) aligned with the coupling system (70) and configured to space the lip (44) and each connector (64) apart beyond the rib (72).

10. The aircraft air inlet according to claim 9, characterized in that: For each connecting member (64), the rib (72) has: a substantially cylindrical central portion (72.1) which is spaced further apart from the inner panel (48) than the remainder of the connector (64); as well as Two truncated cone-shaped portions (72.2, 72.3) connecting the central portion (72.1) to the rest of the connecting piece (64).

11. An aircraft comprising at least one propulsion assembly comprising an air inlet according to any one of the preceding claims.

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