• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Turbomachine, comprising at least one drive shaft having an axis of rotation A and configured to drive a blower wheel via an epicyclic gearbox (10), said gearbox comprising: - a sun gear (12) configured to be driven by said motor shaft (3) about said axis A, - a ring gear (16) surrounding the sun gear and configured to drive a fan shaft (4) about said axis A, and - an annular row of satellites (14) interposed between the sun gear and the ring gear and held by a planet carrier (20) fixed to a stator casing (22) of the turbomachine, said turbine engine further comprising an electrical equipment (30) with a rotor, characterized in that said electrical equipment ( 30) comprises a stator (30b) fixed to said stator housing (22) of the turbomachine via said planet carrier (20), and a rotor (30a) rotated by said sun gear (12).
    公开号:FR3054264A1
    申请号:FR1657125
    申请日:2016-07-25
    公开日:2018-01-26
    发明作者:Yann Le Pache Gwenole；Marc Michel Curlier Augustin；Clement Dupays
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to a turbomachine equipped with a planetary gear reducer.
    STATE OF THE ART
    A turbofan with double flow and double body generally comprises several stages of compressor, in particular a low pressure compressor (BP) and a high pressure compressor (HP), which are arranged in the primary flow stream of the engine. Upstream of the low-pressure compressor is a large, or blowing, moving blade wheel which feeds both the primary flow passing through the LP and HP compressors and the cold flow, or secondary flow, which is directed directly to a cold flow nozzle, called a secondary nozzle. The blower is driven by the rotation shaft of the LP body and generally rotates at the same speed as it. However, it may be advantageous to rotate the fan at a lower speed than that of the motor shaft or LP, in particular when the latter is very large, in order to better adapt it aerodynamically. For this, there is a reduction gear between the BP shaft and a blower shaft, which carries the blower.
    Among the types of reducers used are planetary gear reducers, which have the advantage of offering significant rates of reduction of the speed of rotation, in reduced dimensions. These reducers are characterized by a planetary gear which drives satellite pinions which roll on an outer ring while turning around axes of satellites carried by a planet carrier.
    Conventionally, an aircraft requires electrical and hydraulic energy from a turbomachine in addition to the thrust. On traditional turbomachinery, this power is taken mechanically from the HP shaft to drive the input shaft of an accessory box (AGB, Accessory Gear Box) placed on a casing of the turbomachine. This input shaft is rotated by a transmission shaft driven by a pinion secured to the HP shaft.
    The current trend is to increase the electrical power to be supplied to the aircraft, and therefore the mechanical power drawn from the engine. Previous studies have shown that a mechanical sample taken entirely from the HP shaft was too restrictive from an engine operability point of view. Indeed, a too high mechanical power drawdown has a negative effect on the operability of the HP body, especially when the engine is running at low speed. The solution of a mechanical sample distributed between the HP shaft and the BP shaft would largely restore engine performance and operability.
    Mechanical distribution solutions exist (planetary gear, AGB with two rotational speeds, clutch, etc. - see document FR-A1-2 882 096 for example) but are problematic because of the size of the resulting single generator and the complexity to pass the two speeds towards the space hosting this generator. Indeed, recent engines tend to have thin pods, which involves placing the AGB in the engine compartment (space between the primary and secondary veins). This area having a very constrained volume, it is difficult to install one or more large generators without impacting the lines of the secondary vein and therefore the fuel consumption of the engine. In addition, this area is close to the hot parts of the engine and therefore limits the life of the generators.
    One of the research axes of these engines is therefore to succeed in placing additional generators on the engine without impacting the aerodynamic lines. A generator can be "buried" in the turbomachine as in document W0-A1 -2007/036202, but at the cost of very complicated maintenance and severe environmental constraints. This is also the case for a generator installed in the rear or downstream cone of a turbomachine.
    One solution would be to install this generator in the blower, in the front or upstream cone. The problem with such an installation would be as follows: there is no fixed part on which to rest the stator in this space. The solutions would therefore be limited:
    • or make a rotating stator, connecting the stator (or the rotor) to the LP shaft and the other to the HP shaft. We can thus produce electricity, but it is problematic to get it out. In fact, the rotary contacts making it possible to pass from a rotating fix to a fixed fix are often complex or bulky or have a short lifespan. We could pass the harnesses inside the HP shaft, but that implies to make them go out by the rear cone and therefore to undergo its environmental constraints. In document FR-A1-3 017 413 for example, the equipment (a pump) is installed inside bearings supporting the blower, upstream of the reducer and upstream of the latter. The pump drive speed is the speed difference between the inlet and the outlet of the gear unit. The configuration of the reducer involves a fixed crown and a mobile planet carrier driving the fan in rotation;
    • or we manage to bring a casing element inside the front cone. The only way on a conventional engine would be to bring it from the rear of the engine through the HP shaft, but this has a number of drawbacks (stiffness, mass, and exposure to high temperatures in the rear cone).
    Another solution would be to add a structure fixing the front cone to the fan casing to hold the stator. In document FR-A1-2 919 896, a generator is mounted in the cone, the rotor of which is the LP shaft and the stator a fixed element of the fan cover. This cover is inaccessible from inside the front cone on a conventional engine. The solution described is the addition of radial holding arms between the front cone and the fan casing.
    The present invention provides in particular a simple, effective and economical solution to the above problem of the prior art, in the case of a planetary gearbox turbomachine.
    STATEMENT OF THE INVENTION
    The invention provides a turbomachine, comprising at least one motor shaft having an axis of rotation A and configured to drive a fan wheel by means of a planetary gear reducer, said reducer comprising:
    - a sun gear configured to be driven by said drive shaft around said axis A,
    a ring surrounding the sun gear and configured to drive a fan shaft around said axis A, and
    an annular row of satellites interposed between the sun gear and the crown and held by a planet carrier fixed to a stator casing of the turbomachine, said turbomachine further comprising electrical equipment with a rotor, characterized in that said electrical equipment comprises a stator fixed to said stator casing of the turbomachine via said satellite carriers, and a rotor driven in rotation by said sun gear.
    The invention applies to the specific case of a planetary gear reduction gearbox with a fixed planet carrier. The sun gear is rotated by the rotor shaft, which allows the crown to rotate with a reduction ratio corresponding to the ratio of the primary diameters of the crown and the sun gear. The equipment stator is connected to the stator housing of the turbomachine by the planet carrier. Its rotor is driven in rotation by the sun gear and is advantageously integral with the latter, so as to be driven by the rotor shaft of the turbomachine via the sun gear.
    The turbomachine according to the invention comprises one or more of the following characteristics, taken in isolation from one another or in combination with each other:
    - the rotor of the electrical equipment is integral in rotation with said sun gear;
    - said equipment is coaxial with said reduction gear, upstream thereof, and preferably extends substantially radially inside said blower shaft;
    - Said planetary comprises an upstream axial extension, preferably substantially frustoconical, one free upstream end of which comprises coupling means, preferably with domed grooves, with a corresponding free end of said rotor of the equipment;
    - Said equipment stator comprises a first annular flange for fixing to said planet carrier;
    - Said first flange is integrally connected, for example by means of an annular ring, preferably frustoconical, to first longitudinal ends of fingers of elongated shape whose opposite longitudinal ends are connected to a first annular element comprising a second annular flange of fixation ;
    - Said second flange is fixed to a third flange of a second annular element which is connected to first longitudinal ends of fingers of elongated shape for supporting said planet carrier;
    - Said second and third flanges are fixed by means of the screw type to an element integral with said stator housing of the turbomachine, which is preferably an intermediate housing;
    - Said equipment stator comprises at one longitudinal end said first flange and carries at a opposite longitudinal end a guide bearing;
    - Said guide bearing is mounted inside a substantially cylindrical ring which surrounds a sealing cover and comprises a fourth annular flange configured to be fixed to said fan shaft;
    said crown of the reduction gear is fixed to said shaft of said fan wheel.
    The present invention also relates to a method for dismantling electrical equipment with a rotor from a turbomachine as described above, characterized in that it comprises the steps consisting in:
    - remove the sealing cover and the ring, by axial translation on the side opposite the equipment,
    - remove the equipment, by axial translation on the side opposite the reducer.
    DESCRIPTION OF THE FIGURES
    The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:
    - Figure 1 is a very schematic half-view of a turbomachine,
    FIG. 2 is a simplified diagram representing the kinematics of operation of a planetary gear turbomachine,
    FIG. 3 is a partial schematic view in axial section of a turbomachine according to the invention,
    FIG. 4 is a partial schematic perspective view of a planetary gear reducer,
    FIG. 5 is a schematic perspective view of a support member for an equipment stator, and
    - Figure 6 is another partial schematic view in axial section of the turbomachine according to the invention.
    DETAILED DESCRIPTION
    Referring to Figure 1, we see a turbomachine 1 of the turbofan type with double flow and double body which comprises, conventionally, upstream and downstream (in the direction of gas flow along the longitudinal axis A of the turbomachine), a fan S, a low pressure compressor 1a, a high pressure compressor 1b, a combustion chamber 1c, a high pressure turbine 1 d, 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 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, also called a drive shaft, and form with it a low pressure body (BP).
    In the configuration shown which relates to a conventional turbojet, without reduction gear, the disc on which the blades of the blower S are mounted is driven by a blower shaft 4, or LP journal, which is itself driven directly by the BP shaft 3. In the case where a reduction gear is positioned between the BP shaft 3 and the fan shaft 4, the latter is, in known manner, a reduction gear with planetary gear.
    A planetary gear reducer (referenced 10 in FIG. 2) comprises a planetary gear 12 of axis A of rotation, which drives pinions or satellites 14 which roll on an outer ring 16 while turning around axes of satellites 18 carried by a door -satellites 20. In the configuration shown diagrammatically in FIG. 2, which shows the kinematics of operation of a turbomachine with planetary gear, the planet gear 12 is driven in rotation by the BP shaft 3, the planet carrier 20 is fixedly connected to a stator casing 22 (such as an intermediate casing) of the turbomachine, and the crown 16 rotates the fan shaft 4.
    FIG. 1 shows an example of an intermediate casing 22. This type of casing comprises a hub 22a and a ferrule 22b surrounding the hub and connected to the latter by substantially radial arms 22b passing through the streams 24, 25 of the primary and secondary flows, respectively . The primary flow or hot flow is that which flows inside the engine, from the BP compressor 1a to the BP turbine 1e and the nozzle 1h, and the secondary flow or cold flow flows around the engine. The air flow which enters the turbomachine and which passes through the blower S is divided by an annular separator 26 into a radially internal part which enters the LP compressor forming the primary flow, and into a radially external part which forms the flow secondary. A downstream extension 26a of the separator 26 is carried by the arms 22b of the intermediate casing.
    FIG. 3 represents an embodiment of a turbomachine according to the invention which, as in the case of FIG. 2, comprises a reduction gear 10 with planetary gear, of which:
    the sun gear 12 is rotated by a drive shaft of the turbomachine, in this case the BP shaft 3,
    the crown 16 rotates the fan shaft 4, and
    - the planet carrier 20 is fixed and integral with a stator housing of the turbomachine, which is the intermediate housing 22 in the example shown.
    The turbomachine further comprises electrical equipment 30 with rotor. The invention proposes to attach the stator 30b of this equipment 30 to the aforementioned stator housing (the intermediate housing 22 in the example) by means of the planet carrier 20, and to rotate the rotor 30a of this equipment. by connecting it to the sun gear 12. The rotor 30a of the electrical equipment 30 is preferably made integral in rotation with the sun gear 12 by a coupling link, that is to say that the rotor 30a and the sun gear 12 rotate at the same speed, as explained in the following with reference to the embodiment shown in FIG. 3.
    It nevertheless remains possible to provide a gear link between the rotor 30a and the sun gear 12, so that the rotor 30a rotates at a speed different from the speed of rotation of the sun gear 12 which is that of the motor shaft (l BP shaft 3) of the turbomachine. It may in particular be advantageous to drive the rotor of the electrical equipment at a speed greater than the speed of rotation of the LP shaft. The gear link can consist of a planetary gear train with fixed planet carrier, interposed between the reduction gear 10 and the electrical equipment 30, the crown of which is fixed to the sun gear 12 and the sun gear of which is fixed to the rotor 30a.
    With reference to the embodiment shown in FIG. 3, the sun gear 12 has an elongated tubular shape and comprises a downstream portion 12a substantially cylindrical and of axis A of revolution, and an upstream portion 12b coaxial substantially frustoconical. Portion 12b widens from upstream to downstream. The downstream portion 12a comprises internal longitudinal splines 12aa intended to cooperate by meshing with complementary splines of the BP shaft 3 or of a coupling shaft between the sun gear and the BP shaft. The upstream portion 12b comprises at its free upstream end of smaller diameter internal rectilinear grooves 12ba intended to cooperate by meshing with grooves 30aa complementary to a longitudinal downstream end of the rotor 30a of the equipment 30. The grooves
    12ba and 30aa are preferably of the domed type so as to allow misalignments between the sun gear 12 and the rotor 30a of the equipment 30 in operation. These domed grooves do not require an axial stop device.
    The downstream portion 12a also comprises external grooves 12ab for meshing with the satellites 14 which themselves mesh with the crown 16. The crown 16, the satellites 14 and the downstream portion 12a of the sun gear are stacked one inside the others in a substantially radial plane with respect to the axis A.
    The satellites 14 can be three, four or five, or even more, for example. Each satellite 14 is mounted in rotation on an axis 18 which is carried by the planet carrier 20, which is fixed to it.
    FIG. 4 shows an example (partially shown) of a reduction gear 10 to five satellites 14. The planet carrier 20 has an annular shape and comprises housings for receiving the satellites 14 and which are crossed by the axes 18. Between two satellites 14 adjacent, the planet carrier 20 comprises a transverse rib 20a in which is formed an axial orifice 20aa (Figures 3 and 4). The set of ribs 20a of the planet carrier form an annular collar. In the example shown, the axes 18 of the satellites 14 are located on a circumference C1 of diameter less than the circumference C2 passing through the orifices 20aa of the ribs 20a, the diameter of the circumference C2 being less than the diameter of a circumference C3 passing by the outer periphery of the planet carrier and the satellites.
    As mentioned in the foregoing, the planet carrier 20 is here fixed. It is fixed to the casing, intermediate 22 in the above example, by means of a first annular member 40 visible in FIGS. 3 and 4.
    This first member 40 comprises a downstream annular element 40a which comprises a radially internal annular flange 40aa. The first member 40 further comprises an annular row of longitudinal fingers 40b, which extend upstream in the extension of the external periphery of the annular element 40a. Each finger 40b passes through one of the aforesaid orifices 20aa ίο of the planet carrier 20 and can be retained in the latter by appropriate means. The number of fingers 40b is therefore equal to the number of orifices 20aa, which is equal to the number of satellites 14.
    The annular flange 40aa is applied axially against an annular flange 42 of the intermediate casing 22, or of an annular element 22d, integral with the latter (Figure 3) and for example integral with its hub 22a. The flanges 40aa, 42 are fixed to each other by means of the screw-nut type, not shown.
    A second annular member 44 is fixed to these flanges 40aa, 42. This second member 44, visible in FIGS. 3 and 5, serves to support the stator 30b of the equipment 30. It comprises a downstream annular element 44a which comprises an annular flange radially internal 44aa. The second member 44 further comprises an annular row of longitudinal fingers 44b, which extend upstream in the extension of the external periphery of the annular element 44a. In the example shown, the second member 44 comprises three longitudinal fingers 44b, and is thus adapted for a reduction gear 10 comprising three satellites 14. Each finger 44b comprises at its upstream free longitudinal end a fixing lug 44bb in the form of a sector or segment flange.
    The fingers 44b are located on a circumference C4 of diameter smaller than that of the circumference C1.
    The flange 40aa is interposed between the flanges 44aa and 42. The fixing lugs 44bb of the fingers 44b are applied axially on an radially external annular flange 46b of a frustoconical ferrule 46. The ferrule 46 extends around the axis A in upstream of the reducer 10. It widens from upstream to downstream. The flange 46a is located at the downstream end of the ferrule 46, and its upstream end comprises another radially external annular flange 46a for fixing to the stator 30b of the equipment 30.
    The equipment 30 has a generally cylindrical shape of axis A. It is therefore coaxial with the reducer 10 and mounted here upstream of the latter. The stator 30b surrounds the rotor 30a in the example shown. The rotor 30a can be directly guided inside the stator, for example by a system of the plain bearing type. Alternatively, it can be guided and held in position axially by bearings. The stator 30b has a tubular shape and comprises at its downstream end an annular flange 30bb to which is applied axially and fixed, by means of the screw-nut type or the like, the flange 46a of the ferrule 46.
    The stator 30b comprises at its upstream end an external cylindrical surface for mounting a bearing 48 for supporting the equipment 30. The bearing 48 comprises an internal ring mounted on the stator 30b and an external ring integral in rotation with a ring 50. This bearing eliminates the overhang on the stator of the equipment.
    This ring 50 extends around the upstream end of the equipment 30 and is fixed to the fan shaft 4. The ring 50 comprises at its upstream end a radially external annular flange 50a applied axially from upstream on a radially internal annular flange 4a of the blower shaft
    4. The flanges 4a, 50a are fixed to each other by means of the screw-nut type for example.
    A cover 52 with a substantially circular periphery is engaged inside the ring 50, from upstream, and comprises at its periphery annular sealing means intended to cooperate with an internal cylindrical surface 50b of the ring 50, located upstream of the bearing 48. The cover 52 is coaxial with the equipment 30 and comprises substantially at its center a recess 54 intended to cooperate with a tool for mounting / dismounting the cover, by translation along the axis A.
    It can be seen in FIGS. 3 and 6 (the assembly composed of the reduction gear 10, the equipment 30, the ring 50 and the cover 52 being schematically represented by a rectangle 60 in FIG. 6) that the portion of the shaft fan 4, located upstream of the flanges 4a, 50a, has a diameter greater than the flange 50a and the cover 52.
    Figures 3 and 6 show that the disassembly of the upstream cone 54 (Figure 6) of the turbomachine, allows access to the cover 52 on the one hand, for its extraction by axial translation upstream, and than to the ring 50 and to the bearing 48, which can also be removed together by axial translation upstream after having disengaged the flanges 4a, 50a. It then suffices to separate the flanges 30bbn, 46a in order to be able to remove the equipment 30 by axial translation upstream, the coupling by the splines 30aa, 12ba allowing this disassembly.
    Figure 6 further shows that the equipment is housed radially inside the fan shaft 4 and at least partially inside the fan S.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbomachine (1), comprising at least one motor shaft (3) having an axis of rotation A and configured to drive a fan wheel (S) by means of a reduction gear (10) with planetary gear, said reduction gear comprising:
    - a sun gear (12) configured to be driven by said drive shaft (3) around said axis A,
    a crown (16) surrounding the sun gear and configured to drive a fan shaft (4) around said axis A, and
    - An annular row of satellites (14) interposed between the sun gear and the crown and held by a planet carrier (20) fixed to a stator housing (22) of the turbomachine, said turbomachine further comprising electrical equipment (30) with rotor, characterized in that said electrical equipment (30) comprises a stator (30b) fixed to said stator housing (22) of the turbomachine via said planet carrier (20), and a rotor (30a) driven in rotation by said planetary (12).
    [2" id="c-fr-0002]
    2. Turbomachine (1) according to claim 1, characterized in that the rotor (30a) of the electrical equipment (30) is integral in rotation with said sun gear (12).
    [3" id="c-fr-0003]
    3. Turbomachine (1) according to claim 1 or 2, characterized in that said equipment (30) is coaxial with said reduction gear (10), upstream thereof, and extends substantially radially inside said shaft. blower (4).
    [4" id="c-fr-0004]
    4. Turbomachine (1) according to claim 2 or 3, characterized in that said planetary (12) comprises an upstream axial extension, preferably substantially frustoconical, one free upstream end of which comprises coupling means with a corresponding free end of said rotor (30a) of the equipment (30).
    [5" id="c-fr-0005]
    5. Turbomachine (1) according to one of the preceding claims, characterized in that said stator (30b) of the equipment (30) comprises a first annular flange (30bb) for fixing to said planet carrier (20), said first flange (30bb) being integrally connected to first longitudinal ends of fingers (44b) of elongated shape whose opposite longitudinal ends are connected to a first annular element (44a) comprising a second annular flange (44aa) for fixing.
    [6" id="c-fr-0006]
    6. Turbomachine (1) according to the preceding claim, characterized in that said second flange (44aa) is fixed to a third flange (40aa) of a second annular element (40a) which is connected to first longitudinal ends of fingers ( 40b) of elongate support form of said satellite carriers (20).
    [7" id="c-fr-0007]
    7. Turbomachine (1) according to the preceding claim, characterized in that said second and third flanges (40aa, 44aa) are fixed by means of the screw-nut type to an element (22d) integral with said stator housing of the turbomachine, which is preferably an intermediate casing (22).
    [8" id="c-fr-0008]
    8. Turbomachine (1) according to one of claims 5 to 7, characterized in that said stator (30b) of the equipment comprises at a longitudinal end said first flange (30bb) and carries at a opposite longitudinal end a bearing of guide (48).
    [9" id="c-fr-0009]
    9. Turbomachine according to the preceding claim, characterized in that said guide bearing (48) is mounted inside a ring (50) substantially cylindrical which surrounds a sealing cover (52) and comprises a fourth annular flange (50a) configured to be fixed to said blower shaft (4).
    [10" id="c-fr-0010]
    10. Method for dismantling electrical equipment (30) with rotor of a turbomachine (1) according to the preceding claim, characterized in that it comprises the steps consisting in:
    - remove the sealing cover (52) and the ring (50), by axial translation on the side opposite to the equipment (30), and remove the equipment, by axial translation on the side opposite to the reducer (10).
    1/4
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    同族专利:
    公开号 | 公开日
    US10422286B2|2019-09-24|
    FR3054264B1|2020-07-03|
    US20180023483A1|2018-01-25|
    引用文献:
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    WO2021009436A1|2019-07-16|2021-01-21|Safran Transmission Systems|Epicyclic reduction gear for a turbomachine|
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    FR3090049B1|2018-12-12|2021-01-15|Safran Aircraft Engines|TURBOMACHINE INCLUDING AN ALTERNATOR BETWEEN TWO CONTRAROTARY ELEMENTS|
    GB201820399D0|2018-12-14|2019-01-30|Rolls Royce Plc|Planet carrier and method of assembling of a planet carrier|
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    法律状态:
    2017-04-26| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-26| PLSC| Search report ready|Effective date: 20180126 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1657125A|FR3054264B1|2016-07-25|2016-07-25|REDUCING TURBOMACHINE WITH EPICYCLOIDAL TRAIN|
    FR1657125|2016-07-25|FR1657125A| FR3054264B1|2016-07-25|2016-07-25|REDUCING TURBOMACHINE WITH EPICYCLOIDAL TRAIN|
    US15/658,243| US10422286B2|2016-07-25|2017-07-24|Turbine engine with epicyclic reduction gear train|
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