FR3096353A1 - FRONT ENGINE ATTACHMENT SYSTEM FOR AN AIRCRAFT ENGINE CONTAINING A BEAM MADE IN TWO PARTS - Google Patents

Abstract

FRONT ENGINE MOUNTING SYSTEM FOR AN AIRCRAFT ENGINE COMPRISING A BEAM MADE IN TWO PARTS The invention relates to a front engine mounting system (150) for an engine (102) of an aircraft (100), the system for front engine attachment (150) comprising an engine pylon (152) comprising at its front part a front part (153) having an attachment wall (158) which has a front face, and a front engine attachment (154) comprising a beam (302) fixed against the front face and to which is fixed on either side of a median plane, a connecting rod (304a-b), where each connecting rod (304a-b) is fixed in an articulated manner by at least one first connection point (306a-b, 310) to the beam (302) and is intended to be fixed in an articulated manner by at least one second connection point (308, 312) to the motor (102). The beam (302) consists of a front plate (302a) and a rear plate (302b) removably fixed to each other, where the rear plate (302b) is pressed against the front face and wherein the front plate (302a) is disposed forward of the back plate (302b). Such a front engine attachment system thus comprises a beam in two parts. Each of these two parts can thus come from a part that is less heavy and easier to make. Fig. 3

Description

Description Title of the invention: FRONT ENGINE MOUNTING SYSTEM FOR AN AIRCRAFT ENGINE COMPRISING A BEAM MADE IN TWO PARTS Technical Field 100011 The present invention relates to a front engine mounting system for an aircraft engine, as well as a an aircraft comprising at least one such forward engine attachment.

Prior technique

[0002] An aircraft conventionally comprises at least one engine, in particular a turbojet.

Under each wing and for each engine, the aircraft comprises an engine pylon which is fixed to the structure of the wing and which extends below the wing and the engine is suspended under the engine pylon.

[0003] The engine is fixed to the engine mast by means of an engine attachment system comprising a front engine attachment and a rear engine attachment.

[0004] The front engine attachment comprises, for example, a beam fixed to a front face of the engine mast and two connecting rods fixed between the beam and a front casing of the engine.

[0005] Each connecting rod and the beam define in combination a primary force path between the engine and the engine mast to support the engine loads under normal operating conditions of said engine.

Each connecting rod is equipped with ball joints which are made up of two cut and matched balls.

Such a beam is a solid part obtained by machining a part obtained by forging.

The process for obtaining this beam is relatively long and complex.

If such a beam is satisfactory from the point of view of its use, it is necessary to find a different architecture to facilitate its manufacture and its implementation.

Disclosure of Invention

An object of the present invention is to provide a front engine attachment system whose beam is in two parts to be easier to achieve.

[0009] For this purpose, a front engine attachment system is proposed for an aircraft engine, the front engine attachment system comprising:

[0010] - a reactor mast comprising at its front part a front part having an attachment wall which has a front face, and

[0011] - a front engine attachment comprising a beam fixed against the front face and to which is fixed on either side of a median plane, a connecting rod, where each connecting rod is fixed in an articulated manner by at least a first point to the beam and is intended to be fixed in an articulated manner by at least a second point of connection to the engine, the front engine attachment system being characterized in that the beam consists of a front plate and 'a rear plate detachably fixed to each other, where the rear plate is pressed against the front face and where the front plate is arranged at the front with respect to the rear plate.

[0013] Such a front engine attachment system thus comprises a beam in two parts.

Each of these two parts can thus come from a part that is less heavy and easier to produce.

[0014] Advantageously, each first connection point between the beam and a connecting rod takes the form of a yoke made in the beam, one wall of said yoke consists of an extension of the front plate, and the other wall of said yoke consists of an extension of the rear plate.

[0015] Advantageously, the front engine attachment system comprises, for each connecting rod, a standby safety attachment point activated in the event of failure of a primary force path and which creates an auxiliary force path between the engine and the engine pylon, each stand-by safety attachment point consists of a yoke made in the engine and a pin fitted into bores of said yoke and which passes through a bore of the beam whose diameter is greater than the diameter of the axis, and the bore of the beam consists of a first bore in the front plate and a second bore in the rear plate coaxial with the first bore.

[0016] Advantageously, the fixing of the two plates is effected by bolts each comprising a head and a nut, and each plate comprises a recess to accommodate the head or the nut therein.

[0017] The invention also proposes an aircraft comprising a structure, an engine and a front engine attachment system according to one of the preceding variants, where the engine pylon is fixed to the structure, and where a front part of the engine is fixed to said at least one second connection point.

Brief Description of the Drawings [00181] The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, including:

[0019] [fig.1] is a side view of an aircraft according to the invention,

[0020] [fig.2] is a perspective view of a front engine attachment system according to the invention, and

[0021] [fig.3] is an exploded perspective view of the front engine attachment system of FIG. 2.

[0022] DETAILED DESCRIPTION OF EMBODIMENTS

[0023] In the following description, the terms relating to a position are taken with reference to an aircraft in the forward position, that is to say as it is represented in FIG. 1.

[0024] FIG. 1 shows an aircraft 100 which has an engine 102, in particular a turbojet.

[0025] In the following description, and by convention, we call X the longitudinal direction of the engine 102 oriented positively in the direction of advancement of the aircraft 100, we call Y the transverse direction of the engine 102 which is horizontal. when the aircraft is on the ground, and Z the vertical direction or vertical height when the aircraft is on the ground, these three X directions.

Y and Z being orthogonal to each other.

In the embodiment of the invention presented in FIG. 1, the aircraft 100 comprises an engine 102 under each wing 103, but it is possible to provide several engines under each wing 103.

[0027] Under each wing 103 and for each engine 102, the aircraft 100 has a front engine attachment system 150 which is fixed to the structure of the wing 103 and extends under the wing 103 and supports the part front of engine 102.

As shown in Figs. 2 and 3, the forward engine mounting system 150 comprises an engine pylon 152 fixed to the wing 103 and a forward engine mounting 154 fixed to the engine pylon 152 and to which the front part of the engine 102 is fixed.

In known manner, the engine mast 152 takes for example the form of a box which comprises among other things at its front part, a front part 153 which extends in a substantially vertical plane.

The front engine mount 154 comprises a beam 302 to which is fixed on either side of a median plane XZ, a connecting rod 304a-b.

[0031] Each connecting rod 304a-b is fixed in an articulated manner by at least one first connection point 306a-b, 310 to the beam 302 and is fixed in an articulated manner by at least one second connection point 308, 312 to a part front of the engine 102 which is represented here by a part of its front casing.

In the embodiment of the invention presented here, the front part 153 has an attachment wall 158 which has a front face facing the front of the aircraft 100.

The beam 302 is fixed against the front face of the attachment wall 158, here using bolts 602 which pass through a bore of the beam 302 and a bore of the attachment wall 158.

[0034] The front engine attachment system 150 here also comprises shear pins 604 which pass through a bore in the beam 302 and a bore in the attachment wall 158.

In the embodiment of the invention presented here, the first connecting rod 304a is fixed by two first connecting points 306a-b to the beam 302 and by a second connecting point 308 to the motor 102, and the second connecting rod 304b is fixed by a first connection point 310 to the beam 302 and by a second connection point 312 to the motor 102.

For each connecting rod 304a-b, each point of connection to the beam 302 and to the motor 102 is constituted by a yoke made, respectively in the beam 302 and the motor 102, by a bore passing through the connecting rod 304a-b and by a pin which passes through bores in the yoke and fits into the bore of the connecting rod, where the connecting rod is mounted on the pin via a ball joint.

[0037] Each connecting rod 304a-b, the beam 302, and the front part 153 define in combination a primary path of forces between the engine 102 and the engine pylon 152 to support the loads of the engine 102 under normal operating conditions. operation of said motor 102.

[0038] For better security, the front engine attachment 154, and more particularly the beam 302, comprises, for each connecting rod 304a-b, an additional connection point 314a-b.

The additional connection points 314a-b are arranged on either side of the median plane XZ, and each provides an additional connection between the beam 302 and the motor 102.

Each additional connection point 314a-b takes the form of a pending safety attachment point (called "waiting fail-safc" in English language) which will compensate for a failure of the primary path of efforts, that is- that is to say at least one of the connecting rods 304a-b.

That is to say, when a component of the primary stress path is damaged, the activation of a standby safety attachment point creates an auxiliary stress path between the engine 102 and the engine pylon 152 .

[0039] Each pending safety attachment point 314a-b here consists of a clevis made in the motor 102 and of a shaft fitted into bores of said clevis and which passes through a bore of the beam 302 whose diameter is greater than the diameter of the axis.

Thus, in normal operation, there is no contact between the axis and the beam 302, and in the event of breakage of one of the connecting rods 304a-b, the motor 102 will move and the axis then comes into contact. contact with beam 302.

According to the invention, the beam 302 consists of a front plate 302a and a rear plate 302b.

The front plate 302a is arranged at the front with respect to the rear plate 302b and the rear plate 302b is pressed against the front face of the attachment wall 158.

The front plate 302a and the rear plate 302b each extend in a plane parallel to the front face of the attachment wall 158 and are removably fixed to each other, for example by a series of bolts.

To this end, each plate 302a-b has a series of bores 320a-b coaxial and oriented here generally parallel to the longitudinal direction X.

[0042] The production of the beam 302 in two plates 302a-b facilitates the production of said beam 302 because the two plates 302a-b are actually easier to produce, in particular because their thickness is less. than the state-of-the-art beam.

[0043] As shown in FIG. 2, each connecting rod 304a-b is sandwiched between plates 302a-b.

That is to say, for each connecting rod 304a-b, each plate 302a-b has an extension which comes against a face of the connecting rod 304a-b.

Thus, for each yoke made in the beam 302, one wall of said yoke is made up of an extension of the front plate 302a, and the other wall of said yoke is made up of an extension of the rear plate 302b .

[0045] For each standby safety fixing point 314a-b, the bore of the beam 302 consists of a first bore in the front plate 302a and a second bore in the rear plate 302b coaxial with the first bore.

In the context of fixing the two plates 302a-b by bolts each comprising a head and a nut, each plate 302a-b comprises a recess 322a-b to accommodate the head or the nut therein without these the latter protrude outside the beam 302.

Thus, the front plate 302a has a recess 322a at its face facing forward and the rear plate 302b has a recess 322b at its face facing rear.

For each of the yokes described above, the axis of the yoke is generally parallel to the longitudinal direction X.

6 [Claim 1] [Claim 2] [Claim 3] [Claim 4]

Claims (1)

CLAIMS Front engine mounting system (150) for an engine (102) of an aircraft (100), the front engine mounting system (150) comprising: - an engine pylon (152) comprising at its front part a front part (153) having an attachment wall (158) which has a front face, and - a front engine attachment (154) comprising a beam (302) fixed against the front face and to which is fixed on both sides other from a median plane, a connecting rod (304a-b), where each connecting rod (304a-h) is fixed in an articulated manner by at least a first connection point (306a-b, 310) to the beam (302) and is intended to be attached in an articulated manner by at least one second connection point (308, 312) to the engine (102), the front engine attachment system (150) being characterized in that the beam (302) consists of a front plate (302a) and a back plate (302b) removably attached to each other, where the back plate (302b) is pressed against the front face and where the front plate (302a) is disposed forward relative to the rear plate (302b). Front engine attachment system (150) according to Claim 1, characterized in that each first connection point (306a-b, 310) between the beam (302) and a connecting rod (304a-b) takes the form of a yoke made in the beam (302), in that one wall of said yoke is made up of an extension of the front plate (302a), and in that the other wall of said yoke is made up of an extension of the ifrier plate (302b). Front engine attachment system (150) according to one of the preceding claims, characterized in that it comprises for each connecting rod (304a-b), a stand-by safety attachment point (314a-b) activated in the event of engine failure. 'a primary force path and which creates an auxiliary force path between the engine (102) and the engine pylon (152), in that each stand-by safety attachment point (314a-b) consists of a clevis made in the engine (102) and a pin fitted in bores of said clevis and. which passes through a bore in the beam (302) the diameter of which is greater than the diameter of the pin, and in that the bore in the beam (302) consists of a first bore in the front plate (302a) and a second bore in the back plate (302b) coaxial with the first bore. Front engine mounting system (150) according to one of the preceding claims 7 [Claim 5], characterized in that the fixing of the two plates (302a-b) is effected by bolts each comprising a head and a nut, and cc that each plate (302a-b) has a recess (322a-b) to house the head or the nut therein. Aircraft (100) comprising a structure, an engine (102) and a front engine attachment system (150) according to one of the preceding claims, in which the engine block (152) is fixed to the structure, and in which a front part of the engine (102) is fixed to said at least one second connection point (308, 312).