阅读说明：本技术 用于带有周转齿轮系的减速单元的笼式行星架 (Cage-type planet carrier for reduction unit with epicyclic gear train ) 是由 让-查尔斯·米歇尔·皮埃尔·迪乔凡尼 亚力克西斯·克劳德·米歇尔·东贝克 于 2018-04-26 设计创作，主要内容包括：用于涡轮发动机的带有周转齿轮系的减速单元的行星架(130),所述行星架包括限定内部空间的笼(134),该内部空间用于组装具有旋转轴线A的中心太阳齿轮(151)和围绕轴线A设置并且与所述太阳齿轮啮合的一环形排的行星齿轮(150),所述笼包括以所述轴线A为中心的两个基本平行的环形壁(136,138)和将所述环形壁连接到所述环形壁的外周缘的圆筒形壁(140),所述环形壁中的第一环形壁(136)连接到基本圆柱形的主体(142),其特征在于,所述环形壁中的第二环形壁(138)与润滑装置(158)形成单个部件。(Planet carrier (130) for a reduction unit with epicyclic gear train of a turbine engine, said planet carrier comprising a cage (134) defining an internal space for assembling a central sun gear (151) having an axis of rotation a and an annular row of planet gears (150) arranged about said axis a and meshing with said sun gear, said cage comprising two substantially parallel annular walls (136, 138) centred on said axis a and a cylindrical wall (140) connecting said annular walls to the outer periphery of said annular walls, a first (136) of said annular walls being connected to a substantially cylindrical body (142), characterized in that a second (138) of said annular walls forms a single component with a lubricating device (158).)

1. Planet carrier (130) for a reduction unit with epicyclic gear train of a turbine engine, comprising a cage (134) defining an internal space for mounting a central sun gear (151) having an axis of rotation a and an annular row of planet gears (150) arranged around said axis a and meshing with said sun gear, said sun gear comprising means for coupling to a first shaft, said cage comprising two parallel annular walls (136, 138) centred on said axis a and a cylindrical wall (140) connecting said annular walls at their outer peripheries, a first (136) of said annular walls being connected to a cylindrical body (142) comprising means for coupling to a second shaft, characterized in that a second (138) of said annular walls is associated with lubricating means (158, 160, 162) together formed by a single piece, said lubricating device comprising an annular groove (158) for receiving oil, formed in said second wall and extending to the periphery of a central opening (144) centred on the axis a of said second wall, said annular groove opening radially inwards.

2. The planet carrier (130) according to claim 1, wherein the lubrication device (158, 160, 162) is formed in at least one axial excess thickness (165, 166, 168) of the second annular wall (138).

3. The planet carrier (130) according to any of the preceding claims, wherein the groove (158) is in fluid communication with a channel (160) and a duct (162) formed in the second wall (138) and extending radially outward therefrom.

4. Planet carrier (130) according to the preceding claim, wherein a radially outer end of the channel (160) is connected to a longitudinal end of a lubricant nozzle (172) extending substantially parallel to the axis a.

5. Planet carrier (130) according to claim 3 or 4, wherein the radially outer end of the conduit (162) is connected to the inner radial end of a conduit (178) for supplying lubricant to the planet gears (150).

6. Planet carrier (130) according to the preceding claim, wherein each of the ducts (178) is mounted in a radial hole (180) of the second wall (138) and passes through a shaft (148) for supporting one of the planet gears (150).

7. Planet carrier (130) according to the preceding claim, wherein each of the ducts (178) comprises a longitudinal slot (184) or a set of holes communicating with the inner cavity (152) of the support shaft (148).

8. Planet carrier (130) according to claim 6 or 7, wherein each of the ducts (178) passes through a cover (189) provided and fixed on the second wall (138), which supports a longitudinal end of the support shaft (148).

9. The planet carrier (130) according to the preceding claim, wherein substantially radial fins (164) are arranged in the grooves (158).

10. Aircraft turbine engine, characterized in that it comprises a reduction unit with an epicyclic gear train, the planet carrier (130) of which is a planet carrier as defined in any one of the preceding claims.

11. Turbine engine according to the preceding claim, comprising a lubricant supply device for supplying lubricant to the groove (158), the lubricant supply device comprising a series of injectors (190) arranged around the axis (a) and passing through the opening (144).

12. The turbine engine of the preceding claim, wherein the injector (190) is configured to inject lubricant directly into the groove (158) radially inward.

Technical Field

The invention relates in particular to a planet carrier for a reduction unit with an epicyclic gear train, the planet carrier comprising a cage for receiving the sun and planet gears of the reduction gear.

Background

Disclosure of Invention

According to the invention, this object is achieved by a planet carrier for a reduction unit with epicyclic gear train for a turbine engine, said planet carrier comprising a cage defining an internal space for mounting a central sun gear having an axis of rotation a and an annular row of planet gears arranged about said axis a and meshing with said sun gear, said sun gear comprising means for coupling to a first shaft, said cage comprising two substantially parallel annular walls centred on said axis a and a cylindrical wall connecting said annular walls to the outer periphery of the annular walls, a first of said annular walls being connected to a substantially cylindrical body comprising means for coupling to a second shaft, characterized in that a second of said annular walls is formed in a single piece with lubricating means comprising an annular groove for receiving oil, the annular groove is formed in the second wall and extends to the periphery of a central opening centered on the axis A of the second wall, the annular groove being open radially inwardly.

The direct integration of the lubrication means in the cage makes it possible to eliminate the impeller of the prior art and therefore reduce the axial volume of the planet carrier.

The planet carrier according to the invention may comprise one or more of the following features taken alone or in combination with each other:

-said lubricating means are formed in at least one axial excess thickness of said second annular wall;

-the groove is in fluid communication with a channel and a duct formed in the second wall and extending radially outwardly from the groove;

-the radially outer end of the passage is connected to the longitudinal end of a lubricant nozzle extending substantially parallel to the axis a;

the radially outer end of this conduit is connected to the inner radial end of the lubricant supply conduit of the planet carrier;

-each of said conduits is mounted in a radial hole of said second wall and passes through a shaft for supporting one of said planet gears;

-each of said catheters comprises a longitudinal slot or a set of holes communicating with the lumen of the support shaft;

-each of said conduits passes through a cover provided and fixed on said second wall, said cover supporting a longitudinal end of said support shaft; and

-a substantially radial fin is arranged in the groove; the fins assist in radially flowing lubricant from the inner periphery of the groove to the bottom wall of the groove.

The invention also relates to a turbine engine comprising a reduction unit with an epicyclic gear train, the planet carrier of which is as described above.

The turbine engine may comprise a lubricant supply for supplying lubricant to said grooves, the lubricant supply comprising a series of injectors arranged about said axis a and passing through said openings. The injector is preferably configured to inject lubricant directly into the groove radially outward.

Drawings

Further characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention, with reference to the attached drawings, in which:

figure 1 is a schematic perspective view of a cantilevered impeller planet carrier of the prior art,

figure 2 is a schematic perspective view of a cage-type planet carrier,

figure 3 is a schematic perspective view of a cage-type planet carrier according to the invention,

figures 4 and 5 are schematic partial axial cross-sectional views of the planet carrier of figure 2;

figure 6 is a schematic perspective view of the supply pipe of the planet carrier of figure 2; and

fig. 7 is another schematic partial axial cross-section of the planet carrier of fig. 2 and of the device for supplying the lubricant of the lubrication device of the planet carrier.

Detailed Description

Fig. 1 and 2 have been described above.

Figure 3 shows a planet carrier 130 with reduction gears of an epicyclic gear train for an aircraft turbine engine. The planet carrier 130 is a cage 134 planet carrier comprising two coaxial annular walls 136, 138 and connected to the periphery of the annular walls by a cylindrical wall 140.

The annular wall 136 is secured to a partially visible substantially cylindrical body 142 that includes an engagement means for engaging a shaft, such as a fan shaft of a turbine engine. The coupling means are for example longitudinal slots of the type visible in fig. 1.

In the example shown, the cylindrical wall 140 is perforated and comprises through holes 143 in the radial direction.

The wall 138 comprises a central opening 144 centred on the axis a and a series of orifices 146 regularly distributed about the axis a, the opening 144 and the orifices 146 passing in an axial direction.

The aperture 146 is used to mount a rotating shaft 148 of a planetary gear 150, as shown schematically in fig. 7. Shaft 148 is mounted in cage 134 in axial translation parallel to axis a and through aperture 146. The shaft 148 is fixed at its longitudinal ends to the walls 136, 138, respectively. As can be seen in fig. 4 (the cross-section of fig. 4 axially intersects the shaft 148), the shaft 148 is fixed to a slide bearing 149, and a planetary gear 150 is mounted around the slide bearing 149. The shaft 148 is hollow and includes a cylindrical inner cavity 152. The shaft 148 and the bearing 149 are crossed by at least one radial conduit 154, which at its radially inner end opens into the cavity 152 and at its radially outer end into a longitudinal ridge 156 of the periphery of the bearing (fig. 3 and 4).

Although this is not visible, considering that the planet gears mesh with an outer ring gear of the reduction gear intended to surround the cage 134, the planet gears 150 mounted on the shaft 148 are rotated so that the outer peripheries of the planet gears partially pass through the through holes 143.

The planet gears 150 mesh with a sun gear 151, the sun gear 151 including an internal linear slot for coupling to another shaft (such as a turbine shaft).

The central opening 144 is externally bounded by an annular portion of the wall 138 having an excess thickness in which an annular groove 158 is formed. The groove 158 extends about the axis a and opens radially inward. The radially outer bottom wall of the groove 158 comprises an orifice in fluid communication with the radial channel 160 on the one hand and with the radial duct 162 on the other hand.

Within the groove 158, the fins 164 may be substantially radially disposed to facilitate radial flow of lubricating oil from the inner periphery of the groove to the bottom wall of the groove and the orifices described above.

In the example shown, the number of channels 160 is equal to the number of conduits 162, and the number of conduits 162 is equal to the number of shafts 148 and the number of planetary gears 150. The number is here five. The channels 160 are regularly distributed about the axis a and the ducts 162 are regularly distributed about the axis a, each duct 162 being arranged between two adjacent channels 160. The conduits and channels are formed in the excess thickness 165, 166 of the wall 138. Excess thickness 165 extends radially outward from excess thickness 168, and conduit 160 is formed in excess thickness 165 and groove 158 is formed in excess thickness 168. Excess thickness 166 extends radially between excess thickness 168 and a ledge 170 of wall 138, with conduit 162 formed in excess thickness 166, and aperture 146 formed in ledge 170.

Each of the channels 160 communicates at its radially outer end with a longitudinal end of a tubular nozzle 172, the tubular nozzle 172 being visible in particular in fig. 4 and 5. The nozzle 172 has an elongated shape and extends parallel to the axis a. There are five nozzles and the nozzles are regularly distributed about the axis a, each nozzle being arranged between two adjacent shafts 148. The nozzle is mounted in axial translation through a through hole in the wall 138. The nozzles each include a longitudinal lumen 174, with one longitudinal end of the longitudinal lumen 174 in fluid communication with the channel 160. Each nozzle 172 further includes substantially radial orifices 176, the orifices 176 being distributed over the length of each nozzle and opening into the cavity 174. The lubricant brought into the nozzle 172 by the channel 160 is intended to be sprayed on the gear transmission of the planet gears 150 and the sun gear 151 in the operating state (see also fig. 5 and the arrows of fig. 7).

Each of the conduits 162 communicates at its radially outer end with a longitudinal end of a supply conduit 178, the supply conduit 178 being visible in fig. 4. The conduit 178 has an elongated shape and extends substantially radially with respect to the axis a. There are five conduits and the conduits are regularly distributed around the axis a by being engaged each in a radial hole 180, the radial holes 180 passing through the boss 170 and the respective excess thickness 166 of the wall 138. The holes 180 open at their radially outer ends to the outer periphery of the wall 138, and the conduits 178 are mounted in these holes by radial translation from the outside inwards until their inner radial ends are in fluid communication with the radially outer ends of the ducts 158, as can be seen in fig. 4. Thus, the screw 182 is screwed into the wall 138, and in particular into the threaded aperture of the boss 170 to secure the conduit 178 in the hole 180. The screws 182 may pass through corresponding through holes 183 of the conduit 178 (fig. 4 and 6). In a variant, the screws 182 may be replaced by dowel pins or pins.

Fig. 6 shows a catheter 178. The catheter 178 has an elongated shape and includes a longitudinal lumen 184, one longitudinal end of the longitudinal lumen 184 being axially open and intended to be in fluid communication with the conduit 162. The other longitudinal end of the conduit is closed. The conduit includes a longitudinal slot 186 substantially in the middle of the conduit, the longitudinal slot 186 communicating with the lumen 184. In a variation, the slot 186 may be replaced with a set of holes.

An annular gasket 188 is advantageously disposed around the conduit. One or more of the first washers may be located at the open longitudinal end of the conduit and intended to engage the wall 138, and the other washers may be located on either side of the slot 186 (or bore) and intended to engage the respective shaft 148 (see fig. 4). The slot 186 (or hole) is intended to open into the cavity 152 of the shaft 148, allowing for the supply of lubricant to the shaft 148 and the bearing 149. The lubricant brought into the conduit 178 by the duct 162 is intended to be injected into the cavity 152 and then to flow through the duct 154 up to the periphery of the bearing 149 (see arrows in fig. 4).

In the example shown, each conduit 178 also passes through an annular cover 189 on the side opposite the planet gears 150, which annular cover 189 is returned to and secured to the wall 138, for example by screws. Each cap 189 covers a respective boss 170 of the wall 138 and is intended to be centered on a respective shaft 148 in the aperture 146 of the wall 138.

Fig. 7 shows a device for supplying lubricant to groove 158, which device comprises a series of injectors 190 (for example five injectors), which series of injectors 190 are arranged about axis a and pass through openings 144 of wall 138 of cage 134. Injector 190 is carried by the stator and injects lubricant directly radially outward into groove 158, which then flows into passage 160 and conduit 162, as described above.

Compared with the prior art, the invention has a plurality of advantages: the axial volume is reduced; the perforated part (impeller) which is difficult to machine is removed due to the cage, which is easier to machine by turning; less static uncertainty during installation; the fretting wear problem in the impeller is avoided; the nozzle can be closer to the sun gear; the rigidity of the planet carrier is increased; shorter and lighter nozzles (less dynamic problems), etc.