• 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:
    In order to facilitate the mounting of a front engine attachment (50a) of an aircraft engine assembly, the invention provides: - a shear pin (70) oriented in a longitudinal direction (X) and integral with a rib of front closure (74) of the mast casing and projecting forwards; - a main attachment body (54) arranged axially facing the intermediate housing hub, at the rear thereof, the main attachment body having a hole (62) accommodating the shear pin (70) ; - Fixing means (64) of the main attachment body (54) on the engine; and - means for axially holding the main attachment body (54) relative to the rib (74), these means comprising first screws (78a) whose head cooperates with the rib (74), as well as barrel nuts (80) cooperating with the screws (78a) and housed in the main attachment body (54).
    公开号:FR3061480A1
    申请号:FR1663542
    申请日:2016-12-30
    公开日:2018-07-06
    发明作者:Wolfgang Brochard
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    @ Holder (s): AIRBUS OPERATIONS Simplified stock company.
    by
    O Extension request (s):
    Agent (s): BREVALEX Limited liability company.
    ® ENGINE ASSEMBLY FOR AN AIRCRAFT INCLUDING A FRONT ENGINE MOUNT FOR EASY ASSEMBLY.
    FR 3,061,480 - A1 (57) In order to facilitate the mounting of a front engine attachment (50a) of an engine assembly for an aircraft, the invention provides:
    - A shear pin (70) oriented in a longitudinal direction (X) and integral with a front closing rib (74) of the mast box and projecting forward;
    - A main attachment body (54) arranged axially opposite the intermediate casing hub, at the rear thereof, the main attachment body having an orifice (62) for housing the shear pin (70) ;
    - fixing means (64) of the main attachment body (54) on the engine; and
    - means for axially holding the main attachment body (54) relative to the rib (74), these means comprising first screws (78a) whose head cooperates with the rib (74), as well as barrel nuts ( 80) cooperating with the screws (78a) and housed in the main attachment body (54).

    ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING A FRONT ENGINE MOUNT FOR EASY ASSEMBLY
    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to the field of engine assemblies for aircraft comprising an engine, as well as a device for attaching the engine to a structure of the aircraft, preferably under a wing of this aircraft. Such an attachment device is for example known from document FR 3 014 840.
    It applies preferentially to commercial aircraft.
    STATE OF THE PRIOR ART
    On existing aircraft, engines such as turbofan and double-barrel engines are usually hung below or above the wing, or else attached to the fuselage by complex hooking devices, also called "EMS" (from the English “Engine Mounting Structure”), or even a mast. The usually used hanging masts have a primary structure, also called rigid structure. This primary structure generally forms a box, that is to say it is constituted by the assembly of lower and upper beams connected together by a plurality of transverse stiffening ribs, located inside the box. The side members are arranged on the lower and upper sides, while side panels close the box on the side faces.
    In known manner, the primary structure of these attachment devices is designed to allow the transmission to the wing of the static and dynamic forces generated by the engines, such as the weight, the thrust, or even the various dynamic forces.
    In the solutions known from the prior art, the transmission of forces between the engine and the primary structure is conventionally ensured by attachment means consisting of a front engine attachment, a rear engine attachment and a device for resumption of pushing efforts. These elements together form an isostatic fastening system.
    For example, the front engine attachment is fixed to the central engine casing, or to the hub of an intermediate casing located between the central casing and the fan casing.
    The attachment means thus ensure the transmission of forces in the direction of the mast, while limiting the internal deformations of the engine. To allow the healthiest possible transmission of forces between the motor and the rigid structure, the front motor attachment must be located axially as close as possible to the hub of the intermediate casing, in order to approach the force recovery plane formed by this intermediate casing fitted with structural arms.
    However, getting closer to the hub of the intermediate casing makes mounting the front engine mount difficult, since the axial space between these elements becomes limited. The introduction and handling of the tools and of the fastening elements of this attachment prove to be complicated, and all the more so when the hub has a large diameter intermediate casing hub, as is the case in turbojet engines the fan is driven by a reducer.
    There is therefore a need to optimize the design of the front engine mount, in order to facilitate its mounting.
    STATEMENT OF THE INVENTION
    To meet this need, the subject of the invention is an engine assembly for an aircraft comprising:
    - a double-flow motor comprising a fan casing, a central casing and an intermediate casing situated axially between the blower casing and the central casing, the intermediate casing comprising a hub, an outer ferrule situated in the extension of the casing of blower, as well as structural arms connecting the hub to the outer shell;
    - An engine attachment pylon on a structure of the aircraft, the pylon comprising a primary structure forming a box;
    - means for attaching the engine to the primary structure of the attachment pylon, the attachment means comprising a front engine attachment connecting the primary structure to the hub of the intermediate casing or to the central casing and configured to take up at least s 'exercising in a transverse direction and in a vertical direction of the motor assembly.
    According to the invention, the front engine attachment includes:
    - A shear pin oriented in a longitudinal direction of the engine assembly, the pin being integral with a front closing rib of the box and projecting forward;
    - A main attachment body arranged axially opposite the intermediate casing hub, at the rear thereof, the main attachment body having an orifice for housing the shear pin;
    - means for fixing the main attachment body to the engine; and
    - means for axially holding the main attachment body relative to the front closing rib, these axial holding means comprising first screws whose head cooperates with the front closing rib, as well as barrel nuts cooperating with the first screws and housed in the main attachment body.
    The invention is thus remarkable in that it provides a front engine attachment design which requires for its mounting only limited access, or even zero, between the main attachment body and the hub of the intermediate casing. The front engine attachment can thus be brought as close as possible to the hub, even when the latter has a large diameter, and this for a more direct transmission of forces in the plane of the intermediate casing.
    The invention provides at least one of the following optional characteristics, taken individually or in combination.
    The main attachment body comprises a main fitting carrying a ball joint, an inner ball joint ring defining said housing orifice which receives the shear pin.
    The main attachment body has protrusions projecting forward, the protrusions accommodating the barrel nuts.
    The protrusions have blind holes receiving the barrel nuts.
    The heads of the first screws are pressed against the ears for fixing the front closing rib.
    The main attachment body is completely masked forward by the intermediate casing hub, in the longitudinal direction.
    The means for fixing the main attachment body to the engine are articulated shackles.
    Said axial holding means also comprise a second screw oriented in the longitudinal direction of the engine assembly, and passing through the main attachment body as well as the front closing rib so as to jointly ensure, with the shear pin, the recovery forces linked to the parasitic torsional moment in the longitudinal direction. Alternatively, the front closing rib is equipped with a second shear pin parallel to the pin, so that the two pins together ensure the resumption of the forces associated with the parasitic moment of torsion in the longitudinal direction.
    The engine preferably comprises a fan driven by a reduction gear.
    The invention also relates to an aircraft comprising at least one such engine assembly.
    Finally, the subject of the invention is a method of mounting such an engine assembly, comprising the following steps:
    - Attachment of the main attachment body to the engine, using said attachment means;
    vertical displacement of the engine relative to the attachment pylon fixed to the aircraft, so that the shear pin is aligned and at an axial distance from the housing orifice of the main attachment body;
    - axial displacement of the engine relative to the attachment pylon fixed to the aircraft, so as to cause the shear pin to penetrate into the housing orifice of the main attachment body; and
    - installation and fixing of the first screws, from an area behind the main attachment body.
    Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.
    BRIEF DESCRIPTION OF THE DRAWINGS
    This description will be made with reference to the accompanying drawings, among which;
    - Figure 1 shows a side view of an aircraft comprising engine assemblies according to the invention;
    - Figure 2 is a schematic view in longitudinal section of an engine fitted to one of the engine assemblies of the aircraft shown in the previous figure;
    - Figure 3 is a partial perspective view of one of the engine assemblies, according to a preferred embodiment of the invention;
    - Figure 4 shows a partial side view of the engine assembly shown in the previous figure, showing more particularly the front engine attachment;
    - Figure 5 is a perspective view of the part of the engine assembly shown in the previous figure;
    - Figure 6 is an exploded perspective view of the front engine mount shown in the previous figure;
    - Figure 7 is an un-exploded perspective view of the front engine mount shown in the previous figure;
    - Figure 7a is a sectional view taken along the line VIla-Vlla of Figure 7;
    - Figure 8 is a sectional view taken along line VIII-VIII of Figure 7;
    - Figure 9 is a perspective view of a barrel nut used to make the front engine mount shown in the previous figures; and
    - Figure 10 is a perspective view similar to that of Figure 6, showing an alternative embodiment.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    Referring to Figure 1, there is shown an aircraft 200 comprising a fuselage 3 on which are fixed two airfoils 2 (only one visible in Figure 1), each airfoil carrying an engine assembly 5 according to the invention. This engine assembly 5, also known as a propulsion assembly, comprises an engine 10 with double flow and with double body, such as a turbojet engine, a device 4 for attaching the engine 10, also known as an attachment mast, as well as a nacelle. 11 surrounding the engine. Conventionally, the motor assembly 5 is suspended under its wing 2. However, it could be hung above the wing or attached to the rear part of the fuselage.
    Throughout the description which follows, by convention, the direction X corresponds to the longitudinal direction of the device 4 which is also comparable to the longitudinal direction of the turbojet engine 10 and that of the engine assembly 5, this direction X being parallel to a longitudinal axis of this turbojet engine 10. On the other hand, the direction Y corresponds to the direction oriented transversely relative to the device 4 and also comparable to the transverse direction of the turbojet engine and that of the engine assembly 5, and the direction Z corresponds in the vertical or height direction, these three directions X, Y and Z being orthogonal to each other.
    On the other hand, the terms “front” and “rear” are to be considered with respect to a direction of advance of the aircraft encountered following the thrust exerted by the turbojets 10, this direction being represented schematically by the arrow 7.
    With reference to FIG. 2, it is first of all noted that the turbojet engine 10 is preferably a turbojet engine whose fan is driven not directly by the gas generator, but by a reducer 11 itself driven by the gas reducer . The latter comprises, from front to rear, a low pressure compressor 13, a high pressure compressor 15, a combustion chamber 17, a high pressure turbine 19 and a low pressure turbine 21, as has been schematized on the figure 2.
    The turbojet engine has a structural outer casing formed by different casings. It is, from front to rear, a fan casing 20, an intermediate casing 22, a central casing 24 and a gas ejection casing 26. The intermediate casing 22 includes an outer ring 28 which is located in the rear extension of the fan casing, with substantially the same diameter. This ferrule 28 internally carries structural radial arms 32 which are connected, at their internal end, to a hub 30 of the fan casing. These radial arms 32 are also called OGV (from the English “Outlet Guide Vane”). The intermediate casing elements 28, 30, 32 are crossed by a transverse plane PI of the turbojet engine 10, passing through a rear end of the low pressure compressor 13.
    With reference to FIG. 3, the motor assembly 5 also includes the attachment pylon of which the primary structure 8 is shown, but not the secondary structures intended to be attached to this primary structure 8. These secondary structures are conventional and do not will not be detailed below. They ensure segregation and maintenance of the systems while supporting aerodynamic fairing elements.
    The primary structure 8 forms a box, that is to say that it is formed by upper 36 and lower 38 beams, and two side panels 40. These box elements are connected together by means of internal ribs. transverse stiffening 42, which are usually oriented along parallel planes YZ. These ribs are distributed in the box, along the direction X. It is also possible to provide a more "integrated" design of the box, in the sense of that described above.
    The box 8 is fixed to the wing element 2 by conventional means, not described. In addition, the engine 10 is hooked under the wing to the box 8 by attachment means 52 preferably consisting of a front engine attachment 50a, a rear engine attachment 50b and two connecting rods 50c for resumption of thrust forces. . The rear engine attachment 50b connects the ejection casing 26 to the lower beam 38 of the box. The front engine mount 50a is specific to the present invention, and connects the front end of the box to a front end of the central casing 24, very close to the hub 30 of the intermediate casing.
    Preferably, the attachment means 52 form an isostatic system for taking up forces. In fact, provision is made for the front engine attachment 50a to ensure only the recovery of forces in the directions Y and Z, while the connecting rods 50c only to provide for the recovery of forces in the direction X. As for the rear engine attachment 50b , this defines two lateral half-attachments arranged on either side of the median vertical plane XZ. The first half-tie is designed to ensure only the recovery of the thrust forces oriented in the direction Z, and the second half-tie is designed to ensure only the recovery of the thrust forces oriented in the directions Y and Z. Depending on the configuration , the recovery of forces in the direction Y can also take place in the center of the driving beam, and would then be taken up by the second half-clip only in the event of failure.
    Also, the resumption of the forces exerted in the direction X is effected using the connecting rods 50c, the resumption of the forces exerted in the direction Y is effected using the front engine attachment 50a and of the second rear half-attachment, while the resumption of the forces exerted in the direction Z takes place jointly using the front engine attachment 50a and the two rear half-attachments.
    On the other hand, the resumption of the moment acting in the direction X takes place vertically using the two rear half-fasteners, the resumption of the moment exercising in the direction Y takes place vertically using of these two half-fasteners jointly with the front engine fastener 50a, and the resumption of the moment exerted in the direction Z is carried out transversely using the second rear half-fastener together with the front engine fastener 50a .
    The front engine attachment 50a will now be described with reference to FIGS. 4 to 9.
    First of all, it comprises a main attachment body 54 located in close axial proximity to the rear end of the hub 30. This hub, of substantial diameter due to the presence of the reduction gear, masks the body towards the rear main attachment 54 in direction X. More preferably, it is the whole of the front engine attachment 50a which is masked forwards by the hub 30 of the intermediate casing. In other words, the fastener 50a does not extend beyond the hub 30 in the radial direction.
    The main attachment body 54 is produced by a main fitting 56 extending in a plane YZ. This fitting can be doubled in direction X for safety reasons, and thus take on a so-called “Fail Safe” function. On its front face, the main fitting 56 carries axial protrusions 58 projecting towards the front, for example three protrusions 58 arranged near the periphery of the fitting 56. The protrusions 58 are preferably made in one piece with the main fitting 56, or else attached thereto.
    The main fitting 56 is equipped in its center with a ball joint 60 comprising an outer ring 60a, as well as an inner ring 60b pierced with an orifice 62 for housing a shear pin which will be described below. The orifice 62 is through and has an axis parallel to the direction X.
    The fastener 50a comprises means for fixing the main fitting on the front end of the central casing 24. These means comprise two shackles 64 or rods, articulated at one of their ends on the main fitting 56, and articulated at the 'other end on yokes 66 of the central casing 24. The axes of articulation of the shackles are preferably oriented in the direction X. In addition, the two shackles 64 are preferably arranged in V open downwards, in order to take up the forces Y and Z. The force recovery directions of the shackles 64 intersect at the center of the pin 70 in order to reduce the parasitic moment in the direction X, as will be described later.
    The fastener 50a is also equipped with a shear pin 70 oriented in the direction X, and housed in the orifice 62 of the ball joint carried by the main fitting 56. Preferably, in the assembled state, the pin crosses entirely the orifice 62 and protrudes slightly from the latter, towards the front. The pin 70 and the housing orifice 62 are of complementary circular sections. The pin 70 is integral with a front closing rib 74 of the box 8, being made in one piece with this rib. More specifically, to fulfill a "Fail Safe" function, the rib 74 and the pin 70 are produced by two pieces pressed against one another in the direction Y, and each comprising a half-rib and a half-pin. It is also noted that the rib 74 could be an independent piece (s) attached to the other elements of the box, or else one / pieces integrated into these same box elements such as the side members and / or the side panels.
    Projecting laterally from its lateral edges, the front closing rib 74 comprises fixing ears 76 cooperating with means for axially retaining the main body 54, relative to the rib 74. These means here comprise three first screws 78a whose head cooperates with the ears 76, while being supported on the rear surface thereof. The first three screws 78a thus each have a threaded part extending forward in the direction X, and screwed into a barrel nut 80. Each barrel nut 80 is housed in a blind hole 82 of one of the protrusions 58 of the main attachment body. The blind hole 82 is open upwards and / or laterally, but preferably not downwards to prevent the barrel nut 80 from coming out of this hole during handling, before assembly of the associated screw 78a.
    As a reminder, a barrel nut is generally a nut which has a cylindrical outer surface whose axis 84 is perpendicular to the axis 83 of the threaded hole 84 which passes through it. This axis 83 coincides with the axis of the screw 73, namely here oriented in the direction X. A barrel nut can be produced, as the case may be, in one or two pieces. In the second case, it comprises a floating nut, mounted in a housing formed in a cylindrical nut support. This type of nut is also known as a barrel nut, or a sleeve nut.
    Thus, the barrel nut 80, blocked by the blind hole 82 in rotation and in translation along the axis 83 of the tapped hole 84, allows easy mounting of the first screw 78a intended to be screwed into this same tapped hole 84. The latter can also be extended by a flange 86 deformed for example elliptically, to allow the rotation blocking in the direction X of this screw 78a.
    As shown in FIG. 8, each first screw 78a crosses with clearance a through hole 90 made in the main fitting 56. This makes it possible to facilitate the mounting of these three screws 78a in their respective nuts 80.
    Although this has not been shown, the barrel nut 80 could alternatively be a non-truncated cylinder of circular section, without departing from the scope of the invention.
    It is also possible to provide that the front engine attachment 50a can take up the forces linked to the parasitic moment of torsion in the direction X. To do this, the forces are taken up vertically on the one hand using the shear pin 70 , and on the other hand using a second screw 78b. This second screw 78b thus crosses with a very small clearance the passage hole 90 of the main fitting 56, to obtain an adjusted mounting. It is screwed onto a conventional nut (not shown) bearing against the front surface of this main fitting 56. The head of the second screw 78b is in support bearing against one of the ears 79 of the front closing rib 74 , just like the first three screws 78a. Moreover, the four screws 78a, 78b are distributed around the shear pin 70 centered relative to these. Alternatively, to perform this same function, the rib 74 could be equipped with a second shear pin parallel to the pin 70. This embodiment is shown in FIG. 10. The second pin 70a, of smaller diameter, is located above of the shear pin 70, and enters a housing orifice 62a of the main fitting 56.
    The motor assembly 5 described above allows easy mounting, which requires only a small axial access between the hub 30 of the intermediate casing, and the main attachment body 54. In fact, it is first carried out fixing the main attachment body 54 to the central casing 24, using shackles 64. At this stage, the barrel nuts 80 can be housed in the protrusions 58. Then, a vertical displacement of the engine is carried out relative to the suspension pylon 4 fixed under the wing of the aircraft, so that the shear pin 70 is aligned and at a distance from the housing orifice 62, in the direction X. This state is shown in FIG. 6. The process is continued by moving the motor axially relative to the mast, so as to make the shear pin 70 penetrate the housing orifice of the main attachment body 54, as can be seen in FIG. 7. Finally, the first 78 screws are installed a from an area 94 referenced in FIG. 4, located at the rear of the main attachment body 5 54. No access is thus required on the other side of the body 54 for tightening the screws
    78a in their respective barrel nuts 80. The assembly is completed when the main attachment body 54 is pressed against the fixing lugs 76 of the front closing rib 74. It is noted that in the case of an implementation of the second screw 78b, this is mounted before the first screws 78a, in order to facilitate its fixing.
    Of course, various modifications can be made by those skilled in the art to the invention which has just been described, only by way of nonlimiting examples.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Engine assembly (5) for aircraft comprising:
    - a double-flow motor (10) comprising a fan casing (20), a central casing (24) and an intermediate casing (22) located axially between the blower casing and the central casing, the intermediate casing comprising a hub (30), an outer shroud (28) located in the extension of the fan casing (20), as well as structural arms (32) connecting the hub (30) to the outer shroud (28);
    - An engine attachment pylon (4) (10) on an aircraft structure, the pylon comprising a primary structure (8) forming a box;
    - attachment means (52) of the engine on the primary structure (8) of the attachment mast, the attachment means comprising a front engine attachment (50a) connecting the primary structure (8) to the hub (30) of the intermediate casing or to the central casing (24) and configured to take up at least the forces exerted in a transverse direction (Y) and in a vertical direction (Z) of the engine assembly, characterized in that the front engine attachment (50a) includes:
    - A shear pin (70) oriented in a longitudinal direction (X) of the engine assembly, the pin being integral with a front closing rib (74) of the box and projecting forward;
    - A main attachment body (54) arranged axially opposite the hub (30) of the intermediate casing, at the rear thereof, the main attachment body having an orifice (62) for housing the shear pin (70);
    - fixing means (64) of the main attachment body (54) on the engine; and
    - means for axially holding the main attachment body (54) relative to the front closing rib (74), these axial holding means comprising first screws (78a) whose head cooperates with the front closing rib (74 ), as well as barrel nuts (80) cooperating with the first screws (78a) and housed in the main attachment body (54).
    [2" id="c-fr-0002]
    2. Motor assembly according to claim 1, characterized in that the main attachment body (54) comprises a main fitting (56) carrying a ball joint (60), of which an internal ball joint ring (60b) defines said housing orifice (62) which receives the shear pin (70).
    [3" id="c-fr-0003]
    3. Motor assembly according to claim 1 or claim 2, characterized in that the main attachment body (54) has protrusions (58) projecting forward, the protrusions housing the barrel nuts (80).
    [4" id="c-fr-0004]
    4. Motor assembly according to the preceding claim, characterized in that the protrusions (58) comprise blind holes (82) receiving the barrel nuts (80).
    [5" id="c-fr-0005]
    5. Motor assembly according to any one of the preceding claims, characterized in that the heads of the first screws (78a) are in abutment against fixing ears (76) of the front closing rib (74).
    [6" id="c-fr-0006]
    6. Motor assembly according to any one of the preceding claims, characterized in that the main attachment body (54) is entirely masked forwards by the hub (30) of intermediate casing (22), in the longitudinal direction (X).
    [7" id="c-fr-0007]
    7. Motor assembly according to any one of the preceding claims, characterized in that the means for fixing the main attachment body (54) to the motor (10) are articulated shackles (64).
    [8" id="c-fr-0008]
    8. Motor assembly according to any one of the preceding claims, characterized in that said axial holding means also comprise a second screw (78b) oriented in the longitudinal direction (X) of the motor assembly, and passing through the main body d 'fastener (54) and the front closing rib (74) so as to ensure jointly, with the shear pin (70), the resumption of forces related to the parasitic moment of torsion in the longitudinal direction (X).
    [9" id="c-fr-0009]
    9. Motor assembly according to any one of claims 1 to 7, characterized in that the front closing rib (74) is equipped with a second shear pin (70a) parallel to the pin (70), so that the two pins (70, 70a) jointly ensure the resumption of the forces associated with the parasitic moment of torsion in the longitudinal direction (X).
    [10" id="c-fr-0010]
    10. Motor assembly according to any one of the preceding claims, characterized in that the motor (10) comprises a fan (9) driven by a reduction gear (11).
    [11" id="c-fr-0011]
    11. Aircraft (200) comprising at least one engine assembly (5) according to any one of the preceding claims.
    [12" id="c-fr-0012]
    12. A method of mounting an engine assembly (5) according to any one of claims 1 to 10, characterized in that it comprises the following steps:
    - fixing the main attachment body (54) to the engine (10), using said fixing means (64);
    - vertical displacement of the engine (10) relative to the suspension pylon (4) fixed on the aircraft, so that the shear pin (70) is aligned and at an axial distance from the housing orifice (62) the main attachment body (54);
    - axial displacement of the engine (10) relative to the attachment pylon (4) fixed on the aircraft, so as to cause the shear pin (70) to penetrate into the housing orifice (62) of the main attachment body (54); and
    - Installation and fixing of the first screws (78a), from a zone (94) located behind the main attachment body (54).
    S.61796
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    同族专利:
    公开号 | 公开日
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    CN108263621A|2018-07-10|
    FR3061480B1|2019-05-31|
    US10829233B2|2020-11-10|
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    法律状态:
    2017-12-21| PLFP| Fee payment|Year of fee payment: 2 |
    2018-07-06| PLSC| Publication of the preliminary search report|Effective date: 20180706 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1663542A|FR3061480B1|2016-12-30|2016-12-30|AIRCRAFT ENGINE ASSEMBLY COMPRISING A FRONT ENGINE ATTACHMENT FACILITATING ITS ASSEMBLY|
    FR1663542|2016-12-30|FR1663542A| FR3061480B1|2016-12-30|2016-12-30|AIRCRAFT ENGINE ASSEMBLY COMPRISING A FRONT ENGINE ATTACHMENT FACILITATING ITS ASSEMBLY|
    US15/850,115| US10829233B2|2016-12-30|2017-12-21|Engine assembly for an aircraft comprising a front engine attachment which facilitates its assembly|
    CN201711467924.2A| CN108263621A|2016-12-30|2017-12-29|The method of engine pack, the aircraft including engine pack and component assembling|
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