FR3089264A1 - ASSISTANCE DEVICE FOR THE ALIGNMENT OF TWO ORGANS, PREFERABLY FOR AN AIRCRAFT ENGINE ASSEMBLY, AND ASSEMBLY METHOD USING SUCH A DEVICE - Google Patents

Abstract

The invention relates to a device (50) for assisting the alignment of two members intended to be crossed by an assembly pin (32), the device comprising: - a temporary fixing portion (52) on a first member ; - at least one adjustment system (60a, 60b) of the relative position between the two members; - A support portion (54) of the adjustment system, integral with the temporary fixing portion (52), the system (60a, 60b) comprising a rotary element (64) mounted in a housing (66) of the support portion (54), as well as an eccentric element (70) for controlling relative movement between the members, this element (70) being intended to be supported on a surface of the second member, the adjustment system (60a, 60b) comprising also control means (78, 82) configured to rotate the rotary member (64). Figure for the abstract: Figure 5

Description

Description

Title of the invention: DEVICE FOR AIDING THE ALIGNMENT OF TWO ORGANS, PREFERABLY FOR AN AIRCRAFT ENGINE ASSEMBLY, AND ASSEMBLY METHOD USING SUCH A DEVICE Technical field [0001] The invention relates to the field of aircraft engine assemblies, of the type comprising a turbomachine and its pylon for attachment to a structural part of the aircraft, generally a wing element or a fuselage part.

The invention relates in particular to the mounting of the turbomachine on its attachment pylon, preferably in the case where this turbomachine is intended to be attached to a lateral part of the fuselage.

PRIOR ART [0003] The mounting of the turbomachine on the attachment pylon usually requires alignment between two fixing members respectively provided on these two entities, so as to allow the introduction of an assembly axis through these two organs. The misalignment of these members can cause damage to the assembly pin at the time of its introduction. In the event of imprecise alignment, it may even be impossible to make the assembly pin penetrate through the two fixing members. In such a situation, it becomes necessary to carry out an alignment correction, by moving the turbomachine relative to the mast already fixed on the aircraft.

This type of displacement of the turbomachine requires great precision, which can be complicated to implement.

There therefore remains a need to facilitate alignment between the turbomachine and the attachment pylon, this need existing beyond the field of engine assemblies, and relating to any assembly comprising two members intended to be aligned to be traversed by an assembly axis.

Description of the invention [0006] To meet this need, the subject of the invention is a device for assisting the alignment of two members intended to be crossed by an assembly pin, the device comprising:

- A portion of temporary attachment to a first of said two bodies;

- At least one system for adjusting the relative position between a second of said two members, and said first member;

- A support portion of the adjustment system, said support portion being integral with the temporary fixing portion, the adjustment system comprising a rotary element mounted in a housing of the support portion along an axis of rotation, as well as an eccentric element for controlling relative movement between the first and the second member, this eccentric control element being intended to be supported on a surface of the second member and being integral in rotation with the rotary element, [ The adjustment system also comprising control means configured to rotate the rotary element in its housing of the support portion. The invention thus provides a simple design alignment aid device, offering easy use, and capable of being implemented using conventional tools. It turns out to be perfectly suited for ensuring the alignment of a turbomachine relative to a suspension pylon previously fixed to an aircraft structure. However, any other application can be envisaged, without departing from the scope of the invention.

The invention preferably has at least one of the following optional characteristics, taken individually or in combination.

The control means include:

- a lever for driving the rotary element in rotation, the drive lever comprising a first actuating end connected to and integral in rotation with the rotary element; and [0016] - an actuating means connected to a second end of the drive lever, the second end being opposite the first.

The actuating means is configured to vary a spacing distance between the second end of the control lever and the temporary fixing portion, said actuating means preferably being a worm.

The device comprises two separate adjustment systems, respectively capable of generating a relative movement of the two members in two different directions of movement. In this case, the two eccentric elements are intended to bear respectively on two surfaces of the second member with different orientations, these two surfaces preferably being substantially orthogonal to one another.

Each eccentric element is provided with an anti-abrasive coating, preferably a PTEE coating.

There are two adjustment systems, each of which includes:

- Two rotary elements respectively mounted in housings of two frames of the support portion along a common axis of rotation of the two rotary elements, as well as two eccentric elements for controlling relative movement between the first and the second member, these two eccentric control elements being intended to be supported respectively on two surfaces of the second member and being integral in rotation with the two rotary elements;

- Control means configured to simultaneously rotate the two rotary elements in their housings in the support portion.

These control means can then include:

- two levers for rotating the rotary elements, each drive lever comprising the first actuating end connected to and integral in rotation with one of the two rotary elements, respectively;

- a connecting element connecting the two second ends of the two drive levers; and [0025] - the actuating means cooperating with the connecting element.

The invention also relates to a method of mounting a first member with a second member intended to be crossed by an assembly pin, the method being implemented using such a device d alignment aid and comprising the following successive steps:

- Fixing the temporary fixing portion on the first member, and positioning of each eccentric control element against its associated surface of the second member;

- actuation of the control means of at least one adjustment system, so as to align the orifices for passage of the assembly axis provided respectively on the first and second members; and [0029] - introduction of the assembly axis through the through holes.

Preferably, the first member is an engine fastening member secured to a casing of an aircraft turbomachine, and the second member is a complementary fastening member secured to a turbomachine attachment pylon d 'aircraft.

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;

[Fig.l] shows a schematic rear view of an aircraft engine assembly;

[Fig.2] shows a schematic side view of the turbomachine fitted to the engine assembly shown in the previous figure;

[Fig.3] shows a top view of one of the suspensions fitted to the engine assembly shown in Figure 1;

[Fig.4] shows a longitudinal sectional view of the suspension shown in Figure 3;

[Fig.5] is a perspective view of a device for assisting the alignment of two members intended to be assembled, the device being in the form of a preferred embodiment of the invention ;

[Fig.6] is a sectional view of part of the device shown in the previous figure, the section being taken along the line VI-VI of Figure 5;

[Fig.7] shows a perspective view of the part of the device shown in Figure 6;

[Fig.8] schematically shows a step in an assembly process, implementing the alignment aid device shown in the previous figures;

[Fig.9] also diagrams a step in the process;

[Fig.10] also diagrams a step in the process;

[Fig.il] also diagrams a step in the process;

[Fig.12] also diagrams a step in the process;

[Fig.13] also diagrams a step in the process; and [fig.I4] also diagrams a step in the process.

DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS Referring firstly to FIG. 1, there is shown an aircraft engine assembly 200 comprising a turbomachine 201, a mast 202 for attaching the turbomachine 201, and two suspensions 203 connecting the turbomachine 201 to the mast 202.

This is a configuration in which the turbomachine 201 is attached to a lateral part 205 of the fuselage, preferably at the rear of the latter. To do this, the attachment pylon 202 is equipped with a primary structure, called rigid structure, equipped at its lateral end with a fixing beam 207. The two upper and lower ends of this beam 207 participate in the formation of two suspensions 203. In fact, each suspension 203 is produced using an engine fixing member 10 secured to a casing 12 of the turbomachine, and a complementary fixing member formed by one end of the beam 207 from the mast. These two bodies are assembled by being crossed by an assembly pin 32.

As shown schematically in Figure 2, the turbomachine 201 is a turbofan engine with double flow and double body, with a longitudinal axis 16. It comprises a fan casing 18, followed towards the rear of an intermediate casing corresponding to the casing 12 on which the suspensions are fixed 203. With reference jointly to schematic figures 2 and 3, it is noted that the intermediate casing 12 comprises a hub 20, an outer shroud 22 and structural arms 24 connecting the hub 20 to the ferrule 22.

Each engine fixing member 10 is fixed to the outer shell 22 of the intermediate casing, in the radial continuity of one of the structural arms 24.

Referring now to Figures 3 and 4, there is shown one of two suspensions 203. The engine fixing member 10, also called insulator, is produced using one or more parts assembled to each other, and fixed to the outer shell 22. It defines a first passage orifice 26 oriented substantially axially. The complementary fixing member 14, corresponding to one of the ends of the beam 207 of the mast, takes the form of a female yoke equipped with two ears 28 crossed by a second passage orifice 30, coaxial with the first orifice 26. The engine fixing member 10, which will hereinafter be called "first member", is located between the two lugs 28 of the complementary fixing member 14, which will in turn be called "second member".

The first member 10 and the second member 14 are connected to each other by an assembly pin 32 passing through their through holes 26, 30. As can be seen in Figure 4 at the second orifice passage 30, it may not be directly formed by the yoke ears 28, but by washers 34 pre-fitting holes formed through these ears.

A nut 36 ensures the axial fixing of the assembly axis 32 in the form of a screw, by placing this nut in abutment against one of the two ears 28, and the screw head in abutment on the other hear.

The beam 207 has two opposite lateral flanks 40, each provided with recesses 42 in succession in the circumferential direction in which the beam extends. The recesses 42 are separated from each other by ribs 44. Each of them is delimited by a side wall, for example of square, rectangular or diamond-shaped section, and preferably corresponding to the meeting of four parallel surfaces in pairs . These are the four surfaces 46 to 49 referenced in FIG. 4.

Figures 5 to 7 show a device for assisting the alignment of the two members 10, 14 described above. This device 50 is intended to be used for the implementation of a method for mounting the first member 10 on the second member 14, in the context of an assembly of the turbomachine on the mast previously installed on the fuselage of the aircraft. This process will be described later.

The alignment aid device 50 firstly comprises a temporary fixing portion 52, this portion taking the form of a plate intended to be fixed on the first member 10. More specifically, the portion of temporary fixing 52 is intended to cover the first member 10. The device 50 also includes a support portion integral with the temporary fixing portion 52, the support portion comprising two frames 54 arranged on either side of the fixing portion temporary 52. These two frames 54 are preferably identical or substantially identical, and arranged symmetrically with respect to a median plane Pl of the device 50.

The device 50 also includes two separate systems for adjusting the relative position between the first and second members 10, 14. Each of these two systems 60a, 60b is supported by the frames 54, and it comprises several separate elements. Among them, two rotary assemblies respectively associated with each of the two armatures 54, with these two assemblies arranged symmetrically with respect to the median plane Pl. Each rotary assembly 62 comprises a cylindrical rotary element 64 pivotally mounted in a housing 66 of one of the armatures 54, along an axis of rotation 68 which is common to the two assemblies 62, and substantially orthogonal to the median plane Pl. The rotary element 64 is integral in rotation with an eccentric control element 70, which also adopts a cylindrical shape but d axis 72 distinct from the axis of rotation 68, while being parallel to the latter. The two axes 72 of the two eccentric elements 70 of the same adjustment system are also common.

The eccentric control element 70 is intended to cooperate with the mast beam. Also, to limit the risk of damage to this beam during the use of the device 50, the element 70 can be provided with an anti-abrasive coating of the PTLE type.

Finally, each rotary assembly 62 includes a rotational coupling element 74, for example having a star shape or a polygonal shape. The elements 64, 70, 74 are such that the rotary element 64 is located between the eccentric control element 70 and the rotational coupling element. These three elements 64, 70, 74, integral in rotation with one another, can be made in one piece or with the aid of elements fixedly attached to one another.

Each adjustment system 60a, 60b comprises control means for ensuring the simultaneous rotation of two rotary assemblies 62 relative to the frames 54, by pivoting of the two rotary elements 64 in their respective housings 66 of these frames. These control means comprise a lever 78 for driving in rotation associated with each of the two rotary assemblies 62, namely two levers 78 arranged symmetrically with respect to the plane Pl. Each drive lever 78 comprises a first actuation end connected to the rotary element 64 of its associated assembly 62, by form cooperation with the coupling element 74 of this same assembly. This makes it possible to make the first end of the lever 78 integral in rotation with the rotary element 64 of the associated assembly 62.

The second end of the lever 78, opposite the first, is pivotally mounted on a connecting element 80 in the form of a rod. More specifically, the two ends of the rod 80 are respectively rotatably mounted on the second end of each of the two levers 78 of the control means, the axis of rotation of these links corresponding to the axis of the rod 80. These the latter are completed by an actuating means in the form of an endless screw 82, one threaded end of which cooperates with the rod 80, and of which a possible opposite second threaded end cooperates with a part 84 connecting the two frames 54. This part 84 can also be a rod capable of pivoting on itself relative to the reinforcements 54, as can be seen in FIG. 5.

The worm 82 can be equipped with a control portion 86, for example of hexagonal shape or the like so that it can be actuated in rotation by a conventional tool. Indeed, by rotating the screw 82 through its control portion 86, this results in a variation in the distance between the rod 80 connected to the second ends of the two levers 78, and the rod 84 connecting the two frames 54. This thus leads to varying the spacing distance between the second end of each lever 78, and the temporary fixing portion 52. With this variation in distance, each of the two levers 78 is rotated according to the axis 68 relative to the frame 54, leading its associated eccentric control element 70 to pivot eccentrically along this same axis of rotation 68.

A method of mounting the first member 10 of the turbomachine, with the second member 14 of the mast beam, will now be described with reference to Figures 8 to 14. This method is part of the fixing of the turbomachine 201 on the beam 207 of the mast previously fixed on the fuselage 205 of the aircraft.

A first step thus consists in bringing the turbomachine 201 closer to the beam 207, as shown diagrammatically in FIG. 8. The objective of this first step lies in the positioning of each first member 10 of the engine, in the female yoke forming the second member 14 at each end of the beam 207. At this stage, within each suspension 203 not yet assembled, the alignment of the two members 10, 14 may not be perfectly precise, thus requiring the use of the aid device 50 described above.

The next step is shown diagrammatically in FIGS. 9 to 11. It consists first of all in fixing the device 50 on the first member 10 of each suspension 203 requiring correction of the alignment of the two members 10, 14. To effect this fixing, the temporary fixing portion 52 of the device 50 is mounted on a radially external part of the first member 10, for example using screws. Then, the two eccentric control elements 70 of each of the two adjustment systems 60a, 60b are placed in their respective recesses 42 of the beam 207, as is best visible in FIG. 12. More precisely, each eccentric element 70 is brought into contact with its associated surface of the recess 42 with which they cooperate. For the two eccentric elements 70 of the first adjustment system 60a, the surface of the contacted recess corresponds to the surface 47 oriented substantially circumferentially and of a substantially planar nature. Furthermore, for the two eccentric elements 70 of the second adjustment system 60b, the surface contacted in its associated recess corresponds to the surface 49 oriented substantially radially, and also of substantially planar nature. Consequently, the actuation of the first adjustment system 60a makes it possible to generate a displacement of the first member 10 relative to the second member 14, in a first direction DI substantially orthogonal to the surface 47 of the recess. In addition, the actuation of the second adjustment system 60b makes it possible to generate a displacement of the first member 10 relative to the second member 14, in a second direction D2 substantially orthogonal to the surface 49 of another recess 42, preferably directly adjacent to the one mentioned above. Thanks to the design adopted, it is thus possible to move the first member 10 in two directions DI, D2 substantially orthogonal to each other, relative to the second member 14 remaining fixed relative to the aircraft pre-equipped with the mast. Once each device 50 thus installed on the first member 10 and the second member 14, the control means of one or two adjustment systems 60a, 60b of each device are actuated, in order to achieve the desired alignment between the orifices for passage of these two members 10, 14. This actuation is carried out by rotation of each endless screw 82 concerned, which causes the associated eccentric element 70 to slide on its recess surface. Such a situation is shown diagrammatically in FIGS. 13 and 14 for one of the eccentric elements 70 of the first adjustment system 60a. In these figures, it can be seen that the pivoting of the drive lever 78 along the axis of rotation 68, caused by the actuation of the associated worm screw, causes the eccentric element 70 to slide on the surface 47 of the corresponding recess 42. This sliding causes a spacing / approximation of the axis of rotation 68 relative to the surface 47, in the direction Dl. This same spacing / approximation in the direction Dl is transmitted to the frame 54 (not shown in FIGS. 12 to 14), to the temporary fixing portion 52, then to the first member 10 driving with it the whole of the turbomachine.

Once the members 10, 14 of each suspension are correctly aligned, the assembly pin is introduced through the orifices for passage of these same members, before the devices 50 are withdrawn. Prior to the introduction of the assembly axis 32, a pin of diameter slightly smaller than that of this axis can be introduced into the orifices for passage of the members, so as to check their alignment. This spindle, possibly also coated with an anti-abrasive coating of the PTFE type, is used to avoid possible damage to the assembly pin when the latter is introduced while precise alignment has not yet been obtained. .

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 and according to the scope defined by the appended claims.

Claims (1)

Claims [Claim 1] Device (50) for helping to align two members (10, 14) intended to be crossed by an assembly pin (32), the device comprising: - a temporary fixing portion (52) on a first (10) of said two members; - at least one adjustment system (60a, 60b) of the relative position between a second (14) of said two members, and said first member (10); - A support portion (54) of the adjustment system, said support portion (54) being integral with the temporary fixing portion (52), the adjustment system (60a, 60b) comprising a rotary element (64) mounted in a housing (66) of the support portion (54) along an axis of rotation (68), as well as an eccentric element (70) for controlling the relative movement between the first (10) and the second member (14), this eccentric control element (70) being intended to be supported on a surface (47, 49) of the second member (14) and being integral in rotation with the rotary element (64), the adjustment system (60a, 60b) also comprising control means (78, 82) configured to rotate the rotary element (64) in its housing (66) of the support portion (54). [Claim 2] Device according to claim 1, characterized in that the control means comprise: - A lever (78) for driving in rotation the rotary element (64), the drive lever (78) comprising a first actuating end connected to and integral in rotation with the rotary element (64); and - an actuating means (82) connected to a second end of the drive lever (78), the second end being opposite the first. [Claim 3] Device according to claim 2, characterized in that the actuating means (82) is configured to vary a distance between the second end of the control lever (78) and the temporary fixing portion (52), said actuating means (82) preferably being an endless screw (82). [Claim 4] Device according to any one of the preceding claims, characterized in that it comprises two separate adjustment systems (60a, 60b), respectively capable of generating a relative movement of the two members (10, 14) in two directions of movement ( DI, D2) different. [Claim 5] Device according to claim 4, characterized in that two respective eccentric elements (70) of the two separate adjustment systems (60a, 60b) are intended to bear respectively on two surfaces of the second member (47, 49) of different orientations , these two surfaces preferably being substantially orthogonal to one another. [Claim 6] Device according to any one of the preceding claims, characterized in that each eccentric element (70) is provided with an anti-abrasive coating, preferably a PTFE coating. [Claim 7] Device according to any one of the preceding claims, comprising two adjustment systems (60a, 60b), characterized in that each adjustment system (60a, 60b) comprises: - two rotary elements (64) respectively mounted in housings (66) of two frames of the support portion (54) along a common axis of rotation (68) of the two rotary elements (64), as well as two eccentric elements (70 ) relative movement control between the first (10) and the second member (14), these two eccentric control elements (70) being intended to be supported on respectively two surfaces (47, 49) of the second member (14) and being integral in rotation with the two rotary elements (64); - control means (78, 82) configured to simultaneously rotate the two rotary elements (64) in their housings (66) of the support portion (54). [Claim 8] Device according to claim 7, characterized in that the control means comprise: - two levers (78) for rotating the rotating elements (64), each driving lever (78) comprising the first actuating end connected to and integral in rotation with one of the two rotating elements (64) , respectively ; - a connection element (80) connecting the two second ends of the two drive levers (78); and - the actuation means (82) cooperating with the connection element (80). [Claim 9] Method for mounting a first member (10) with a second member (14) intended to be crossed by an assembly pin (32), the method being implemented using a device for assisting in the alignment (50) according to any one of the preceding claims, characterized in that it comprises the following successive steps: - fixing the temporary fixing portion (52) on the first member (10), and placing each eccentric control element (70) against its associated surface (47, 49) of the second member (14); - actuation of the control means (78, 82) of at least one adjustment system (60a, 60b), so as to align passage orifices (26, 30) of the assembly axis (32) provided respectively on the first and second members (10, 14); and - introduction of the assembly pin (32) through the through holes (26, 30). [Claim 10] Method according to claim 9, characterized in that the first member (10) is an engine fixing member secured to a casing (12) of an aircraft turbomachine (201), and in that the second member (14) is a complementary fastening member integral with an attachment pylon (202) of an aircraft turbomachine.