METHOD FOR ASSEMBLING A REDUCTION GEAR AND FACILITY FOR IMPLEMENTING THE METHOD

Abstract

A method of mounting a gearbox is described. The gearbox includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The method consists in applying simultaneously and independently a first torque to the first crown centered on the axis of the first crown and a second torque is applied to the second crown centered on the axis of the second crown, the first torque and the second torque having identical values.

Claims

1. A method of mounting a reduction gear of longitudinal axis, comprising an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation on a planet carrier, the outer sun gear comprising a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears, the method comprising: a) providing an assembly comprising the inner sun gear, the planet gears meshing with the inner sun gear and carried by a planet carrier; b) mounting the first crown and the second crown around the planet gears so that toothings of the first crown and the second crown mesh with the first toothings of the planet gears and the second toothings of the planet gears, respectively; and c) applying a first torque to the first crown centered on the axis of the first crown and a second torque to the second crown centered on the axis of the second crown, the first torque and the second torque having identical values and being applied in the same direction of rotation about the axes of the first and second crowns.

2. The method according to claim 1, in which after step c), the method comprises a step of joining the first crown and the second crown.

3. The method according to claim 2, wherein the joining step is carried out by bolting a first annular flange of the first crown with a second annular flange of the second crown (14b).

4. The method according to claim 1, in which the applied torque has a value which corresponds to the torque undergone by the reduction gear during a given phase of use, this torque being at least greater than 10 N.

5. The method according to claim 1, in which the first and second toothings of the planet gears, the first toothing of the first crown and the second toothing of the second crown are inclined with respect to the longitudinal axis of the reduction gear.

6. The method according to claim 5, wherein the first toothing of the first crown and the second toothing of the second crown have a herringbone arrangement cooperating with a chevron arrangement formed by the first and second toothings of the planet gears.

7. The method according to claim 1, which includes an intermediate step between steps a) and b) consisting of locking the inner sun gear, planet gears and planet carrier against rotation about the longitudinal axis.

8. An installation for mounting an outer sun gear with a double crown in a reduction gear, comprising: a frame for supporting said reduction gear along its longitudinal axis; first means for applying a torque around the axis of a first ring configured to engage with a first crown of the outer sun gear; second means for applying a torque around the axis of a second ring configured to engage with a second crown of the outer sun gear, the first ring being connected to the first torque-applying means by first connecting means allowing a degree of freedom of the first ring in a plane perpendicular to the longitudinal axis and the second ring being connected to the second torque-applying means by second connecting means allowing a degree of freedom of the first ring in a plane perpendicular to the longitudinal axis, the first connecting means being independent of the second connecting means.

9. The installation according to claim 8, wherein: the first means for applying a torque comprise N traction members carried by the frame, evenly distributed around the axis of said first ring, the first means for applying a torque comprise N traction members carried by the frame, evenly distributed around the axis of said first ring.

10. The installation according to claim 8, wherein the first torque application means may comprise at least one first traction member and at least one second traction member carried by the frame and configured to exert a traction force at two diametrically opposite points of the first ring and in opposite directions, the second torque application means comprising at least one third traction member and at least one fourth traction member carried by the frame and configured to exert a traction force at two diametrically opposite points of the second ring and in opposite directions.

11. The installation according to claim 9, in which each traction member is connected to the ring with which it is associated by a connecting rod articulated in rotation at one end to the ring in question and articulated in rotation at the opposite end to a movable part of said traction member.

12. The installation according to claim 9, in which the traction members are cylinders.

13. The installation according to claim 8, wherein the first ring and the second ring comprise on their inner faces axial splines capable of cooperating with corresponding axial splines formed on radially outer faces of annular flanges of the first and second crowns.

14. The installation according to, wherein the frame comprises means for preventing rotation about the longitudinal axis of the gearbox, the inner sun gear and the planet carrier.

15. The method according to claim 1, which includes an intermediate step between steps a) and b) comprising locking the inner sun gear, planet gears and planet carrier against rotation about the longitudinal axis.

16. The installation according to claim 8, wherein the reduction gear has an epicyclic or planetary configuration.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0038] FIG. 1 is a radial sectional diagram of a gearbox;

[0039] FIG. 2 is a longitudinal diagram of a turbomachine;

[0040] FIG. 3 is a schematic perspective view of an reduction gear of an epicyclic type deprived of an outer sun gear;

[0041] FIG. 4 is a schematic sectional view of the outer sun gear comprising two crowns to be joined together and surrounding planet gears with two toothings;

[0042] FIGS. 5a and 5b are schematic perspective and cross-sectional views of the reduction gear in FIG. 3 mounted on an outer sun gear mounting facility;

[0043] FIGS. 6a and 6b are schematic perspective and front views of the installation in FIGS. 5a and 5b also showing a gantry supporting application means intended to allow the application of a torque to the outer planetary gear;

[0044] FIGS. 7 and 8 are schematic sectional views illustrating the assembly steps of the outer planetary gear of the reduction gear.

DETAILED DESCRIPTION

[0045] FIG. 1 schematically illustrates the structure of an epicyclic or planetary reduction gear. This type of reduction gear 10 typically includes an inner sun gear planetary 12 (also called central pinion or solar gear) and an outer sun gear 14, the two sun gears being coaxial. The inner sun gear 12 can be rotated about its X axis, the outer sun gear 14 can be fixed, or rotationally coupled to a propeller as in the case of a turboprop or a blower wheel as in the case of a double flow turbojet. The reduction gear 10 further comprises planet gears or planet pinions 16 mounted to be movable in rotation on pivot pins 18 of a planet carrier 20. Each planet gear 16 meshes with both the inner sun gear 12 and with the outer sun gear 14. The planet carrier 20 is fixed or able to pivot pin about the axis X of the inner sun gear 12 and the outer sun gear 14. The inlet can be formed by the sun gear 12 and the outlet by the planet gear carrier 20.

[0046] In another example, the carrier 20 can be fixed or rotatably coupled to a propeller of a turboprop or a blower wheel of a dual-flow turbojet engine.

[0047] FIG. 2 shows schematically a turbomachine 22 comprising from upstream to downstream a blower 24, a low pressure compressor 28a and a high pressure compressor 28b, a combustion chamber 29, a high pressure turbine 26a and a low pressure turbine 26b. The high-pressure turbine rotor drives the high-pressure compressor rotor and the low-pressure turbine rotor drives the low-pressure compressor rotor, which is connected to the blower. A reduction gear 10 is interposed between the blower rotor and the low-pressure compressor rotor to reduce the rotational speed of blower 24, depending on the rotational speed of the low-pressure turbine rotor.

[0048] The central pinion, or inner sun gear 12, surrounds and is then fixed in rotation to the shaft 32 of the low-pressure compressor 28, as illustrated for example in FIGS. 1 and 2. In particular, the reduction gear 10 can be mounted in a radially formed annular chamber inside a low-pressure compressor 28a arranged downstream of the blower impeller 24 and upstream of a high-pressure compressor 28b, as shown in FIG. 2.

[0049] FIG. 3 shows the previously detailed reduction gear 10 in perspective, the outer sun gear not being shown. We can thus distinguish the planet carrier 20 carrying planet gears 16, as well as the toothings of the planet gears 16a and 16b. As can also be seen in FIG. 4, the outer sun gear 14 consists of a first crown 14a and a second crown 14b. The planet gears 16 each comprise a first toothing 16a and a second toothing 16b which are axially spaced along the longitudinal X axis. The first toothing 16a of the planet gears 16 mesh with a first toothing 34 of the first crown 14a of the outer sun gear 14 and the second toothing 16b of the planet gears 16 mesh with a second toothing 36 of the second crown 14b. As can be seen, the first toothing 34 of the first crown 14a and the second toothing 36 of the second crown 14a are inclined in relation to the longitudinal X axis of reduction gear 10. More specifically, the first 34 and second 36 toothing of crowns 14a, 14b are inclined in a herringbone configuration, which increases the contact area between toothings 16a, 16b of planet gears 16 and toothing 34, 36 of crowns 14a, 14b. In order to obtain such a mounting, it is easy to understand that the first crown 14a and the second crown 14b must be mounted along the longitudinal X-axis and in opposite directions. It should also be noted that the first crown 14a comprises a radial annular flange 38 intended to be applied and fixed, by bolting for example, to a second radial annular flange 40 of the second crown 14b. The connection of these two radial annular flanges 38, 40 can also be used to fix one or more other flanges, allowing for example the crown holder 41 to be fixed together with the said radial annular flanges 38, 40.

[0050] As indicated above, the first crown 14a and the second crown 14b are mounted, for example, by centring the second crown 14b on the first crown 14a. However, this assembly leads to an overloading of one of the first 16a and second 16b toothings of the planet gears 16, which is undesirable.

[0051] An installation and a procedure is thus proposed for the optimal mounting and alignment of the first crown 14a and the second crown 14b around the toothings 16a and 16b of planet gears 16.

[0052] FIGS. 5a, 5b, 6a and 6b represent an installation 42 according to this document, the installation comprising a frame 44 forming means for supporting the reduction gear and comprising a first support member 46, a second support member 48 and a third support member 50 carried by a base 52 of the frame 44. The first unit 46 and the second unit 48 are used to hold the planet carrier in position. For example, in the case of a planet carrier with an epicyclic configuration, these units 46, 48, 50 comprise a tubular body 51 extending along the longitudinal axis X of the reduction gear. The first unit 46 and the second unit 48 each comprise an opening for receiving the tubular body 51 connected to the planet carrier. The third support unit 50 comprises an arm 55 extending along the longitudinal axis X of reduction gear 10 when supported by frame 44. The first support unit 46 has an opening whose inner periphery includes means for preventing rotation such as axial splines for example, cooperating with splines 53 of the tubular body 51. The arm 55 has a fastening device with the inner sun gear 12, e.g. via splines 54 cooperating with splines on the radially inner side of the inner sun gear 12. Thus, the inner sun gear 12, the planet gears and the planet carrier are locked in rotation around the X axis on arm 55. The splines on the radially inner face of inner sun gear 12 are pre-existing and allow the inner sun gear 12 to be coupled in rotation with shaft 32 of the compressor. A nut can be screwed onto the free end of arm 55 and tightened via the end of the planet carrier.

[0053] Frame 44 also includes a gantry 56, shown only in FIGS. 6a and 6b and carried by base 52. This gantry 56 has a substantially rectangular shape formed by two first vertical uprights 58a, 58b and two second horizontal uprights 60a, 60b. In one particular embodiment, the horizontal upright 60b could be confused with the base 52.

[0054] The gantry 56 carries a first ring 62 and a second ring 64 axially spaced from each other and each having an axis substantially aligned with the longitudinal X-axis of the gearbox without being purely coaxial therewith. The first ring 62 is connected to first means for applying a torque 66 to the first ring 62 carried by the gantry 56 via first connecting means 68 allowing a degree of freedom of the first ring 62 in rotation about the longitudinal X axis. Similarly, the second ring 64 is connected to the gantry 56 to second torque application means 70 to the second ring 64 via second connecting means 72 allowing a degree of freedom of the second ring 64 in rotation around the longitudinal X axis. As can be seen, the first connecting means 68 and the second connecting means 72 are independent of each other, thus allowing the first ring 62 and the second ring 64 to be linked independently to the portal 56.

[0055] The first means of applying torque 66 comprises a first traction member 74 and a second traction member 76 carried by the gantry 56 of frame 44. The first traction member 74 is carried by a horizontal upright 60a of gantry 56 and the second traction member 76 is carried by the horizontal upright 60b opposite gantry 56. The second means of applying torque 70 comprises a third traction member 78 and a fourth traction member 80 carried by the gantry 56 of frame 44. The third traction member 78 is carried by a vertical upright 58a of gantry 56 and the fourth traction member 80 is carried by the vertical upright 58b opposite gantry 56. In a particular configuration, the traction members 74, 76, 78, 80 are cylinders each comprising a cylinder body 74a, 76a, 78a, 80a and a rod 74b, 76b, 78b, 80b translationally mounted in the cylinder body 74a, 76a, 78a, 80a.

[0056] A connecting rod 82, 84, 86, 88 connects one end of each cylinder rod 74a, 76a, 78a, 80a to the periphery of a ring 62, 64. In particular, the first traction member 74 is connected by a first connecting rod 86 to the first ring 62 and the second traction member 76 is connected by a second connecting rod 82 to the first ring 62. The third traction member 78 is connected by a third connecting rod 80 to the second ring 64 and the fourth traction member 80 is connected by a fourth connecting rod 88 to the second ring 64.

[0057] As shown in FIGS. 6a and 6b, each connecting rod 82, 84, 86, 88 is rotatably hinged at one end to a ring 62, 64 and at its opposite end to the cylinder rod 74b, 76b, 78b, 80b. In particular, it is observed that the first link 82 and the second link 86, which are connected to the first ring 62, are oriented substantially parallel and extend in opposite directions from a first direction 90 substantially perpendicular to the longitudinal X axis and from opposite ends of a diameter of the first ring 62. Also, the third link 84 and the fourth link 88, which are connected to the second ring 64, are oriented substantially parallel and extend in opposite directions from a second direction 92 substantially perpendicular to the longitudinal X axis and from opposite ends of a diameter of the second ring 64. Note that the first direction 90 is perpendicular to the second direction 92, which in particular saves space for mounting the torque application means on the gantry.

[0058] The first ring 62 comprises first means of coupling in rotation with the first crown 14a, these first means of coupling cooperating with complementary means carried by the first crown. Also, the second ring 64 comprises second means of coupling in rotation with the second crown 14b, these second means of coupling cooperating with complementary means carried by the second crown 14b. In a practical embodiment, the first coupling means of the first ring 62 and the second coupling means of the second ring 64 are splines 94 which cooperate with splines 96 of the radially outer surfaces of the first crown 14a and the second crown 14b.

[0059] To mount the first crown 14a and the second crown 14b in reduction gear 10, the installation as described above is used. It is understood that another installation could be used, however.

[0060] Thus, in a first step, the assembly consisting of the inner sun gear 12, the planet gears 16 and the planet carrier 20 is mounted on frame 44 in the indicated position as shown and described in FIGS. 5a and 5b. In a second step, the first crown 14a is mounted around the planet gears 16 so that the first toothing 34 of the first crown 14a meshes with the first toothing 16a of the planet gears 16. Also, in this second step, the second crown 14b is mounted around the planet gears 16 so that the second toothing 36 of the second crown 14b meshes with the second toothing 16b of the planet gears 16. In a third step, the first ring 62 is mounted in engagement with the radially outer periphery of the first flange 38 and the second ring 64 is mounted in engagement with the radially outer periphery of the second flange 40. In a fourth step, a first torque is simultaneously and independently applied to the first ring 62 centred on the axis of the first ring 14a and a second torque is applied to the second ring 14b centred on the axis of the second ring 14b, the first torque and the second torque having identical values. The first torque and the second torque are applied in the same direction of rotation around the axes of the first and second crowns. The application of the torques independently to each of the first ring 62 and the second ring 64 is made possible by the use of the linkage means as described above. In a fifth step, the first 38 and second 40 flanges are tightened together by bolting 96 into holes in the first and second flanges.

[0061] In another embodiment, the engagement of the first ring 62 with flange 38 of the first ring 14a, and of the second ring 64 with flange 40 of the second ring 14b, can be achieved by systems other than external radial engagements, such as tie rods passing through the screw holes of flanges 38 and 40.

[0062] In a process embodiment, the torque applied to a value which corresponds to the torque undergone by the reduction gear during a given phase of use, this torque being, for example, greater than 10 N. It is understood that the torque must be non-zero.