Engine accessories and aircraft

Abstract

An aircraft engine accessory (200) comprising a beam (152), a link (154), a wear piece (250a-b) and a fixing device (260), the beam (152) being fixed to a pylon and comprising a yoke (158) having two walls (158a-b), the link (154) having a hinged portion housed in the yoke (158), wherein the link (154) has a front side face (160a) and a rear side face (160b) facing the inner faces of the walls (158a-b), for each wall (158a-b), the wear piece (250a-b) is arranged between the wall (158a-b) and the corresponding side face (160a-b) of the link (154) against the inner face of the wall (158a-b), the fixing device (260) ensuring the fixing of the wear piece (250a-b) to the wall (158a-b). The wear piece thus prevents excessive tilting of the link and wear of the link or of the yoke.

Description

TECHNICAL FIELD

[0001] The present invention relates to an engine attachment for an aircraft engine, wherein the engine attachment comprises a yoke, a link and a wear piece between the yoke and the link, which forms a damper in the event of a convergence of the link and the yoke. The present invention also relates to an aircraft comprising an engine and such an engine attachment. BACKGROUND

[0002] Aircrafts generally comprise engines fixed under the wings. To this end, the aircraft comprises a pylon fixed under the wing and supporting the engine. The fixing between the engine and the pylon is carried out by means of an engine attachment. Generally, the engine attachment comprises a beam fixed to the pylon by means of bolts and at least one link having two articulated parts, one of which is articulated on the beam and the other of which is articulated on the engine. Generally, the engine attachment comprises a link having two articulated parts and a link having three articulated parts, two of which are articulated on the beam and the other of which is articulated on the engine.

[0003] The link having two articulated parts has one hole at each end, inside which a cage having a spherical inner surface is positioned, and each articulated part is in the form of a shaft which supports a spherical nut on which the spherical inner surface of the cage fits.

[0004] Thus, each articulated part constitutes a spherical joint and, in certain cases, the link having two articulated parts can pivot around its articulated parts to come into contact with the beam or the engine. Eventually, it can be the case that the beam, the engine or the link are damaged and must be replaced.

[0005] Thus, there is a need to find a device which prevents wear of the link and / or the beam and / or the engine. SUMMARY

[0006] One object of the present invention is to propose an engine attachment for an aircraft engine, wherein the engine attachment comprises a yoke, a link and a wear piece, which forms a damper in the event of a convergence of the link and the yoke or the engine.

[0007] To this end, an engine attachment is proposed, which is intended to be fixed between a pylon of an aircraft and an engine, the engine attachment comprising:

[0008] - a beam intended to be fixed to the pylon and comprising a yoke having two walls, each of which comprises an inner face oriented towards the inner face of the other wall;

[0009] - a link having two articulations, wherein a first articulation is provided at a first end of the link and is housed in the yoke to ensure the fixing of the link to the beam, and wherein a second articulation is provided at a second end of the link and is intended to ensure the fixing of the link to the engine, wherein the link has a front side and a rear side opposite the front side, wherein each side faces one of the inner faces of one of the walls;

[0010] - a wear piece, for each wall, provided against the inner face of the wall between the wall and the corresponding side of the link; and

[0011] - a fixing device ensuring the fixing of the wear piece to the wall, wherein the fixing device for a wear piece comprises a paddle and two bolts, the bolts fixing the paddle and the wear piece by clamping the wall between the paddle and the wear piece.

[0012] The wear piece thus prevents excessive tilting of the link and wear of the link or of the yoke.

[0013] According to a particular embodiment, the wear piece is in the form of a U whose arms extend outwards, and has curved portions facing the paddle in parallel, and the shank of each bolt passes through one of the curved portions and the paddle.

[0014] According to another particular embodiment, the wear piece is flat, and the paddle is in the form of a U whose arms extend inwards, and the face of the paddle faces the wear piece in parallel, and the shank of each bolt passes through one of the arms of the paddle and the wear piece.

[0015] Advantageously, the paddle has two flanges, and each flange bears against a side of a corresponding wall.

[0016] The invention also proposes an aircraft comprising a pylon, an engine and an engine accessory according to one of the preceding variants, wherein the beam is fixed to the pylon, and wherein the second articulation ensures the fixing of the link to the engine. BRIEF DESCRIPTION OF DRAWINGS

[0017] The above-mentioned and other features of the invention will become more apparent after reading the following description of exemplary embodiments, given in connection with the drawings, in which:

[0018] Figure 1 is a side view of an aircraft comprising an engine accessory according to the invention;

[0019] Figure 2is a perspective partial exploded view of an engine attachment according to the present invention;

[0020] Figure 3 is a view of an engine attachment according to the present invention, seen along the arrow III in Figure 2

[0021] Figure 4 is a perspective view of another engine attachment according to another embodiment of the present invention; and

[0022] Figure 5 is a view similar to Figure 3 of a variant embodiment of the present invention. DETAILED DESCRIPTION

[0023] Figure 1 An aircraft 100 is shown having a fuselage 102 to which wings 104 are fixed on both sides. At least one engine 108, such as a turbofan engine, is fixed under each wing 104. The engine 108 is fixed to the wing 104 by a pylon 106, and the fixing between the engine 108 and the pylon 106 is carried out by engine attachments, in particular by a front engine attachment and a rear engine attachment.

[0024] In the following description, by convention, X denotes the longitudinal direction of the jet engine, which is oriented univocally in the direction of advancement of the aircraft, i.e. in the longitudinal direction of the engine nacelle, Y denotes the transverse direction which is horizontal when the aircraft is on the ground, and Z denotes the vertical direction or vertical height when the aircraft is on the ground, the three directions X, Y and Z being orthogonal to each other.

[0025] The front engine attachment is fixed between the pylon 106 and the front part of the engine 108, and the rear engine attachment is fixed between the pylon 106 and the rear part of the engine 108.

[0026] Figure 2 and 3 An engine attachment 200 according to a first embodiment of the present invention is shown. The present invention is equally applicable to a front engine attachment or to a rear engine attachment.

[0027] The engine attachment 200 comprises a beam 152 which is fixed, for example by bolts, to the pylon 106.

[0028] The engine attachment 200 further comprises at least one link 154 having two articulations, with a first articulation provided at a first end 154a of the link 154 and a second articulation provided at a second end 154b of the link 154.

[0029] ​Typically, at each end 154a-b, the connecting rod 154 has a hole 156 in which a retainer with a spherical inner surface is positioned, and each hinge is in the form of a shaft 155 that supports a spherical nut 157, the spherical inner surface of which is positioned around the spherical nut.

[0030] The first hinge ensures that the connecting rod 154 is fixed to the beam 152, and the second hinge ensures that the connecting rod 154 is fixed to the engine 108.

[0031] The first hinge is housed in the yoke 158 of the beam 152, and the second hinge is housed in the yoke of the engine 108. Each yoke 158 has two walls, all of which are parallel. For each yoke 158, a connecting rod 154 is positioned between the walls of each yoke 158, and the axes of the two yokes 158 are parallel to each other, specifically parallel to the longitudinal direction X. Each wall of each yoke 158 has a hole coaxial with the holes 156 at the corresponding ends 154a-b of the connecting rod 154, thereby allowing the shaft 155 of the pivot to be positioned. The shaft 155 is secured by a fixing device 159, which is conventional to those skilled in the art and will not be described further.

[0032] Each yoke 158 has a front wall 158a facing forward and a rear wall facing backward relative to the front wall 158a, and each wall 158a-b has an inner surface oriented toward the inner surface of the other wall 158b-a and an outer surface oriented in the opposite direction to the inner surface.

[0033] Link 154 has a front side 160a and a rear side 160b opposite to the first side 160a and oriented rearward, and each side 160a-b faces the wall 158a-b of each yoke 158. More specifically, the front side 160a faces the inner surface of the front wall 158a, and the rear side 160b faces the inner surface of the rear wall 158b.

[0034] To prevent tilting forces from causing the connecting rod 154 to contact either the walls 158a-b of the yoke 158 of the beam 152 or the engine 108, the engine accessory 200 includes wear members 250a-b for each wall 158a-b of the yoke 158 of the beam 152. These wear members are fixed inside the yoke 158 against the wall 158a-b, specifically against the inner surface of the wall 158a-b, and between the wall 158a-b and the corresponding side surface 160a-b of the connecting rod 154. The wear members 250a-b prevent friction between the connecting rod 154 and the yoke 158 of the beam 152 and cause wear upon contact with the connecting rod 154. Furthermore, by restricting the rotation of the connecting rod 154, the wear members 250a-b prevent contact between the connecting rod 154 and the yoke of the engine 108.

[0035] Each wear part 250a-b is directly fixed to the wall 158a-b of the yoke 158 by the fixing device 260.

[0036] Figure 4 An engine accessory 400 according to a second embodiment of the present invention is shown. Elements identical to those in the first and second embodiments have the same reference numerals.

[0037] The difference between the first and second embodiments lies in the fixing devices 260 and 460 used to fix each wear part 250a-b, 450a-b to the associated wall 158a-b.

[0038] exist Figure 2 and Figure 3 In this embodiment of the invention, the fixing device 260 for fixing the wear parts 250a-b includes a paddle-type component 262 and two bolts 264a-b. The paddle-type component 262 is supported against the outer surface of the wall 158a-b, while the wear parts 250a-b are supported against the inner surface of the wall 158a-b. The bolts 264a-b fix the paddle-type component 262 and the wear parts 250a-b by clamping the wall 158a-b between the paddle-type component 262 and the wear parts 250a-b.

[0039] Bolts 264a-b are located on both sides of the bulkhead 158a-b, that is, on the port and starboard sides in this case.

[0040] Wearing parts 250a-b are U-shaped, with each arm of the U extending outwards, and the wearing parts have curved portions facing parallel to the paddle component 262. Therefore, the bolt shank of each bolt 264a-b passes through a curved portion and the paddle component 262.

[0041] To ensure proper positioning of the wear parts 250a-b, the paddle component 262 has a cylindrical notch 266 that is supported on the top of the ring 267 of the fixing device 159.

[0042] To restrict the rotation of the wear parts 250a-b about an axis parallel to the longitudinal direction X, the paddle-type component 262 has two flanges 268, and each flange 268 is supported against one side of the corresponding wall 158a-b. One side of the wall 158a-b is the surface connecting the side surface 160a-b.

[0043] In addition, in order to ensure good clamping of the wall 158a-b by the wear parts 250a-b and the paddle component 262, the dimensions of the wear parts 250a-b and the paddle component 262 are calculated such that when they are in place, there is a gap “J” between the bent portion and the paddle component 262 before the bolts 264a-b are tightened.

[0044] exist Figure 4In embodiments of the present invention, the fixation means 460 for fixing the wear part 450a-b comprises two bolts 464a-b which are directly fixed to the corresponding wall 158a-b, and wherein the bolt shaft of each bolt 464a-b passes through the wear part 450a-b and clamps it between the wall 158a-b and the bolt head of the bolt 464a-b.

[0045] In embodiments of the present invention presented herein, each wall 158a-b comprises two lugs 462 in each of which a hole is formed for the passage of a bolt 464a-b.

[0046] The bolts 464a-b are arranged on both sides of the wall 158a-b, that is to say, here, port and starboard.

[0047] Figure 5 A variant is shown in which the paddle part 262 is U-shaped, each arm of the U-shaped extends inwards, and the face of the U-shaped faces parallel to the flat wear part 250a-b. Thus, the bolt shaft of each bolt 264a-b passes through one arm of the paddle part 262 and the wear part 250a-b.

Claims

1. An engine accessory (200, 400) intended for attachment between a pylon (106) of the aircraft (100) and the engine (108), the engine accessory (200, 400) comprising: A beam (152) is intended to be fixed to a hanger (106) and includes a yoke (158) having two walls, each wall including an inner surface oriented toward the inner surface of the other wall; A connecting rod (154) having two hinges, wherein a first hinge is disposed at a first end (154a) of the connecting rod (154) and housed in the yoke (158) to ensure that the connecting rod (154) is fixed to the beam (152), and wherein a second hinge is disposed at a second end (154b) of the connecting rod (154) and is intended to ensure that the connecting rod (154) is fixed to the engine (108), wherein the connecting rod (154) has a front side and a rear side opposite to the front side, wherein each side faces an inner surface of one of the walls; Wearing member, for each wall, the wearing member abutting against the inner surface of the wall is disposed between the corresponding side surface of the wall and the connecting rod (154); and A fixing device (260, 460) ensures that the wear part is fixed to the wall, wherein the fixing device for fixing the wear part includes a paddle component (262) and two bolts, the bolts fixing the paddle component (262) and the wear part by clamping the wall between the paddle component (262) and the wear part.

2. The engine accessory according to claim 1, characterized in that, The wear member is U-shaped, wherein each arm extends outward, and the wear member has a curved portion facing the paddle component (262) parallel to it, and wherein the bolt shank of each bolt passes through one of the curved portions and the paddle component (262).

3. The engine accessory according to claim 1, characterized in that, The wear member is flat, wherein the paddle component (262) is U-shaped, wherein each arm extends inward and one face of the paddle component faces the wear member parallel to it, and wherein the bolt shank of each bolt passes through one of the arms of the paddle component (262) and the wear member.

4. The engine accessory according to claim 1, characterized in that, The paddle component (262) has two flanges (268), wherein each flange (268) supports one side of the corresponding wall.

5. An aircraft (100), comprising a pylon (106), an engine (108), and engine accessories (200, 400) according to claim 1, wherein, The beam (152) is fixed to the bracket (106), and the second hinge ensures that the connecting rod (154) is fixed to the engine (108).

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