• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an engine attachment (154) for a motor (102) comprising a beam (302) intended to be fixed to a reactor mast and to which a connecting rod is fixed on either side of a median plane. (304a-b), wherein each link (304a-b) is hingedly attached at one end to the beam (302) and is adapted to be hingedly attached by the other end thereof to the motor (102). ), wherein each link (304a-b) and the beam (302) together define a primary path of effort between the motor (102) and the reactor mast to support the engine loads. The engine attachment (154) is characterized in that it also comprises for each connecting rod (304a-b), a standby security fixing point (314a-b) activated in the event of failure of the primary effort path and which creates an auxiliary path of forces between the engine and the engine mast, and in that the two standby security fixing points (314a-b) are arranged on either side of the median plane (XZ). Such an engine attachment thus allows a lateral offset of the security attachment points pending, thus facilitating their access by a technician.
    公开号:FR3073205A1
    申请号:FR1760469
    申请日:2017-11-08
    公开日:2019-05-10
    发明作者:Stephane Combes；Jean GELIOT；Thomas Deforet；Adeline Soulie；Benoit ORTEU
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    The present invention relates to an engine attachment of an aircraft engine, an engine attachment system using such an engine attachment, and an aircraft comprising at least one such engine attachment or such an engine attachment system.
    STATE OF THE PRIOR ART
    An aircraft conventionally comprises at least one engine, in particular a turbojet. Under each wing and for each engine, the aircraft has a jet engine mast which is attached to the wing structure and which extends below the wing and the engine is suspended under the jet engine mast.
    The engine is attached to the engine mast via an engine attachment system that includes a front engine attachment and a rear engine attachment.
    The front engine attachment conventionally comprises a beam fixed under the engine mast and two connecting rods fixed between the beam and a front part of the engine.
    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.
    In the event of failure of one of the connecting rods, there is a pending safety fixing point (known as "waiting fail-safe") which will compensate for a failure of a primary effort path. That is to say, when a component of a primary force path is damaged, activation of the standby safety attachment point creates an auxiliary force path between the engine and the engine mast.
    This pending safety attachment point is located at the mid-plane and is generally difficult to access during maintenance operations.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide an engine attachment which allows offset from the pending safety attachment point to facilitate access and reduce the forces introduced into the engine.
    To this end, an engine attachment is proposed for an engine of an aircraft which comprises a reactor mast, the engine attachment comprising a beam intended to be fixed to the engine mast 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 one of its ends to the beam and is intended to be fixed in an articulated manner by the other of its ends to the engine, where 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, the engine attachment being characterized in that it also includes, for each connecting rod, a standby safety fixing point activated in the event of failure of the primary force path and which creates an auxiliary force path between the engine and the engine mast, and in that the two standby safety fixing points are arranged s on either side of the midplane.
    Such a motor attachment thus allows lateral offset of the pending safety attachment points, thus facilitating their access by a technician.
    Advantageously, each standby safety attachment point consists of a yoke produced in the engine and an axis fitted into said yoke and which passes through a bore in the beam whose diameter is greater than the diameter of the axis.
    The invention also provides an engine attachment system for an engine of an aircraft, the engine attachment system comprising:
    a reactor mast comprising an upper wall, a lower wall and on each side a side wall, which together delimit a front face at the level of the front part of the reactor mast, and
    - an intermediate piece which takes the form of a bowl with a bottom wall and four side walls which extend around the bottom wall, and
    - a motor attachment according to one of the preceding variants, where the beam is fixed against an external face of the bottom wall, where the intermediate piece fits at the level of the front face of the engine mast so that a inner face of the bottom wall comes against the front face of the reactor mast, where a side wall of the intermediate piece comes to bear against a side wall of the reactor mast, where another side wall of the intermediate piece comes to bear against the another side wall of the reactor mast, where another side wall of the intermediate piece comes to bear against the upper wall of the reactor mast, where another side wall of the intermediate piece comes to bear against the bottom wall of the reactor mast, and where each side wall of the intermediate piece and the associated wall of the engine mast are fixed to each other.
    According to a particular embodiment, each side wall of the reactor mast takes the form of a U open towards the inside of the reactor mast and has a bottom which constitutes the side wall, a first flap which extends parallel to the upper wall. and a second flap which extends parallel to the bottom wall, each side wall of the engine mast is positioned between the side walls of the intermediate piece, and the top wall and the bottom wall are pressed against the outside of the side walls of the intermediate piece.
    According to another particular embodiment, each side wall of the reactor mast takes the form of a U open towards the inside of the reactor mast and has a bottom which constitutes the side wall, a first flap which extends parallel to the wall upper and a second flap which extends parallel to the lower wall, each side wall of the engine mast is positioned outside the side walls of the intermediate piece, the upper wall is pressed outside against the side wall of the intermediate piece and the first flap, and the bottom wall is pressed outside against the second flap.
    The invention also provides an aircraft comprising a structure, an engine and an engine attachment system according to one of the preceding variants, where the engine mast is fixed to the structure, and where a front part of the engine is fixed to said other ends. connecting rods.
    The invention also proposes an aircraft comprising a structure, an engine, a reactor mast fixed to the structure and an engine attachment according to one of the preceding variants, where the beam is fixed to the reactor mast and where a front part of the engine is fixed. at said other ends of the connecting rods.
    BRIEF DESCRIPTION OF THE DRAWINGS
    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 accompanying drawings, among which:
    Fig. 1 is a side view of an aircraft according to the invention, FIG. 2 is an exploded perspective view of a reactor pylon according to an embodiment of the invention.
    Fig. 3 is a perspective view of an engine attachment system according to the invention, said system comprising an engine mast and a front engine attachment fixed to the engine mast via an intermediate part, FIG. 4 is a front view of the front engine mount as shown in FIG. 3, according to an embodiment of the invention, FIG. 5 is a perspective view of a front engine attachment and of an intermediate part according to an embodiment of the invention, FIG. 6 is a rear view in section of the intermediate piece according to a first embodiment of the invention, and FIG. 7 is a rear view in section of the intermediate piece according to a second embodiment of the invention.
    DETAILED DESCRIPTION OF EMBODIMENTS
    In the following description, the terms relating to a position are taken with reference to an aircraft in the advancing position, that is to say as shown in FIG. 1.
    Fig. 1 shows an aircraft 100 which has an engine 102, in particular a turbojet.
    In the description which follows, and by convention, X is called the longitudinal axis of the engine 102 oriented positively in the direction of advance of the aircraft 100, Y is called 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 directions X, Y and Z being orthogonal to one another.
    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.
    Under each wing 103 and for each engine 102, the aircraft 100 has an engine attachment system 150 which is fixed to the structure of the wing 103 and extends under the wing 103 and supports the front part of the engine 102 .
    With reference to Figs. 2, 3 and 4, the engine attachment system 150 comprises a reactor mast 152 fixed to the wing 103 and a front engine attachment 154 attached to the engine mast 152 and to which the front part of the engine 102 is fixed, and an attachment rear engine 153 (not described since it is not part of the invention) fixed to the engine mast 152 and to which is fixed an intermediate or rear part of the engine 102.
    In known manner, the reactor mast 152 takes the form of a box which has an upper wall 202, a lower wall 204 and on each side, a side wall 206a-b. These different walls 202, 204 and 206a-b are fixed to each other to form the reactor mast 152.
    The reactor mast 152 has at its front part, a front face which is delimited by the different walls 202, 204 and 206a-b of the reactor mast 152 and which extends in a substantially vertical plane.
    With reference to Figs. 3 and 4, the front engine attachment 154 comprises a beam 302 to which is fixed on either side of a median plane XZ, a connecting rod 304a-b.
    Each connecting rod 304a-b is hingedly attached by one of its ends to the beam 302 and is hingedly attached by the other of its ends to a front part of the engine 102.
    According to the invention, the engine attachment system 150 also comprises an intermediate part 156 which takes the form of a bowl with a bottom wall 158 and four side walls 160a-d which extend around the bottom wall 158 .
    With reference to FIG. 3, the beam 302 is fixed against an outer face of the bottom wall 158, here using bolts 602. The outer face of the bottom wall 158 is the face which is oriented towards the front of the aircraft 100.
    The intermediate piece 156 fits at the front face of the reactor mast 152 so that an inner face of the bottom wall 158 comes against the front face of the reactor mast 152, that a side wall 160a of the intermediate piece 156 comes to bear against a side wall 206a of the reactor mast 152, that another side wall 160b of the intermediate piece 156 comes to bear against the other side wall 206b of the reactor mast 152, that another side wall 160c of the intermediate piece 156 comes to bear against the upper wall 202 of the reactor mast 152, and that another side wall 160d of the intermediate piece 156 comes to bear against the bottom wall 204 of the reactor mast 152.
    The inside face of the bottom wall 158 is the face opposite the outside face, that is to say the face which is oriented towards the rear of the aircraft 100.
    Each side wall 160a-d of the intermediate piece 156 is parallel to the wall 202, 204, 206a-b associated with the reactor mast 152.
    Each side wall 160a-d of the intermediate piece 156 and of the associated wall 202, 204, 206a-b of the engine mast 152 are fixed to each other, here using bolts 604.
    Such an arrangement makes it possible to arrange the beam 302 at the level of the front part of the reactor mast 152, thereby saving space compared to a position under the reactor mast 152. In addition, the particular shape of the intermediate piece 156 makes it possible to guarantee good rigidity of the front part of the reactor mast 152 and good transmission of the forces from the beam 302 to the reactor mast 152.
    Fig. 6 shows a first particular assembly of the intermediate part 156 on the reactor mast 152 and FIG. 7 shows a second particular assembly of the intermediate part 156 on the reactor mast 152.
    In the first and second assemblies, each side wall 206a-b of the reactor mast 152 takes the form of a U open towards the inside of the reactor mast 152. Each side wall 206a-b of the reactor mast 152 thus has a bottom which constitutes the side wall, a first flap which extends parallel to the upper wall 202 and a second flap which extends parallel to the lower wall 204.
    In the first assembly, each side wall 206a-b of the reactor mast 152 is positioned inside the bowl, that is to say between the side walls 160a-d of the intermediate piece 156, while the upper wall 202 and the lower wall 204 press against the outside against the side walls 160c-d of the intermediate piece 156.
    In the second assembly, each side wall 206a-b of the reactor mast 152 is positioned outside the bowl, that is to say outside the side walls 160a-d of the intermediate piece 156, while the upper wall 202 is pressed against the outside against the side wall 160c of the intermediate piece 156 and the first flap, and the lower wall 204 is pressed against the outside against the second flap.
    In this embodiment, the first flap is shorter than half of the side wall 160c of the intermediate piece 156 opposite to allow the upper wall 202 to bear against both the first flap and the side wall 160c of intermediate piece 156.
    In the embodiment of the invention presented here, the first connecting rod 304a is fixed by two connecting points 306a-b to the beam 302 and by a connecting point 308 to the motor 102, and the second connecting rod 304b is fixed by a connection point 310 to the beam 302 and via a connection point 312 to the motor 102.
    For each connecting rod 304a-b, each connection point to the beam 302 and to the motor 102 is constituted by a yoke produced, respectively in the beam 302 and the motor 102, by a bore passing through the connecting rod 304a-b and by an axis of shear, for example simple, which crosses the yoke and is fitted into the bore of the connecting rod through a ball joint.
    Each connecting rod 304a-b, the beam 302, and the intermediate part 156 define in combination a primary path of forces between the engine 102 and the engine mast 152 to support the loads of the engine 102 under normal operating conditions of said engine 102.
    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 standby safety attachment point (called "waiting fail-safe" in English) which will compensate for a failure of the primary force path, that is to say at least one of the connecting rods 304a-b. In other words, when a component of the primary force path is damaged, the activation of a standby safety attachment point creates an auxiliary force path between the engine 102 and the engine mast 152 .
    The installation of two standby safety attachment points 314a-b ensures better security, and the placement on either side of the median XZ plane of each of them makes it possible to separate the points of pending security attachment 314a-b from the median plane, which facilitates access by a technician to each of these pending security attachment points 314a-b. Indeed, when there is only one standby safety attachment point, it is located in the median plane XZ, that is to say here just below the engine mast 152 which is particularly difficult to access .
    Each standby safety fixing point 314a-b consists for example of a yoke produced in the motor 102 and an axis 316a-b fitted in said yoke and which passes through a bore of the beam 302 whose diameter is greater to the diameter of the axis 316a-b. Thus, in normal operation, there is no contact between the axis 316a-b and the beam 302, and in the event of a rupture of one of the connecting rods 304a-b, the motor 102 will move and the axis 316a-b then comes into contact with the beam 302.
    Although the invention has been more particularly described in the case of a fixing of the front engine attachment to the front face of the engine mast via an intermediate piece, it can be implemented in other types front engine attachment systems, such as in the context of a direct fixing of the beam under the engine mast or a direct fixing of the beam on the front face of the engine mast.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1) Engine attachment (154) for an engine (102) of an aircraft (100) which comprises a jet engine mast (152), the engine attachment (154) comprising a beam (302) intended to be fixed to the jet engine mast ( 152) 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 one of its ends to the beam (302 ) and is intended to be articulated by the other of its ends to the motor (102), where each connecting rod (304a-b) and the beam (302) define in combination a primary path of forces between the motor ( 102) and the engine mast (152) to support the engine loads (102), the engine mount (154) being characterized in that it also includes, for each connecting rod (304a-b), a safety fixing point on standby (314a-b) activated in the event of failure of the primary force path and which creates an auxiliary force path between the motor and the engine mast, and in that the two standby safety attachment points (314a-b) are arranged on either side of the median plane (XZ).
    [2" id="c-fr-0002]
    2) Engine attachment (154) according to claim 1, characterized in that each standby safety attachment point (314a-b) consists of a yoke made in the engine (102) and an axis (316a- b) fitted into said yoke and which passes through a bore in the beam (302) whose diameter is greater than the diameter of Tax (316ab).
    [3" id="c-fr-0003]
    3) Engine attachment system (150) for an engine (102) of an aircraft (100), the engine attachment system (150) comprising:
    - a reactor mast (152) comprising an upper wall (202), a lower wall (204) and on each side, a side wall (206a-b), which together define a front face at the level of the front part of the reactor mast (152), and
    - an intermediate piece (156) which takes the form of a bowl with a bottom wall (158) and four side walls (160a-d) which extend around the bottom wall (158), and
    - a motor attachment (154) according to one of claims 1 or 2, where the beam (302) is fixed against an external face of the bottom wall (158), where the intermediate piece (156) fits at the level from the front face of the reactor mast (152) so that an internal face of the bottom wall (158) comes against the front face of the reactor mast (152), where a side wall (160a) of the intermediate piece (156) bears against a side wall (206a) of the reactor mast (152), where another side wall (160b) of the intermediate piece (156) comes to bear against the other side wall (206b) of the reactor mast (152), where another side wall (160c) of the intermediate piece (156) comes to bear against the upper wall (202) of the engine mast (152), where another side wall (160d) of the intermediate piece (156 ) comes to bear against the lower wall (204) of the reactor mast (152), and where each side wall (160a-d) of the intermediate piece (156) and the wall (202, 204, 206a-b) associated with the engine mast (152) are fixed to each other.
    [4" id="c-fr-0004]
    4) Engine attachment system (150) according to claim 3, characterized in that each side wall (206a-b) of the engine mast (152) takes the form of a U open towards the inside of the engine mast (152 ) and comprising a bottom which constitutes the side wall, a first flap which extends parallel to the upper wall (202) and a second flap which extends parallel to the lower wall (204), in that each side wall ( 206a-b) of the reactor mast (152) is positioned between the side walls (160a-d) of the intermediate piece (156), and in that the upper wall (202) and the lower wall (204) are pressed against the outside against the side walls (160c-d) of the intermediate piece (156).
    [5" id="c-fr-0005]
    5) Engine attachment system (150) according to claim 3, characterized in that each side wall (206a-b) of the engine mast (152) takes the form of a U open towards the inside of the engine mast (152 ) and comprising a bottom which constitutes the side wall, a first flap which extends parallel to the upper wall (202) and a second flap which extends parallel to the lower wall (204), in that each side wall ( 206a-b) of the reactor mast (152) is positioned outside the side walls (160a-d) of the intermediate piece (156), in that the upper wall (202) is pressed against the wall on the outside side (160c) of the intermediate piece (156) and the first flap, and in that the bottom wall (204) is pressed outside against the second flap.
    [6" id="c-fr-0006]
    6) aircraft (100) comprising a structure, an engine (102) and an engine attachment system (150) according to one of claims 3 to 5, where the engine pylon (152) is fixed to the structure, and where a front part of the motor (102) is fixed to said other ends of the connecting rods (304a-b).
    [7" id="c-fr-0007]
    7) aircraft (100) comprising a structure, an engine (102), a reactor mast (152) fixed to the structure and an engine mount (154) according to one of claims 1
    5 or 2, where the beam (302) is fixed to the engine mast (152) and where a front part of the engine (102) is fixed to said other ends of the connecting rods (304a-b).
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3073205B1|2020-11-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1928740A1|2005-09-26|2008-06-11|AIRBUS France|Strut for locking the engine of an aircraft|
    US20150166188A1|2013-02-06|2015-06-18|Commercial Aircraft Corporation Of China, Ltd|Front installation node integrated with aircraft pylon|FR3096347A1|2019-05-21|2020-11-27|Airbus Operations|FRONT ENGINE ATTACHMENT SYSTEM FOR AN AIRCRAFT ENGINE CONTAINING A BEAM MADE IN TWO PARTS|
    FR3096350A1|2019-05-21|2020-11-27|Airbus Operations|FRONT ENGINE ATTACHMENT SYSTEM FOR AN AIRCRAFT ENGINE CONTAINING A BEAM MADE IN THREE PARTS|
    FR3096660A1|2019-05-29|2020-12-04|Airbus Operations|PRIMARY STRUCTURE OF A MAST FOR A REACTOR OF AN AIRCRAFT|
    EP3750812A1|2019-06-14|2020-12-16|Airbus Operations |Aircraft engine assembly comprising a rear engine mount|
    FR3098794A1|2019-07-18|2021-01-22|Airbus Operations |Aircraft thruster assembly featuring an improved primary mast structure and front engine attachment|
    WO2021104913A1|2019-11-27|2021-06-03|Airbus Operations |Front engine attachment system for an aircraft engine, comprising a more lightweight structure|
    FR3113484A1|2020-08-24|2022-02-25|Airbus Operations |Aircraft thruster assembly comprising connecting rods of a front engine attachment connected directly to a front transverse reinforcement of a primary structure of an aircraft mast|
    法律状态:
    2019-05-10| PLSC| Publication of the preliminary search report|Effective date: 20190510 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-11-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1760469A|FR3073205B1|2017-11-08|2017-11-08|ENGINE ATTACHMENT OF AN AIRCRAFT ENGINE|
    FR1760469|2017-11-08|FR1760469A| FR3073205B1|2017-11-08|2017-11-08|ENGINE ATTACHMENT OF AN AIRCRAFT ENGINE|
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