TURBO ENGINE OF AN AIRCRAFT

Abstract

Power transmission module (110) for an aircraft, this module comprising a torque input (110a) connected to a turbine shaft (3), a first torque output (110b) and a second torque output (110c), this power transmission module (110) comprising a mechanical reducer (6) including a solar element (7) forming said torque input (110a), and satellites (120) carried by a satellite carrier (10), characterized in that each of the satellites (120) comprises at least three independent gear sets (120a, 120b, 120c) and includes: - a first gear set meshed with the solar element (7), - a second gear set meshed with an element forming one of the torque outputs (110b, 110c), and - a third gear set meshed with another element.

Description

Domaine technique de l'invention

[0001] The present invention relates to a power transmission module for an aircraft turbomachine, as well as a turbomachine comprising such a module. Arrière-plan technique

[0002] The state of the art includes in particular documents WO-A1-2010 / 092263, FR-A1-2 987 416, FR-A1-3 008 462, FR-A1-3 008 463, FR-A1-3 041 054, US-A1-2015 / 354672, EP-A1-3 859 134 and US-B2-9,797,470.

[0003] Newer generations of turbofan engines, particularly those with a high bypass ratio, incorporate a mechanical gearbox to drive the fan shaft. Typically, the gearbox's purpose is to transform the high rotational speed of the power turbine shaft into a slower rotational speed for the fan shaft.

[0004] Such a reduction gear generally comprises a central pinion, called the sun gear, a ring gear, and pinions called planet gears, which mesh between the sun gear and the ring gear. The planet gears are held by a frame called the planet carrier. The sun gear, ring gear, and planet carrier are planetary gears because their axes of revolution coincide with the longitudinal X-axis of the turbomachine. The planet gears each have a different axis of revolution and are evenly spaced around the same operating diameter of the planetary gears. These axes are parallel to the longitudinal X-axis.

[0005] There are several gearbox architectures. In state-of-the-art turbomachinery, gearboxes are of the planetary or epicyclic type. In other similar applications, there are so-called differential or compound architectures. In a planetary gearbox, the planet carrier is fixed, and the ring gear forms the output shaft of the device, rotating in the opposite direction to the sun gear. In an epicyclic gearbox, the ring gear is fixed, and the planet carrier forms the output shaft of the device, rotating in the same direction as the sun gear. In a differential gearbox, no element is fixed in rotation. The ring gear rotates in the opposite direction to both the sun gear and the planet carrier. Gearboxes can consist of one or more meshing stages. This meshing is achieved in various ways, such as by contact, friction, or magnetic fields.

[0006] In this application, the terms "stage" or "toothing" refer to at least one series of interlocking teeth with at least one series of complementary teeth. A toothing system may be internal or external.

[0007] A satellite can have one or two gear stages. A single-stage satellite has teeth that can be straight, helical, or chevron-shaped, with teeth on the same diameter. These teeth cooperate with both the sun gear and the crown gear.

[0008] A two-stage satellite comprises two sets of teeth located on different diameters. One set of teeth cooperates with the sun gear and a second set of teeth generally cooperates with the corona.

[0009] Newer generations of turbomachinery may include a mechanical gearbox that drives the main fan and another fan, which can be considered a smaller or secondary fan. The gearbox is part of a power transmission module used to drive the main fan shaft and the secondary fan shaft.

[0010] However, the technologies currently proposed for this type of power transmission module are not satisfactory, particularly from the point of view of their complexity, size and mass.

[0011] The invention offers an improvement that makes it possible to mitigate all or part of these drawbacks. Résumé de l'invention

[0012] The invention relates to a power transmission module for an aircraft turbomachine, comprising: a torque input configured to be connected to a turbine shaft, a first torque output, and a second torque output, characterized in that each of the satellites comprises at least three independent gears and includes: a second set of teeth meshed with an element forming one of the first and second torque outputs, and a third set of teeth meshed with another element, this other element forming the other of the first and second torque outputs when said planet carrier is fixed, or this other element being a fixed ring when said planet carrier is mobile and forms the other of the first and second torque outputs.

[0013] In this application, the terms "upstream" and "downstream" refer to the flow of gases in the turbomachine, and in particular in the turbomachine's ducts (from upstream to downstream).

[0014] The invention proposes using triple-toothed satellite gears in the power transmission module's gearbox. One of these teeth is meshed with the solar element and dedicated to transmitting the input torque. Another tooth is meshed with an element dedicated to transmitting one of the output torques; this other element could be, for example, a ring gear or another solar element. Finally, the last tooth is meshed with another element, which can be either dedicated to transmitting the other output torque or a fixed ring gear. In the first case, when the other element is dedicated to transmitting an output torque, the gearbox's planet carrier is fixed. In the second case, when the other element is a fixed ring gear, the planet carrier is movable and dedicated to transmitting the other output torque.

[0015] There are a multitude of possible configurations depending in particular on the positions of the torque inputs and outputs, the diameters of the teeth, the types of teeth (helical, straight, herringbone), etc.

[0016] This solution is compatible with multi-stage gearboxes. It is also compatible with gearboxes where the planet carrier rotates, such as epicyclic or differential gearboxes. It is also compatible with gearboxes with spur, helical, or herringbone gears. Finally, it is compatible with gearboxes with a one-piece planet carrier or a cage-type carrier.

[0017] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other: said first, second and third gear teeth have different diameters; said second torque output includes a tubular portion through which said first torque output passes; the element forming said second torque output is a ring gear or another sun gear; said first, second and third gear teeth are selected from spur, helical or herringbone gears; said first gear tooth is located upstream and is of the helical type, the second gear tooth is meshed with said first torque output and is of the spur type, and said third gear tooth located downstream is meshed with the fixed ring gear and is of the helical type; said first gear tooth is located upstream and is of the herringbone type, the second gear tooth is meshed with said first torque output and is of the spur type, and said third gear tooth located downstream is meshed with the fixed ring gear and is of the helical type; each of the planet gears includes a fourth gear tooth;Each of the satellites comprises two independent gears meshed with two independent gears of the solar element and separated from each other by two other gears of the satellite.

[0018] The present invention also relates to an aircraft turbomachine, comprising at least one module as described above.

[0019] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other: a gas generator equipped with a turbine comprising a turbine shaft having an axis of rotation, a main blower propeller driven in rotation by a main shaft coupled to the first torque output, this propeller being located upstream of a first annular nozzle separating two annular flow paths respectively of an internal primary flow and an external secondary flow, a secondary blower propeller driven in rotation by a secondary shaft coupled to the second torque output, this propeller being located in the primary flow path; the transmission module is located inside an annular casing which comprises two coaxial annular walls, respectively internal and external, defining between them said primary flow path;The internal annular wall of the annular housing is connected to an upstream annular support of at least one bearing guide for said first torque output, and / or to a downstream annular support of at least one bearing guide for said second torque output; the internal annular wall of the annular housing is connected to said fixed ring which is located between said first and second supports. Brève description des figures

[0020] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which: [ Fig.1 ] there figure 1 is a schematic axial cross-sectional view of a turbomachine for an aircraft, [ Fig.2 ] there figure 2 is a partial axial cross-sectional view of a mechanical reducer, [ Fig.3 ] there figure 3 is a schematic axial cross-sectional view of a turbomachine for an aircraft, [ Fig.4 ] there figure 4 is a schematic axial cross-sectional view of a turbomachine for an aircraft according to the invention, [ Fig.5 ] there figure 5 is a very schematic axial cross-sectional view of a power transmission module of the turbomachine of the figure 4 , [ Fig.6 ] there figure 6 is a partial schematic axial cross-sectional view of the turbomachine's power transmission module figure 4 , [ Fig.7 ] there figure 7 is another partial schematic axial cross-sectional view of the turbomachine's power transmission module figure 4 and illustrates a variant of the satellite gear design; [ Fig.8 ] there figure 8 is a schematic perspective and axial cross-sectional view of the turbomachine's power transmission module. figure 4 and illustrates another variant of the satellite gear design; [ Fig.9a-9b ] THE figures 9a et 9b are views similar to that of the figure 5 and illustrate alternative implementations of the power transmission module; [ Fig.9c-9d ] THE figures 9c et 9d are views similar to that of the figure 5 and illustrate other embodiments of the power transmission module; [ Fig.9e-9f ] THE figures 9e et 9f are views similar to that of the figure 5 and illustrate other embodiments of the power transmission module; [ Fig.9g-9h ] THE figures 9g et 9h are views similar to that of the figure 5 and illustrate other embodiments of the power transmission module; [ Fig.9i-9j ] THE figures 9i et 9j are views similar to that of the figure 5 and illustrate other embodiments of the power transmission module; [ Fig.10 ] there figure 10 is a partial schematic perspective and axial section view of a power transmission module and shows the directions of rotation of its parts. Description détaillée de l'invention

[0021] There figure 1 describes a turbomachine 1 which conventionally comprises a fan S or fan blade and a gas generator including a low-pressure compressor 1a, a high-pressure compressor 1b, an annular combustion chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1e, and an exhaust nozzle 1h. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 2 and together form a high-pressure (HP) unit. The low-pressure compressor 1a and the low-pressure turbine 1e are connected by a low-pressure shaft 3 and together form a low-pressure (LP) unit.

[0022] The turbomachine 1 is a dual-flow turbomachine in that two airflows, primary F1 and secondary F2 respectively, flow along the longitudinal axis X of the turbomachine. The incoming airflow F, which enters the turbomachine and passes through the fan S, is split in two downstream of the fan by an annular separating nozzle 17. A radially internal airflow flows inside the nozzle 17 and forms the primary flow F1, which flows inside the gas generator. A radially external airflow flows outside the nozzle 17 and forms the secondary flow F2, which flows around the gas generator.

[0023] The blower S is driven by a blower shaft 4 which is driven by the BP shaft 3 by means of a reducer 6. This reducer 6 is generally of the planetary or epicycloidal type.

[0024] The following description concerns an epicycloidal type reducer, whose planet carrier and sun gear are mobile in rotation, the ring gear of the reducer being fixed in the frame of reference of the motor.

[0025] The gearbox 6 is positioned in the upstream part of the turbomachine. A fixed structure schematically comprising, here, an upstream part 5a and a downstream part 5b which make up the motor or stator housing 5 is arranged to form an enclosure E surrounding the gearbox 6. This enclosure E is closed upstream by seals at the level of a bearing allowing the passage of the blower shaft 4, and downstream by seals at the level of the passage of the BP shaft 3.

[0026] There figure 2 Figure 6 shows an epicyclic reduction gear. At the input, the reduction gear 6 is connected to the shaft BP 3, for example via internal splines 7a. Thus, the shaft BP 3 drives a planetary gear called the sun gear 7. Typically, the sun gear 7, whose axis of rotation coincides with that of the longitudinal axis X, drives a series of gears called planet gears 8, which are equally spaced around the same diameter around the axis of rotation X. This diameter is equal to twice the operating center distance between the sun gear 7 and the planet gears 8. The number of planet gears 8 is generally defined between three and seven for this type of application.

[0027] The set of satellites 8 is held by a frame called the satellite carrier 10. Each satellite 8 rotates around its own Y axis, and meshes with the ring 9.

[0028] Our output is: ▪ In this epicyclic configuration, the set of planet gears 8 drives the planet carrier 10 in rotation around the X-axis of the turbomachine. The ring gear is fixed to the motor or stator housing 5 via a ring carrier 12, and the planet carrier 10 is fixed to the fan shaft 4. ▪ In another planetary configuration, the set of planet gears 8 is held by a planet carrier 10, which is fixed to the motor or stator housing 5. Each planet gear drives the ring gear, which is connected to the fan shaft 4 via a ring carrier 12. ▪ In another differential configuration, the set of planet gears 8 is held by a planet carrier 10, which is connected to a first fan shaft 5. Each planet gear drives the ring gear, which is connected to a second, counter-rotating fan shaft 4 via a ring carrier 12.

[0029] Each satellite 8 is mounted to rotate freely using a bearing 11, for example, a roller bearing or hydrodynamic bearing. Each bearing 11 is mounted on one of the axes 10b of the satellite carrier 10, and all the axes are positioned relative to each other using one or more structural frames 10a of the satellite carrier 10. There is a number of axes 10b and bearings 11 equal to the number of satellites. For operational, assembly, manufacturing, inspection, repair, or replacement purposes, the axes 10b and the frame 10a may be separated into several parts.

[0030] For the same reasons mentioned above, the teeth of a satellite gear can be separated into several helices or teeth, each with a median plane P, P'. In our example, we detail the operation of a reducer in which each satellite gear comprises two sets of herringbone teeth cooperating with a ring gear divided into two half-rings: ▪ An upstream half-crown 9a consisting of a rim 9aa and a mounting flange half 9ab. The front helix is ​​located on the rim 9aa and meshes with a helix of toothed gear 8d on each satellite 8. The helix of toothed gear 8d also meshes with that of the solar sphere 7. ▪ A downstream half-crown 9b consisting of a rim 9ba and a mounting flange half 9bb. The rear helix is ​​located on the rim 9ba and meshes with a helix of toothed gear 8d on each satellite 8. The helix of toothed gear 8d also meshes with that of the solar sphere 7.

[0031] Although the helix widths vary between the solar 7, the satellites 8 and the crown 9 because of the overlapping teeth, they are all centered on a median plane P for the upstream teeth and on another median plane P' for the downstream teeth.

[0032] There figure 2 This illustrates the case of a single-stage gear reducer, that is, the same toothing 8d of each satellite 8 cooperates with both the solar 7 and the ring 9. Even though the toothing 8d comprises two sets of teeth, these teeth have the same average diameter and form a single set of teeth called a chevron.

[0033] The mounting flange 9ab of the upstream half-crown 9a and the mounting flange 9bb of the downstream half-crown 9b form the mounting flange 9c of the crown. The crown 9 is attached to a crown carrier by joining the mounting flange 9c of the crown and the mounting flange 12a of the crown carrier using, for example, a bolted assembly.

[0034] The arrows of the figure 2 The diagram describes the oil delivery within the gearbox 6. Oil enters the gearbox 6 from the stator section 5 via a distributor 13 by various means, which will not be detailed in this view as they are specific to one or more types of architecture. The distributor 13 comprises injectors 13a and arms 13b. The injectors 13a lubricate the gear teeth, and the arms 13b lubricate the bearings. Oil is supplied to injector 13a and exits through end 13c to lubricate the gear teeth. Oil is also supplied to arm 13b and flows through the bearing's supply port 13d. The oil then flows through the shaft in one or more buffer zones 10c and exits through ports 10d to lubricate the planetary gear bearings.

[0035] There figure 3 shows a 100-series twin-flow aircraft turbomachine.

[0036] The references used in the figure 1 are used in the figure 3 to refer to the same elements.

[0037] The inlet airflow F entering the turbomachine 100 and passing through the fan S, which is a main fan, is split in two downstream of the fan S by an annular separating nozzle 17. An internal radial airflow flows inside the nozzle 17 and forms the primary flow F1. An external radial airflow flows outside the nozzle 17 and forms the secondary flow F2, which flows around the gas generator.

[0038] The turbomachine 1 here includes a secondary blower S' which includes a propeller or bladed wheel located in the flow duct of the primary flow F1.

[0039] The turbomachine 100 includes a power transmission module 110 having a torque input 110a connected to the low pressure shaft 3, a first torque output 110b connected to the main shaft 104 driving the rotor and propeller of the main blower S, and a second torque output 110c connected to the secondary shaft 114 driving the rotor and propeller of the secondary blower S'.

[0040] There figure 4 illustrates a double-flow turbomachine 100 according to an embodiment of the invention.

[0041] The power transmission module 110 of this turbomachine 100 includes a reduction gear 6 similar to that of the figures 1 et 2 , and includes 120 satellites with three independent gears 120a, 120b, 120c (only one satellite being visible at the figure 4 ).

[0042] The reducer 6 includes the torque input 110a and the two torque outputs 110b, 110c.

[0043] The torque input 110a is formed by the solar element 7 of the reducer 6 which is coupled to the low-pressure shaft 3 and which is meshed with one of the teeth (120c in the example of the figure 4 ) of each of the 120 satellites.

[0044] As will be explained in detail below, there are a multitude of possible configurations for the meshing of the 120a, 120b, and 120c gears of the 120 satellites. figures 4 à 8 And 9a à 9j illustrate several possible configurations and several variations of the same configuration, among the multitude of possible configurations (more than 1000). As can be seen in the figures 4 à 8 Specifically, the diameters of the 120a, 120b, and 120c gears can be different. The 120a, 120b, and 120c gears can be arranged in any order or according to their diameters, for example, from smallest to largest diameter upstream to downstream, or from largest to smallest diameter upstream to downstream. Each gear set can be meshed with a ring gear or a sun gear.

[0045] The advantage of changing the positional gears is that it allows the forces in the satellites 120a, 120b, 120c to be balanced and the residual moments to be minimized.

[0046] Generally speaking, the teeth located upstream are called "upstream teeth", the teeth located downstream are called "downstream teeth", and the teeth located between the upstream and downstream teeth are called "intermediate teeth".

[0047] In the example shown in the figure 4 The larger diameter upstream toothing 120a is meshed with a first ring 12b forming the first torque output 110b and connected to the main shaft 104. This main shaft 104 is guided in rotation by at least one bearing 170a which is carried by an upstream annular support 170.

[0048] The smaller diameter downstream toothing 120c is meshed with the solar 7 which forms the torque input 110a and is connected to the low pressure shaft 3. The intermediate toothing 120b is meshed with a second ring 12c which is fixed.

[0049] The planet carrier 10 of the reducer 6 is mobile in rotation and forms the second torque output 110c by being connected to the secondary shaft 114. This secondary shaft 114 is guided in rotation by at least one rolling bearing 180a which is carried by a downstream annular support 180.

[0050] The transmission module 110 is located inside an annular housing 160 which includes two coaxial annular walls 160a, 160b defining between them the flow vein of the primary flow F1.

[0051] The annular supports 170, 180 are fixed to the housing 160. The bearings 170a, 180a are respectively located upstream and downstream of the module 110. The ring 12c is located between the supports 170, 180.

[0052] The low-pressure shaft 3 is guided in rotation by at least one roller bearing 190a which is carried by another annular support 190.

[0053] In the example shown in the figure 5 The upstream toothing 120a of smaller diameter is meshed with the solar 7 which forms the torque input 110a and is connected to the low pressure shaft 3. An upstream end of the low pressure shaft 3 or of the solar 7 can be centered and guided inside the planet carrier 10, upstream of the reducer 6.

[0054] The planet carrier 10 is rotationally mobile and forms the second torque output 110c by being connected to the secondary shaft 114. The planet carrier 10 includes a downstream tubular portion 10e through which the low-pressure shaft 3 passes. The guide bearings (not shown) of the planet carrier 10 or of the secondary shaft 114 can be supported by the housing 160, as mentioned above.

[0055] The larger diameter downstream 120c teeth are meshed with a fixed 12c ring connected to the 160 housing.

[0056] The intermediate toothing 120b is meshed with the ring 12b which is mobile in rotation and forms the first torque output 110b by being connected to the main shaft 104. The guide bearing (not shown) of this main shaft 104 can be carried by the housing 160, as mentioned above.

[0057] There figure 6 is a less schematic view of reducer 6 of the figure 5 The types of gear teeth can be identical or different. For example, 120a, 120b, and 120c teeth can be straight, helical, or herringbone. Alternatively, all configurations and combinations are possible.

[0058] In the case of the figure 7 For example, the upstream gear 120a is helical, the intermediate gear 120b is spur, and the downstream gear 120c is helical. With a predefined helix angle, it is possible with such a solution to cancel the axial forces on the planet gears 120. In the case of the figure 8 The upstream toothing 120a is of the herringbone type, the intermediate toothing 120b is of the straight type, and the downstream toothing 120'c is of the helical type. Each of the satellites 120 also includes a fourth toothing 120d meshing with the solar 7. The teeth 120b and 120'c are located between the teeth 120a and 120d, and the solar 7 includes two independent teeth 7a, axially spaced for meshing with the teeth 120a and 120d.

[0059] This last solution is interesting because it maintains the direction of rotation on both torque outputs 110b, 110c. Unlike a solution with one output on a second solar cell, this solution is suitable for a reduction ratio greater than 1.9.

[0060] In the TR1 configuration of the figure 9a The smaller diameter downstream gear 120c meshes with the solar element 7. The larger diameter upstream gear meshes with the ring gear 12b, which forms the first torque output 110b, and the intermediate gear 120b meshes with the ring gear 12c, which forms the second torque output 110c. The planet carrier 10 is fixed.

[0061] The TR1' configuration of the figure 9b is close to the TR1 configuration. The difference concerns the upstream teeth 120a which is meshed with the ring 12c which forms the second torque output 110c, and the intermediate teeth 120b are meshed with the ring 12b which forms the first torque output 110b.

[0062] In the TR2 configuration of the figure 9c The smaller diameter downstream toothing 120c is meshed with the solar 7. The larger diameter upstream toothing 120a is meshed with another solar 7' which forms the first torque output 110b, and the intermediate toothing 120b is meshed with the ring 12c which forms the second torque output 110c and which includes a tubular portion 12c1 through which the solar 7 or the low pressure shaft 3 passes. The planet carrier 10 is fixed.

[0063] In the TR2' configuration of the figure 9d The smaller diameter upstream gear 120a meshes with the solar element 7. The larger diameter downstream gear 120c meshes with another solar element 7', which includes a tubular portion 7b through which the solar element 7 or the low-pressure shaft 3 passes, forming the second torque output 110c. The intermediate gear 120b meshes with the ring gear 12b, which forms the first torque output 110b. The planet carrier 10 is fixed.

[0064] In the TR3 configuration of the figure 9e The intermediate gear 120b meshes with the solar element 7. The larger diameter upstream gear 120a meshes with another solar element 7', which forms the first torque output 110b. The smaller diameter downstream gear 120c meshes with another solar element 7" which includes a tubular section 7b through which the solar element 7 or the low-pressure shaft 3 passes, forming the second torque output 110c. The planet carrier 10 is fixed.

[0065] The TR3' configuration of the figure 9f is close to the TR3 configuration. The difference lies in the upstream 120a gear, which meshes with the 7" solar element that forms the second torque output 110c, and the downstream 120c gear, which meshes with the 7" solar element that forms the first torque output 110b. In the TR4 configuration of the figure 9g The smaller diameter downstream gear 120c meshes with the solar shaft 7. The larger diameter upstream gear 120a meshes with the ring gear 12b, which forms the first torque output 110b. The intermediate gear 120b meshes with the fixed ring gear 12c. The planet carrier 10 is movable and includes a tubular portion 10e through which the solar shaft 7 or the low-pressure shaft 3 passes, forming the second torque output 110c.

[0066] In the TR4' configuration of the figure 9h The smaller diameter upstream gear 120a meshes with the solar element 7. The larger diameter downstream gear 120c meshes with the ring gear 12c, which forms the second torque output 110c. The intermediate gear 120b meshes with the fixed ring gear 12b. The planet carrier 10 is movable and forms the first torque output 110b.

[0067] In the TR5 configuration of the figure 9i The smaller diameter downstream gear 120c meshes with the solar shaft 7. The larger diameter upstream gear 120a meshes with another solar shaft 7', which forms the first torque output 110b. The intermediate gear 120b meshes with the fixed ring gear 12b. The planet carrier 10 is movable and includes a tubular portion 10e through which the solar shaft 7 or the low-pressure shaft 3 passes, forming the second torque output 110c.

[0068] In the TR5' configuration of the figure 9j The intermediate gear 120b meshes with the solar element 7. The larger diameter upstream gear 120a meshes with the fixed ring gear 12b. The smaller diameter downstream gear 120c meshes with another solar element 7', which includes a tubular portion 7b through which the solar element 7 or the low-pressure shaft 3 passes, forming the second torque output 110c. The planet carrier 10 is movable and forms the first torque output 110b.

[0069] There figure 10Figure 6 shows the directions of rotation of the components of the power transmission module 110, part of the gearbox 6. Only one satellite 120 is shown, and arrow F3 indicates its direction of rotation around its Y-axis. The solar elements 7 and 7' rotate in the same directions F4 and F5 around the longitudinal X-axis of the gearbox 6. The ring 12b rotates in the opposite direction around this X-axis.

[0070] All these solutions allow for two outputs from a single input with constant reduction ratios. Depending on the desired reduction ratio and direction of rotation, one or more configurations can meet the need. For example, if a ratio of 1 / 1.5 / 8 is required (i.e., a 1:1 torque input (110a), a first 1:1.5 torque output (110b), and a second 1:8 torque output (110c) is desired), then one of the preferred solutions is the TR4 type.

[0071] The power transmission module 110 according to the invention thus makes it possible, from the high speed transmitted by the low-pressure shaft 3, to provide two torque outputs at two different speeds, while minimizing the mass and size of the gearbox 6 of this module. The invention is particularly suited to low reduction ratios, for example less than two, and to power levels on the order of megawatts.

[0072] Although the invention is illustrated in the context of a twin-flow aircraft turbomachine, the module can be fitted to another type of turbomachine.

Claims

1. Aircraft turbomachine (100), comprising: + a gas generator equipped with a turbine (1e) having a turbine shaft (3) with an axis of rotation (X), and + a main fan propeller (S) driven in rotation by a main shaft (104), this propeller being located upstream of a first annular nozzle (17) separating two annular flow paths, respectively, of an internal primary flow (F1) and an external secondary flow (F2), + a secondary fan propeller (S') driven in rotation by a secondary shaft (114), this propeller being located in the flow path of the primary flow (F1), and + a power transmission module (110), comprising - a torque input (110a) configured to be connected to a turbine shaft (3), - a first torque output (110b) coupled to the main shaft (104), and - a second torque output (110c) coupled to the secondary tree (114),This power transmission module (110) comprises a mechanical reducer (6) including a solar element (7) forming said torque input (110a), and satellites (120) carried by a satellite carrier (10), each of these satellites (120) having a first set of teeth meshing with the solar element (7), each of the satellites (120) comprising at least three independent sets of teeth (120a, 120b, 120c) and comprising: - a second set of teeth meshing with an element forming one of the first and second torque outputs (110b, 110c), and - a third set of teeth meshing with another element, this other element forming the other of the first and second torque outputs (110b, 110c) when said satellite carrier (10) is fixed, or this other element being a fixed ring gear (12b, 12c) when said satellite carrier (10) is movable and forms the other of the first and second couple outputs (110b, 110c).

2. Turbomachine (100) according to claim 1, wherein said first, second and third gear teeth (120a, 120b, 120c) have different diameters.

3. Turbomachine (100) according to claim 1 or 2, wherein said second torque output (110c) comprises a tubular portion through which said first torque output (110b) passes.

4. Turbomachine (100) according to any one of the preceding claims, wherein the element forming said second torque output is a ring (12b, 12c) or another solar element (7', 7").

5. Turbomachine (100) according to any one of the preceding claims, wherein said first, second and third gears (120a, 120b, 120c) are selected from straight, helical or herringbone gears.

6. Turbomachine (100) according to claim 5, wherein said first gear (120a) is located upstream and is of the helical type, the second gear (120b) is meshed with said first torque output (110b) and is of the straight type, and said third gear (120c) located downstream is meshed with the fixed ring gear (12b, 12c) and is of the helical type.

7. Turbomachine (100) according to claim 5, wherein said first gear (120a) is located upstream and is of the herringbone type, the second gear (120b) is meshed with said first torque output (110b) and is of the straight type, and said third gear (120c) located downstream is meshed with the fixed ring (12b, 12c) and is of the helical type.

8. Aircraft turbomachine (100) according to any one of the preceding claims, wherein each of the satellites comprises a fourth gear (120d).

9. Aircraft turbomachine (100) according to any one of the preceding claims, in which each of the satellites (120) comprises two independent gears (120a, 120d) meshed with two independent gears (7a) of the solar (7) and separated from each other by two other gears (120b, 102c) of the satellite.

10. Aircraft turbomachine (100) according to any one of the preceding claims, wherein the transmission module (110) is located inside an annular housing (160) which comprises two coaxial annular walls, respectively internal (160b) and external (160a), defining between them said primary flow channel.

11. Aircraft turbomachine (100) according to claim 10, wherein the inner annular wall (160b) of the annular housing (160) is connected to an upstream annular support (170) of at least one bearing (170a) with a guide bearing of said first torque output (110b), and / or to a downstream annular support (180) of at least one bearing (180a) with a guide bearing of said second torque output (110c).

12. Aircraft turbomachine (100) according to claim 11, wherein the inner annular wall (160b) of the annular housing (160) is connected to said fixed ring (12c) which is located between said first and second supports (170, 180).