AIRCRAFT TURBOMACHINE MECHANICAL REDUCER

专利摘要:
Mechanical reduction gear (60) of a turbomachine (1), in particular of an aircraft, this reduction gear comprising a sun (70) having an axis of rotation (X), a ring (90) which extends around the sun and which is configured to be stationary in rotation around said axis, satellites (80) which are meshed with the sun and the crown and which are held by a planet carrier (100) which is configured to be stationary or in rotation about said axis, each satellite comprising a first toothing (82) of average diameter D1 for engagement with the solar, and a second toothing (84) of average diameter D2, different from D1, for engagement with the crown, stationary or in rotation, characterized in that the first and second teeth of each satellite comprise chevron teeth and have symmetry with respect to a plane (H) perpendicular to said axis and passing substantially through the middle of the satellite. Figure for abstract: Figure 4
公开号:FR3095251A1
申请号:FR1904052
申请日:2019-04-16
公开日:2020-10-23
发明作者:Louis Simon Adrien；Loïc Clément LEFEBVRE Simon；Pierre MOULY Guillaume
申请人:Safran Transmission Systems SAS；
IPC主号:

专利说明:

[0001] Technical field of the invention
[0002] The present invention relates to the field of mechanical reduction gears for turbomachines, in particular aircraft.
[0003] Technical background
[0004] The state of the art includes in particular the documents WO-A1-2010/092263, FR-A1-2 987 416, FR-A1-3 008 462, FR-A1-3 008 462 and FR-A1-3 041 054 .
[0005] The role of a mechanical gearbox is to modify the speed and torque ratio between the input axis and the output axis of a mechanical system.
[0006] New generations of dual-flow turbomachines, particularly those with a high bypass ratio, include a mechanical reduction gear to drive the shaft of a fan (also called a “fan”). Usually, the purpose of the reduction gear is 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.
[0007] Such a reducer comprises a central pinion, called sun gear, a crown and pinions called satellites, which are engaged between the sun gear and the crown. The satellites are held by a frame called the planet carrier. The solar, the crown and the planet carrier are planetary because their axes of revolution coincide with the longitudinal axis X of the turbomachine. The satellites each have a different axis of revolution evenly distributed over the same operating diameter around the axis of the planetary gears. These axes are parallel to the longitudinal axis X.
[0008] There are several reducer architectures. In the state of the art of turbofan engines, the reduction gears are of the planetary or planetary type. In other similar applications, there are so-called differential or “compound” architectures.
[0009] - 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 sun.
[0010] - On an epicyclic reduction gear, the crown is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the sun gear.
[0011] - On a differential gearbox, no element is fixed in rotation. The crown rotates in the opposite direction to the sun and the planet carrier.
[0012] 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. There are several types of contact meshing such as straight, helical or chevron gears.
[0013] The increase in reduction ratios of target motor architectures leads to the use of so-called “double-stage” reduction gears. Indeed, beyond a ratio of around 7, the so-called "single stage" technology loses its interest because it is no longer compact enough. It is then necessary to use so-called “double-stage” reducers.
[0014] In a single stage technology, it is the same toothing of a satellite which cooperates with the sun and the crown. In a double-stage technology, the toothing of the satellite which cooperates with the sun is different from the toothing of the satellite which cooperates with the crown. In general, the teeth of a satellite which cooperate respectively with the solar and the crown have different average diameters.
[0015] The main problem with double-stage gearboxes lies in the fact that they are asymmetrical with respect to a plane perpendicular to the X axis. Thus, the power entering downstream from the inside and emerging upstream through the outside generates non-negligible moments at the level of the satellites (the expressions “upstream” and “downstream” referring to the general flow of gases in the turbomachine). Also, to gain in compactness and quality of meshing, it is preferable to use helical teeth.
[0016] The helical teeth generate significant axial forces at the interfaces between the reducer and the motor.
[0017] The use of herringbone teeth could solve these problems of axial force. However, this does not solve the bearing moments and complicates the assembly and manufacture of the reducer.
[0018] The present invention proposes an improvement to this technology which is simple, efficient and economical.
[0019] The invention relates to a mechanical reduction gear for a turbomachine, in particular for an aircraft, this reduction gear comprising:
[0020] - a solar having an axis of rotation,
[0021] - a corona that extends around the sun,
[0022] - satellites which are meshed with the sun gear and the crown and which are held by a planet carrier, each satellite comprising a first toothing of average diameter D1 for meshing with the sun gear, and a second toothing of average diameter D2, lower at D1, for meshing with the crown,
[0023] characterized in that the first and second teeth of each satellite have symmetry with respect to a plane perpendicular to said axis and passing substantially in the middle of the satellite,
[0024] and in that each of the first and second toothings comprises herringbone teeth, the chevron of the first toothing being formed by upstream teeth of the first toothing separated from downstream teeth of the first toothing by being arranged on either side of the plane, and the upstream teeth of the second set of teeth being separated from the downstream teeth of the second set of teeth by the first set of teeth.
[0025] The use of satellites with symmetrical teeth makes it possible to solve the aforementioned problem of moments at the bearings of the satellites. In addition, the teeth of the satellites are herringbone to optimize the compactness and meshing of the gearbox.
[0026] In the present application, a toothing with herringbone teeth is understood to mean a toothing comprising two series of teeth oriented in different directions. The teeth of the first series are inclined with respect to the axis around which extends this first series, and the teeth of the second series are inclined differently with respect to its axis. The teeth of the two series are thus inclined relative to each other to form chevrons.
[0027] The reducer according to the invention may comprise one or more of the following characteristics, taken separately from each other, or in combination with each other:
[0028] the upstream teeth of the first set of teeth are separated by an annular groove from the downstream teeth of this first set of teeth; each satellite comprises a cylindrical body and an annular web extending substantially radially outwards from the middle of this body, the teeth of the second set of teeth being located at the axial ends of the body, and the teeth of the first set of teeth being located at the outer periphery of the veil; the sun gear comprises teeth with herringbone teeth and comprising upstream and downstream teeth located respectively on either side of said plane; the ring gear comprises a toothing with herringbone teeth and comprising upstream and downstream teeth located respectively on either side of said plane and separated from each other by the second toothing; the teeth of the crown are respectively carried by two rings fixed one and the other on a crown holder; the crown carrier has a generally biconical and substantially symmetrical shape with respect to said plane which passes through the middle of the larger diameter of the crown carrier; the crown carrier includes bearings at its ends to guide the planet carrier or a drive shaft of the planet carrier;
[0029] - the crown is configured to be immobile in rotation around said axis, and the planet carrier is configured to be mobile in rotation around this axis.
[0030] The invention further relates to a turbomachine, in particular for an aircraft, comprising a mechanical reduction gear as described above.
[0031] Brief description of figures
[0032] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:
[0033] Figure 1 is a schematic view in axial section of a turbomachine using the invention,
[0034] Figure 2 is a partial view in axial section of a mechanical reducer,
[0035] Figure 3 is another partial view in axial section of a mechanical reducer, and illustrates the technique prior to the present invention,
[0036] Figure 4 is a schematic view in axial section and in perspective of a reducer according to the invention, and
[0037] Figure 5 is another schematic view in axial section of the reducer of Figure 4.
[0038] Detailed description of the invention
[0039] FIG. 1 describes a turbomachine 1 which comprises, in a conventional manner, a fan 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 1e and a exhaust pipe 1h. 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 body (HP). The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3 and form with it a low pressure body (LP).
[0040] The fan S is driven by a fan shaft 4 which is driven by the LP shaft 3 by means of a reducer 6. This reducer 6 is generally of the planetary or planetary type.
[0041] The description which follows relates to a reducer of the planetary type, of which the planet carrier and the solar are mobile in rotation, the crown of the reducer being fixed in the frame of the motor.
[0042] The reducer 6 is positioned in the upstream part of the turbomachine. A fixed structure comprising schematically, here, an upstream part 5a and a downstream part 5b which makes up the motor casing or stator 5 is arranged so as to form an enclosure E surrounding the reducer 6. This enclosure E is here closed upstream by seals at the level of a bearing allowing the crossing of the fan shaft 4, and downstream by seals at the level of the crossing of the LP shaft 3.
[0043] Figure 2 shows an epicyclic reducer 6. At the input, the reducer 6 is connected to the BP shaft 3, for example via internal splines 7a. Thus, the BP shaft 3 drives a planet gear called the sun gear 7. Conventionally, the sun gear 7, whose axis of rotation coincides with that of the turbomachine X, drives a series of gears called satellites 8, which are evenly distributed over the same diameter around the axis of rotation X. This diameter is equal to twice the operating center distance between the solar 7 and the satellites 8. The number of satellites 8 is generally defined between three and seven for this type of application.
[0044] The set of satellites 8 is held by a frame called the planet carrier 10. Each satellite 8 rotates around its own Y axis, and meshes with the ring gear 9.
[0045] As output we have:
[0046] In this epicyclic configuration, all of the satellites 8 rotate the planet carrier 10 around the axis X of the turbomachine. The ring gear is fixed to the motor casing or stator 5 via a ring gear carrier 12 and the planet gear carrier 10 is fixed to the fan shaft 4. In another planetary configuration, the set of satellites 8 is held by a planet carrier 10 which is fixed to the motor casing or stator 5. Each satellite drives the crown which is attached to the fan shaft 4 via a crown carrier 12. In another differential configuration, the set of satellites 8 is held by a planet carrier 10 which is connected to a first fan shaft 5. Each satellite drives the ring gear which is attached to a second contra-rotating fan shaft 4 via a carrier -crown 12.
[0047] Each satellite 8 is mounted free to rotate using a bearing 11, for example of the bearing or hydrodynamic bearing type. Each bearing 11 is mounted on one of the axes 10b of the planet carrier 10 and all the axes are positioned relative to each other using one or more structural frames 10a of the planet carrier 10. There are a number of axes 10b and bearings 11 equal to the number of satellites. For reasons of operation, assembly, manufacture, control, repair or replacement, the axles 10b and the frame 10a can be separated into several parts.
[0048] For the same reasons mentioned above, the toothing of a satellite can be separated into several helices or teeth each having a median plane P, P'. In our example, we detail the operation of a reducer, each satellite of which comprises two series of herringbone teeth cooperating with a crown separated into two half-crowns:
[0049] An upstream half-crown 9a consisting of a rim 9aa and a fixing half-flange 9ab. On the rim 9aa is the front helix meshed with a helix of the 8d toothing of each satellite 8. The helix of the 8d toothing also meshes with that of the solar 7. A downstream half-crown 9b consisting of a rim 9ba and a fixing half-flange 9bb. On the rim 9ba is the rear helix meshed with a helix of the 8d toothing of each satellite 8. The helix of the 8d toothing also meshes with that of the solar 7.
[0050] If the helix widths vary between the solar 7, the satellites 8 and the crown 9 because of the toothing overlaps, they are all centered on a median plane P for the upstream teeth and on another median plane P' for the teeth downstream.
[0051] FIG. 2 thus illustrates the case of a reduction gear with a single meshing stage, that is to say that the same toothing 8d of each satellite 8 cooperates with both the sun gear 7 and the ring gear 9. Even if the 8d toothing comprises two series of teeth, these teeth have the same average diameter and form a single and same toothing called a chevron.
[0052] The fixing half-flange 9ab of the upstream crown 9a and the fixing half-flange 9bb of the downstream crown 9b form the fixing flange 9c of the crown. The crown 9 is fixed to a crown holder by assembling the fixing flange 9c of the crown and the fixing flange 12a of the crown holder using a bolted assembly for example.
[0053] The arrows in Figure 2 describe the routing of the oil in the reducer 6. The oil arrives in the reducer 6 from the stator part 5 in a distributor 13 by various means which will not be specified in this view because they are specific to one or more types of architecture. Distributor 13 includes injectors 13a and arms 13b. The injectors 13a have the function of lubricating the teeth and the arms 13b have the function of lubricating the bearings. The oil is brought to the injector 13a to come out through the end 13c in order to lubricate the teeth. The oil is also brought to the arm 13b and circulates via the supply port 13d of the bearing. The oil then circulates through the shaft in one or more buffer zones 10c and then exits through the holes 10d in order to lubricate the bearings of the satellites.
[0054] Figure 3 shows another example of gear architecture, called a double gearing stage, in which each planet gear 8 comprises two separate toothings 8d1, 8d2 configured to cooperate respectively with crown 9 and sun gear 7.
[0055] In this figure 3, the elements already described in the foregoing are designated by the same references.
[0056] The gearing 8d1 for meshing with the crown 9 has an average diameter noted D2 and is located in a median plane P. The gearing 8d2 for meshing with the sun gear 7 has an average diameter noted D1 and is located in another median plane P '. The median planes P, P' are parallel to each other and perpendicular to the X axis. The diameter D2 is less than the diameter D1. Finally, each toothing 8d1, 8d2 here comprises a single helix.
[0057] As mentioned above, this “double-stage” architecture generates significant moments at the level of the satellites 8.
[0058] The present invention proposes to solve this problem by means of double-stage satellites with symmetrical teeth, a preferred embodiment of the invention being represented in FIGS. 4 and 5.
[0059] The reducer 60 of Figures 4 and 5 comprises:
[0060] - a solar 70 having an axis of rotation X,
[0061] - a crown 90 which extends around the sun and which is configured to be stationary in rotation around the X axis, and
[0062] - satellites 80 which are meshed with the solar 70 and the crown 90 and which are maintained by a planet carrier 100 which is configured to be mobile in rotation around the X axis.
[0063] The plane H is defined as being a median plane perpendicular to the axis X and passing substantially in the middle of the reducer 60 (FIG. 5).
[0064] The sun gear 70 comprises internal splines 70a for coupling with the BP shaft 30 as well as an external toothing 70b for meshing with the satellites 80. The toothing 70b has two series of adjacent herringbone teeth, one separated from the other. the other by an annular groove 72 oriented radially outwards. The toothing 70b is symmetrical with respect to the plane H, its teeth being located on either side of the plane H which passes through the groove 72.
[0065] The crown 90 is formed by two independent rings 90a, 90b and comprises a set of teeth which is separated into two series of chevron teeth 90d1, 90d2 carried respectively by the two rings.
[0066] The rings 90a, 90b are arranged symmetrically with respect to the plane H which therefore extends between these rings. The rings are connected and fixed to a crown holder 120 by means of annular connecting flanges 122. The flanges 122 are independent of each other, each flange having in axial half-section a general S-shape giving it a certain radial flexibility by elastic deformation in operation.
[0067] Each ring 90a, 90b extends around the X axis and is fixed to the corresponding flange 122 by its outer periphery. Its inner periphery includes one of the teeth 90d1, 90d2.
[0068] In the example shown, which is not limiting, the crown holder 120 has a generally annular shape around the X axis and more particularly biconical. It thus comprises a first section upstream or on the left in the drawing, with an upstream end of smaller diameter, and a downstream end of larger diameter which is connected to the upstream end of larger diameter of the other section, downstream or right on the drawing. The larger diameter ends of the sections are therefore interconnected, and their smaller diameter ends form the axial ends of the crown carrier.
[0069] The upstream end of the crown gear carrier 120 extends around the planet gear carrier 100 or a shaft connected to this planet gear carrier, and is centered and guided in rotation on the planet gear carrier or the shaft via at least one bearing 124. In the same way, the downstream end of the crown gear carrier 120 extends around the planet gear carrier 100 or a shaft connected to this planet gear carrier, and is centered and guided in rotation on the planet carrier or the shaft via at least one other bearing 126.
[0070] As is the case with the crown 90, the crown holder 120 has a symmetry with respect to the plane H which intersects the crown holder in its middle and therefore passes through the ends of the largest diameter of the aforementioned sections.
[0071] Each satellite 80 comprises a first toothing 82 of average diameter D1 for meshing with the sun gear 70, and a second toothing 84 of average diameter D2, different from D1 and in particular less than D1, for meshing with the ring gear 90. The average diameters are measured from the Y axis of each satellite and represent the average between the maximum diameter and the minimum diameter of a toothing of this satellite.
[0072] Each satellite 80 comprises a cylindrical body 86 and an annular web 88 extending substantially radially outwards from the middle of this body 86. The toothing 84 is separated into two series of chevron teeth 84d1, 84d2 which are located respectively on the axial ends of the body 86. The toothing 82 comprises two series of herringbone teeth 82d1, 82d2 which are located at the outer periphery of the veil 88 and which are separated from each other by an annular groove 89 opening radially towards the outside of the Y axis.
[0073] The toothing 82 is crossed in its middle by the plane H which passes through the groove 89, the teeth 82d1, 82d2 therefore being arranged on either side of the plane H. The teeth 84d1, 84d2 are also arranged symmetrically with respect to at the H plane.
[0074] The toothing 82 and the outer periphery of the veil 88 have an axial dimension which is less than the axial distance between the rings 90a, 90b, as well as between the flanges 122, so that each satellite 80 can freely rotate in the door. -crown 120 and between the rings 90a, 90b and the flanges 122.
[0075] The solution thus proposes to "symmetrize" the teeth of the satellites of the reducer in order to symmetrize the axial forces as well as the moments to which the satellites are subjected in operation. This solution also makes it possible to gain in length or axial dimension compared to a herringbone toothing by eliminating the inter-toothing groove of the meshing stage with the ring gear.
[0076] This solution is compatible with:
[0077] - "epicyclic" use with rotating planet gear carrier and fixed ring gear;
[0078] - "planetary" use with rotating crown and fixed planet carrier
[0079] - "differential" use with crown and rotating planet carriers.
[0080] - rolling element bearings and also hydrodynamic bearings
[0081] - a one-piece or multi-part satellite carrier.

权利要求:
Claims (10)
[0001]
Mechanical reduction gear (60) for a turbomachine (1), in particular an aircraft, this reduction gear comprising: - a solar (70) having an axis (X) of rotation, - a crown (90) which extends around the solar (70), - satellites (80) which are meshed with the solar (70) and the crown (90) and which are held by a planet carrier (100), each satellite (80) comprising a first toothing (82) of average diameter D1 for meshing with the sun gear (70), and a second toothing (84) of average diameter D2, different from D1, for meshing with the ring gear (90), characterized in that the first and second toothings (82, 84) of each satellite (80) have symmetry with respect to a plane (H) perpendicular to said axis (X) and passing substantially in the middle of the satellite (80), and in that each of the first and second toothings (82, 84) comprises herringbone teeth (82d1, 82d2, 84d1, 84d2), the chevron of the first toothing being formed by upstream teeth (82d1) of the first toothing ( 82) separated from downstream teeth (82d2) of the first set of teeth (82) being arranged on either side of the plane (H), and the upstream teeth (84d1) of the second set of teeth (84) being separated from the downstream teeth (84d2) of the second toothing (84) by the first toothing (82).
[0002]
Mechanical reduction gear (60) according to the preceding claim, in which the upstream teeth (82d1) of the first toothing (82) are separated by an annular groove (89) from the downstream teeth (82d2) of this first toothing (82).
[0003]
Mechanical reduction gear (60) according to one of the preceding claims, in which each satellite (80) comprises a cylindrical body (86) and an annular web (88) extending substantially radially outwards from the middle of this body ( 86), the teeth (84d1, 84d2) of the second toothing (84) being located at the axial ends of the body, and the teeth (82d1, 82d2) of the first toothing (82) being located at the outer periphery of the veil (88 ).
[0004]
Mechanical reduction gear (60) according to one of the preceding claims, in which the sun gear (70) comprises toothing with herringbone teeth and comprising upstream and downstream teeth (70a, 70b) located respectively on either side of said plane ( H).
[0005]
Mechanical reduction gear (60) according to one of the preceding claims, in which the ring gear (90) comprises toothing with herringbone teeth and comprising upstream and downstream teeth (90d1, 90d2) located respectively on either side of said plane ( H) and separated from each other by the second toothing (84).
[0006]
Mechanical reduction gear (60) according to the preceding claim, in which the teeth (90d1, 90d2) of the crown (90) are carried respectively by two rings (90a, 90b) one and the other fixed to a crown carrier ( 120).
[0007]
Mechanical reduction gear (60) according to the preceding claim, in which the crown carrier (120) has a generally biconical shape and substantially symmetrical with respect to said plane (H) which passes through the middle of the larger diameter of the crown carrier.
[0008]
Mechanical reduction gear (60) according to the preceding claim, in which the crown carrier (120) comprises at its ends bearings (124, 126) to guide the planet carrier (100) or a drive shaft of the planet carrier.
[0009]
Mechanical reduction gear (60) according to one of the preceding claims, in which the ring gear (90) is configured to be stationary in rotation around said axis (X), and the planet carrier (100) is configured to be mobile in rotation around of this axis.
[0010]
Turbomachine (1), in particular for an aircraft, comprising a mechanical reduction gear (60) according to one of the preceding claims.

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同族专利:

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引用文献:

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FR3111390A1|2020-06-11|2021-12-17|Safran Transmission Systems|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|

法律状态:
2020-03-18| PLFP| Fee payment|Year of fee payment: 2 |

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2020-10-23| PLSC| Publication of the preliminary search report|Effective date: 20201023 |

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2021-03-23| PLFP| Fee payment|Year of fee payment: 3 |

优先权:

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申请号 | 申请日 | 专利标题

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FR1904052A|FR3095251B1|2019-04-16|2019-04-16|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|

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FR1904052|2019-04-16|FR1904052A| FR3095251B1|2019-04-16|2019-04-16|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|

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JP2020072120A| JP2020176721A|2019-04-16|2020-04-14|Mechanical reduction gear of aircraft turbomachine|

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US16/848,642| US20200332721A1|2019-04-16|2020-04-14|Mechanical reduction gear of aircraft turbomachine|

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CN202010296519.4A| CN111828174A|2019-04-16|2020-04-15|Mechanical speed reducer for aircraft turbine|

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EP20169893.3A| EP3726031B1|2019-04-16|2020-04-16|Mechanical gear for aircraft turbine engine|