OIL NOZZLE FOR AN AIRCRAFT TURBOMACHINE REDUCTION GEAR

Abstract

Oil nozzle (26) for an epicyclic reduction gear (10) of an aircraft turbomachine (1), comprising a body (28) and a fixing lug (30) which is located at a first longitudinal end (28a) of the body (28) and which is formed in one piece with the body (28), the body (28) comprising an internal cavity (32) and oil projection orifices (34) in fluid communication with said cavity (32), characterized in that the internal cavity (34) comprises two portions, a first portion (36) of the cavity (34) which has a frustoconical shape and which is located at the first end (28a) of the body (28), and a second portion (38) of the cavity (32) which has a cylindrical shape with a constant diameter (D) and which extends from the smallest diameter of the first portion (36) to a second closed end (28b) of the body (28). Figure for abstract: Figure 3

Description

Title of the invention: OIL NOZZLE FOR AN AIRCRAFT TURBOMACHINE REDUCER Technical field of the invention

[0001] The present invention relates to an oil nozzle for a reducer, in particular an epicyclic reducer, of an aircraft turbomachine, as well as a reducer and a turbomachine comprising one or more of these nozzles. Technical background

[0002] The state of the art includes in particular documents FR-A1-3 069 300, FRAI-3 069 301 and FR-A-3 099 220.

[0003] The role of a mechanical reducer is to modify the speed and torque ratio between the input axis and the output axis of a mechanical system.

[0004] New generations of dual-flow turbomachines, particularly those with a very high bypass ratio, include a mechanical reducer to drive the shaft of a fan. Usually, the reducer aims to transform the so-called fast rotation speed of the shaft of a power turbine into a slower rotation speed for the shaft driving the fan.

[0005] Such a reducer comprises a central pinion, called a sun gear, a crown gear and pinions called satellite gears, which are engaged between the sun gear and the crown gear. The satellite gears are held by a frame called a planet carrier. The sun gear, the crown gear and the planet carrier are planet gears because their axes of revolution coincide with the longitudinal axis X of the turbomachine. The satellite gears each have a different axis of revolution equally distributed over the same operating diameter around the axis of the planet gears. These axes are parallel to the longitudinal axis X.

[0006] There are several gearbox architectures. In the state of the art of dual-flow turbomachines, the gearboxes are of the planetary or epicyclic type. In other similar applications, there are so-called differential or compound architectures. - On a planetary gearbox, the planet carrier is fixed and the crown constitutes the output shaft of the device which rotates in the opposite direction to the solar. - On an epicyclic reducer, the crown is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the solar. - On a differential reducer, no element is fixed in rotation. The crown rotates in the opposite direction to the sun and the planet carrier.

[0007] The reducers can be composed of one or more meshing stages. This meshing is ensured in different ways such as by contact, by friction or even by magnetic fields.

[0008] There are several types of contact meshing such as with straight, helical or herringbone teeth.

[0009] One of the major challenges with these reducers is the lubrication of the various components that make them up.

[0010] One of the particularities of epicyclic reducers is the presence of fixed nozzles in the reference frame of the planet carrier, that is to say nozzles rotating at the speed of the planet carrier.

[0011] The main problem is the resistance of the nozzles under centrifugal force with a design that can be manufactured at reduced cost, that is to say a less complex design making assembly easier and reducing its duration.

[0012] Concerning the holding of the nozzles, the nozzles are subjected to a significant centrifugal force. Indeed, under the effect of the rotation of the planet carrier and its own mass, the nozzles must hold mechanically over a significant number of cycles. Furthermore, the nozzles must as much as possible limit the pressure losses before the projection of the oil.

[0013] A nozzle for an epicyclic reducer is generally fixed to a planet carrier by means of a lubricating impeller. A nozzle conventionally comprises a body having an elongated shape along an axis, and a fixing lug which is located at a first longitudinal end of the body and which is formed in one piece with the body. The fixing lug is used to fix and secure in rotation the nozzle to the impeller and therefore to the planet carrier, by means of a screw or a nut.

[0014] The nozzle body comprises an internal cavity which extends along the axis of the body. This internal cavity opens at the first end of the body and is closed at a second longitudinal end of the body, opposite the first end. The cavity is generally closed by a plug attached and fixed to the body.

[0015] The body further comprises oil projection orifices in fluid communication with the cavity, in order to project oil onto the gears of the reducer.

[0016] The present invention proposes an improvement to the current technique which makes it possible to respond in a simple, effective and economical manner to the aforementioned needs. Summary of the invention

[0017] The invention relates to an oil nozzle for a reducer, in particular an epicyclic gearbox, of an aircraft turbomachine, this nozzle comprising a body having an elongated shape along an axis, and a fixing lug which is located at a first longitudinal end of the body and which is formed in a single piece with the body, the body comprising an internal cavity which extends along the axis, this internal cavity opening at said first end and being closed at a second longitudinal end of the body, opposite the first end, the body further comprising oil projection orifices in fluid communication with said cavity, characterized in that the internal cavity comprises two coaxial portions, a first portion of the cavity which has a frustoconical shape and which is located at the first end of the body, and a second portion of the cavity which has a cylindrical shape with constant diameter and which extends from the smallest diameter of the first portion to the second closed end of the body which is formed in one piece with the rest of the body.

[0018] The nozzle, and in particular its internal part, is thus optimized both to simplify the nozzle and facilitate its manufacture, and on the other hand to limit mechanical constraints and pressure losses during operation.

[0019] More specifically, concerning the inner part of the nozzle and its body, its internal cavity has been optimized in order to have a single diameter over the length of its second portion which represents the largest portion of the cavity. Having a single diameter has made it possible to eliminate the plug at the end of the nozzle. The presence of this plug increased the mass, via the presence of the plug and the location for it, thereby increasing the load on the nozzle fixing lug via centrifugal force. It should also be noted that the elimination of a plug at the end makes it possible to avoid a manual gluing operation and polymerization baking, allowing simpler and faster manufacturing. The uniform diameter of the inner part of the nozzle and its closed end therefore allow for improved performance of the nozzle under centrifugal force.Additionally, the inner portion of the nozzle has a first inlet portion or section having a truncated cone geometry. This inlet section is positioned opposite the closed end of the nozzle.

[0020] The uniform diameter of the inner part of the nozzle, its closed end and its inlet section allow a reduction in the hydraulic pressure losses of the nozzle. In other words, the inner part of the nozzle is optimized so as to increase the efficiency of the hydraulic elements upstream and downstream of the nozzle. For example, the technical elements of the nozzle described above allow the transition from a “pipe chain” architecture to a “pressure tank” architecture to which the nozzle is connected. The truncated cone geometry allows the oil to be channeled from the pressure tank, external to the nozzle, the single diameter allowing the pressure losses in the nozzle to be reduced and the closed end allowing its mass to be reduced as explained above.

[0021] The solution proposed below is compatible with a single-stage or multi-stage reducer. It is also compatible with a so-called epicyclic, planetary or differential reducer. It is also compatible with straight, helical, or spiral teeth. coïdal or chevron. It is also compatible with any type of planet carrier, whether monobloc or cage and cage carrier type. It is also compatible with any type of satellite bearing, whether it is composed of a rolling element, a hydrodynamic bearing, etc.

[0022] The nozzle according to the invention may also have one or more of the following optional characteristics, taken alone or in combination with each other: - the body comprises at its second end a bottom wall which closes the cavity and which defines a third portion of the cavity of truncated or conical shape which is coaxial with the first and second portions and the largest diameter of which is located on the side of the second portion of the cavity; - the bottom wall has a thickness which is equal to + / -10% to a thickness of the body along the cavity;

[0023] — the cavity is formed solely by said first and second portions, or by said first, second and third portions; - the body comprises a tubular extension which extends along the axis beyond the fixing lug, this tubular extension comprising said first portion of the cavity and at least one external annular groove for housing a sealing gasket;

[0024] — the internal cavity opens at one axial end of the extension; - the fixing lug is located at an annular excess thickness of the body;

[0025] — apart from the excess thickness, any cross-section of the body is identical and rectangular shape; - the fixing lug is connected to the body by a concave curved connecting fillet; - the fillet has a sectional shape that corresponds to a curve having a polynomial equation of degree 2; the fillet between the leg and the nozzle body is thus optimized to form a connecting parabola. This connecting parabola allows the nozzle to have a homogeneous stress level and a positive margin level; - the polynomial equation of degree 2 is, for example, y = 8.1754x2 - 10.734x + 3.8845; - the body has a general prismatic shape with a rectangular base; concerning the external part of the nozzle and its body, in order to resolve the problem of holding the nozzles, the shape of the nozzles has been optimized to have the best compromise between mass, mechanical strength and bending stiffness; the prismatic shape ensures better mechanical strength of the nozzle body and also limits the bending of the nozzle which can lead to a drop targeting performance. This prismatic section is not square; the section is deliberately longer, for example in the radial direction than in the tangential direction (relative to the rotation of the planet carrier). The objective is to keep the material to a minimum in the tangential direction (the quantity of material between the pipe and the outside of the nozzle) and to deliberately have more material in the radial direction (to increase the rigidity of the part to bending stress by centrifugation); finally, from a manufacturability point of view, the technical elements of the nozzle described above also allow for an improvement. More precisely, making a prismatic shape on the outside allows for a reduction in complexity and manufacturing time.Additionally, previous nozzle designs had local overthicknesses at the orifices, thus resulting in additional operations which are no longer necessary with nozzles according to the present invention; . - the orifices are all located on the same flat surface of the body, which extends along the axis; - the holes are aligned on the same line parallel to the axis; - the holes and the fixing lug are oriented in the same direction vis- with respect to said axis; still at the level of the external shape of the nozzle, the orientation of the fixing lug is preferably such that it is mainly stressed in traction which is an elementary stress, easy to control. For example, an orientation in the opposite direction (stress in bending) can lead to detachment of the lug. It is then no longer stressed by an elementary stress, and its dimensioning, in particular in fatigue, is more complex to control.

[0026] The present invention also relates to a reducer, in particular an epicyclic reducer, for an aircraft turbomachine, this reducer comprising a sun gear centered on a first axis, a fixed ring extending around the sun gear and the first axis, and satellites meshed with the sun gear and the ring gear and rotatable around second axes parallel to the first axis, the satellites being carried by a planet carrier which is rotatable around the first axis and which carries nozzles as described above. Advantageously, the fixing lug of each of the nozzles is oriented radially towards the first axis. Brief description of the figures

[0027] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:

[0028] [Fig.l] [Fig.l] is a schematic axial sectional view of an aircraft turbomachine,

[0029] [Fig.2] [Fig.2] is an axial sectional view of an epicyclic reducer,

[0030] [Fig.3] [Fig.3] is a schematic perspective view of an oil nozzle according to an embodiment of the invention,

[0031] [Fig.4] [Fig.4] is a partial schematic view in axial section of a reducer comprising the nozzle of [Fig.3],

[0032] [Fig.5] [Fig.5] is an enlarged view of part of [Fig.3],

[0033] [Fig.6] [Fig.6] is a graph with a curve showing the profile of a rac fillet connection of the nozzle according to the invention,

[0034] [Fig.7] [Fig.7] is another view on a larger scale of a part of [Fig.3], and

[0035] [Fig.8] [Fig.8] is a schematic perspective view of a spinning wheel equipped with several nozzles according to the invention. Detailed description of the invention

[0036] [Fig.l] shows a turbomachine 1 which comprises, in a conventional manner, a fan propeller S, a low-pressure compressor 1a, a high-pressure compressor 1b, an annular combustion chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1c and an exhaust nozzle 1h.

[0037] The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 2 and form with it a high-pressure (HP) body. The low-pressure compressor 1a and the low-pressure turbine 1c are connected by a low-pressure shaft 3 and form with it a low-pressure (LP) body.

[0038] The fan propeller S is driven by a fan shaft 4 which is coupled to the LP shaft 3 by means of a reducer 10 with an epicyclic gear train shown here schematically.

[0039] The reducer 10 is positioned in the front part of the turbomachine 1. A fixed structure comprising schematically, here, an upstream part 5a and a downstream part 5b is arranged so as to form an enclosure E1 surrounding the reducer 10.

[0040] This enclosure E1 is here closed upstream by seals at the level of a bearing allowing the fan shaft 4 to pass through, and downstream by seals at the level of the passage of the LP shaft 3.

[0041] With reference to [Fig. 2], the reducer 10 comprises a crown 14 which is fixed by means of a crown carrier (not shown) to the fixed structure 5a, 5b with flexible means arranged to enable it to follow the possible movements of the fan shaft 4, in certain cases of degraded operation for example. In a planetary architecture, the crown carrier is composed of a more or less flexible part which drives the crown and a part held by bearings or bearings and on which the blower is mounted. These fixing means are known to those skilled in the art and are not detailed here. A brief description can be found for example in FR-A1-2 987 416.

[0042] The reducer 10 engages on the one hand on the LP shaft 3 via splines 7 which drive a planetary or sun gear pinion 11, and on the other hand on the fan shaft 4 which is attached to a planet carrier 13. Conventionally, the sun 11, whose axis of rotation X coincides with that of the turbomachine 1, drives a series of planet gears or planets 12, which are distributed regularly on the circumference of the reducer 10. The number of planets 12 is generally defined between three and seven.

[0043] The satellites 12 also rotate around the axis X of the turbomachine 1 except in the case of a planetary where they rotate only around their axes of revolution, by meshing with internal teeth of the crown 14, which is fixed to a stator of the turbomachine 1 by means of flanges 20 in the case of an epicyclic or fixed to a rotor of the turbomachine in the case of a planetary.

[0044] Each of the satellites 12 rotates freely around a satellite axis / bearing 16 connected to the planet carrier 13, using a bearing which can be smooth, as shown in [Fig.2], or a rolling element bearing (ball or roller bearings).

[0045] The rotation of the satellites 12 around their satellite axes 16, due to the cooperation of their pinions with the teeth of the crown 14, causes the rotation of the planet carrier 13 around the axis X, and consequently that of the fan shaft 4 which is connected to it, at a rotation speed which is lower than that of the LP shaft 3.

[0046] [Fig. 2] shows the routing of the oil to the reducer 10 and its path inside it. Arrows show in [Fig. 2] the path followed by the oil from, in this example, a buffer tank linked to the fixed structure of the turbomachine 1, to the pinions and bearings to be lubricated.

[0047] The lubrication device comprises in particular a first part linked to the fixed structure and delivering the oil to the rotating parts of the reducer 10, and a wheel 22 rotating with the planet carrier 13 and receiving this oil in the case of an epicyclic.

[0048] The lubrication device further comprises an oil distributor 24 for supplying oil to the satellite axes 16, and oil nozzles 26, the distributor and the nozzles 26 being supplied with oil by the impeller 22.

[0049] Figures 3 to 8 illustrate an embodiment of a nozzle 26 according to the invention.

[0050] With reference to Figures 3 and 4, the nozzle 26 comprises a body 28 having a shape elongated along an axis Y, and a fixing lug 30 which is located at a first longitudinal end 28a of the body 28 and which is formed in one piece with the body 28.

[0051] The body 28 comprises an internal cavity 32 which extends along the Y axis. This internal cavity 32 opens at the first end 28a of the body 28, preferably axially, and is closed at a second longitudinal end 28b of the body 28, opposite the first end 28a.

[0052] The body 28 further comprises oil projection orifices 34 in fluid communication with the cavity 32.

[0053] The particularity of the invention lies in the fact that the internal cavity 32 has a simplified shape compared to the prior art and comprises two adjacent portions 36, 38.

[0054] The first portion 36 or inlet portion of the cavity 32 has a frustoconical shape and is located at the level of the first end 28a of the body 28.

[0055] The second portion 38 of the cavity 32 has a cylindrical shape with constant diameter D and extends from the smallest diameter of the first portion 36 to the second closed end 28b of the body 28.

[0056] The first portion preferably has a length L1 along the Y axis, which represents less than 10%, and more preferably less than 5%, of the total length Lmax of the nozzle 26 (see [Fig.5]).

[0057] The second portion preferably has a length L2 along the Y axis, which represents more than 85%, and more preferably more than 90%, of the total length Lmax of the nozzle 26. This means that the internal cavity 32 of the nozzle has a constant diameter over more than 85%, or even 90%, of the length of the nozzle 26.

[0058] In the example shown, the body 28 comprises at its second end 28b a bottom wall 40 which closes the cavity 32 and which defines a third portion 40 of the cavity 32 (see [Fig.7]). This bottom wall 40 is formed in a single piece with the rest of the body 28. This third portion 42 preferably has a truncated or conical shape whose largest diameter is located on the side of the second portion 38 of the cavity 32.

[0059] The third portion 42 preferably has a length L3 along the Y axis, which represents less than 5%, and more preferably less than 2%, of the total length Lmax of the nozzle 26.

[0060] The bottom wall 40 preferably has a thickness E2 which is equal to + / -10% of a thickness E1 of the body 28 along the cavity 32. It is therefore understood that the nozzle 26 preferably has a constant thickness over a major part of its length, including at its second closed end 28b.

[0061] The cavity 32 is preferably simplified as much as possible to facilitate its production and can therefore comprise only the first and second portions 36, 38, or the first, second and third portions 36, 38, 42.

[0062] In the example shown, the body 28 of the nozzle 26 comprises an extension tubular 44 which extends along the Y axis beyond the fixing lug 30.

[0063] The first part 36 of the cavity 32 is preferably located or formed in this extension 44 and opens out at an axial end of the latter.

[0064] The extension 44 preferably comprises an external cylindrical centering surface 44a on which an external annular groove 46 is formed for housing a sealing gasket 48 (see [Fig.5]).

[0065] The extension 44 preferably has a length L4 along the Y axis, which represents less than 15%, and more preferably less than 10%, of the total length Lmax of the nozzle 26.

[0066] Figures 3 to 5 show that the fixing lug 30 is located at the level of an annular excess thickness 50 of the body.

[0067] The fixing lug 30 is preferably connected to the body 28 or to this excess thickness 50 by a connecting fillet 52 of concave curved shape, which is better visible in [Fig.5],

[0068] This fillet 52 preferably has a sectional shape which corresponds to a curve having a polynomial equation of degree 2. This sectional shape of the fillet makes it possible to reduce the stresses in this zone. An example of a polynomial equation of degree 2 to which the shape of the fillet can correspond is that illustrated by the curve of [Fig.6] and whose expression is y = 8.1754x2- 10.734x + 3.8845.

[0069] As seen in [Fig. 5], the fixing lug 30 comprises an orifice 54 for the passage of a fixing element of the screw or nut type. The fixing lug comprises two parallel faces onto which this orifice 54 opens, one of these faces being located on the side of the extension 44 and being intended to bear on a complementary face of the planet carrier or the impeller, as illustrated in [Fig. 4]. The extension 44 ensures the centering and correct positioning of the nozzle 26 on the planet carrier or the impeller. During assembly, the hole 54 of the fixing lug 30 is aligned with a corresponding hole in the planet carrier or impeller and the fixing element is tightened, which allows the nozzle 26 to be correctly positioned around its Y axis. In other words, the fixing lug 30 and its hole 54 form a means for positioning the nozzle 26.

[0070] [Fig. 3] further shows that the nozzle 26 preferably has a generally prismatic shape with a rectangular base. This means that the body 26 has a simple geometric shape whose bases are parallel and superimposable, that is to say identical. Apart from the aforementioned excess thickness 50, any cross-section of the body 28 is identical and rectangular in shape. This section is therefore not square, but on the contrary elongated in one direction to limit the stresses undergone by the nozzle 26 in operation.

[0071] The orifices 34 are preferably all located on the same flat surface of the body, which extends along the Y axis. The orifices 54 may be aligned on the same line parallel to the axis. Advantageously, as can be seen in [Fig. 4], the orifices 54 and the fixing lug 30 are oriented in the same direction with respect to the Y axis. This is a radial direction with respect to this Y axis.

[0072] The nozzle 26 according to the invention can be made of metallic material, for example by machining and drilling a block. Concretely, the extension 44 and the connection fillet 52 can be made by conventional turning, the turning of the fixing lug 30 can be made by milling, the prismatic shape of the body 28 can be made by conventional milling.

[0073] The present invention also relates to a reducer, in particular an epicyclic reducer, for an aircraft turbomachine, equipped with nozzles 26 as described above.

[0074] The reducer 10 may be of the type described above with reference to Figures 1 and 2 and is partly visible in [Fig.4]. This reducer 10 comprises a sun gear 11 centered on a first axis X, a fixed ring gear 14 extending around the sun gear 11 and the first axis X, and satellites 12 meshed with the sun gear 11 and the ring gear 14 and rotatable around second axes Z parallel to the first axis X, the satellites being carried by a planet carrier 13 which is rotatable around the first axis X and which carries the nozzles 26.

[0075] As can be seen in [Fig.8], the nozzles 26 can be fixed to the planet carrier 13 by means of a wheel 22 whose operation is described above and illustrated in [Fig.2].

[0076] The impeller 22 has an internal annular groove 22a into which oil is sprayed and is conveyed by conduits internal to the impeller to the extensions 44 of the nozzles 26 which are engaged in corresponding housings of the impeller.

[0077] The impeller 22 has a generally annular shape and extends around the axis X. The nozzles are fixed by their lugs 30 on the impeller 22 and all extend on the same side of the impeller 22, parallel to the axis X. When the impeller 22 is mounted on the planet carrier 13, the nozzles are inserted into the spaces between the sun 11 and the planets 13, and between the crown 14 and the planets 13, at the level of their meshings for the purpose of lubricating them by spraying oil.

[0078] Advantageously, as described above, the fixing lug 30 of each of the nozzles 26 is oriented radially towards the axis X so that this lug works in traction during operation of the reducer 10.

Claims

Claims

1. Oil nozzle (26) for a reducer (10), in particular an epicyclic, of an aircraft turbomachine (1), this nozzle (26) comprising a body (28) having an elongated shape along an axis (Y), and a fixing lug (30) which is located at a first longitudinal end (28a) of the body (28) and which is formed in one piece with the body (28), the body (28) comprising an internal cavity (32) which extends along the axis (Y), this internal cavity (32) opening at the level of said first end (28a) and being closed at the level of a second longitudinal end (28b) of the body (28), opposite the first end (28a), the body (28) further comprising oil projection orifices (34) in fluid communication with said cavity (32), characterized in that the internal cavity (32) comprises two coaxial portions,a first portion (36) of the cavity (32) which has a truncated cone shape and which is located at the first end (28a) of the body (28), and a second portion (38) of the cavity (32) which has a cylindrical shape with a constant diameter (D) and which extends from the smallest diameter of the first portion (36) to the second closed end (28b) of the body (28) which is formed in one piece with the rest of the body (28).,

2. Nozzle (26) according to the preceding claim, in which the body (28) comprises at its second end (28b) a bottom wall (40) which closes the cavity (32) and which defines a third portion (42) of the cavity of truncated or conical shape which is coaxial with the first and second portions (36, 38) and the largest diameter of which is located on the side of the second portion (38) of the cavity (32).

3. A nozzle (26) according to claim 2, wherein the bottom wall (40) has a thickness (E2) which is equal to + / -10% of a thickness (El) of the body (28) along the cavity (32).

4. Nozzle (26) according to one of the preceding claims, in which the body (28) comprises a tubular extension (44) which extends along the axis (Y) beyond the fixing lug (30), this tubular extension (44) comprising said first portion (36) of the cavity (32) and at least one external annular groove (46) for housing a seal (48).

5. Nozzle (26) according to one of the preceding claims, in which the fixing lug (30) is located at an annular excess thickness (50) of the body (28).

6. Nozzle (26) according to one of the preceding claims, in which the fixing lug (30) is connected to the body (28) by a connecting fillet (52) of concave curved shape.

7. A nozzle (26) according to claim 6, wherein the fillet (52) has a sectional shape which corresponds to a curve having a polynomial equation of degree 2.

8. A nozzle (26) according to claim 7, wherein the polynomial equation of degree 2 is y = 8.1754x2 - 10.734x + 3.8845.

9. Nozzle (26) according to one of the preceding claims, in which the body (28) has a generally prismatic shape with a rectangular base.

10. Nozzle (26) according to one of the preceding claims, in which the orifices (34) are all located on the same flat surface of the body (28), which extends along the axis (Y).

11. Nozzle (26) according to claim 10, in which the orifices (34) are aligned on the same line parallel to the axis (Y).

12. Nozzle (26) according to one of the preceding claims, in which the orifices (34) and the fixing lug (30) are oriented in the same direction with respect to said axis (Y).

13. Reducer (10), in particular epicyclic, for an aircraft turbomachine (1), this reducer (10) comprising a sun gear (11) centered on a first axis (Y), a fixed crown (14) extending around the sun gear (11) and the first axis (Y), and satellites (12) meshed with the sun gear (11) and the crown (14) and rotatable around second axes (Z) parallel to the first axis (X), the satellites (12) being carried by a planet carrier (13) which is rotatable around the first axis (X) and which carries nozzles (26) according to one of the preceding claims.

14. Reducer according to claim 13, in which the fixing lug (30) of each of the nozzles (26) is oriented radially towards the first axis (X).

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