• 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 (1) with an aircraft reducer, comprising a first shaft (15) and a second shaft (3) having the same axis of rotation, the second shaft being rotated via a gearbox (7) by the first shaft, the first shaft being connected to the reducer by a connecting system comprising elastically deformable means conferring on the connection system a certain flexibility in operation, said deformable means comprising at least one annular bellows (16) extending around said axis, characterized in that said deformable means further comprise an annular pin (17) with a substantially U-shaped cross section, which extends around said axis.
    公开号:FR3075874A1
    申请号:FR1763045
    申请日:2017-12-22
    公开日:2019-06-28
    发明作者:Fabien Patrick Becoulet Julien；Jean-Marie Tan-Kim Alexandre
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    REDUCING TURBOMACHINE FOR AN AIRCRAFT
    TECHNICAL AREA
    The present invention relates to an aircraft reducer turbomachine.
    STATE OF THE ART The state of the art includes in particular document FR-A1 -2 979 121.
    A turbomachine, such as a turbofan engine, conventionally comprises an air inlet comprising a fan whose outlet air flow is divided into an air flow which enters the engine and forms a hot flow or flow primary, and in an air flow which flows around the engine and which forms a cold flow or secondary flow.
    The engine typically comprises from upstream to downstream, in the gas flow direction, at least one compressor, a combustion chamber, at least one turbine, and an exhaust nozzle in which the combustion gases leaving the turbine and forming the primary flow are mixed with the secondary flow. A turbomachine can also be of the “double-body” type, which means that it has two rotors arranged coaxially. A first body is called a low pressure body and a second body is called a high pressure body. In known manner, the engine comprises in this case, from upstream to downstream, a low pressure compressor, a high pressure compressor, the combustion chamber, a high pressure turbine and a low pressure turbine.
    In the case of a reducer turbomachine, the turbine shaft drives the fan shaft via the reducer which is lubricated and housed in a lubrication enclosure. Depending on the type of reduction gear used, planetary or planetary, the blower shaft will rotate in the same direction or in the opposite direction to the turbine shaft, and the blower shaft will rotate at a lower speed than that of the turbine shaft. The turbine shaft, which is the low pressure turbine shaft in the case of a double-body turbomachine, is generally coupled to a shaft of the low pressure compressor which is itself coupled to an input shaft of the reducer. This input shaft crosses the reducer and engages a solar of the latter.
    To ensure proper operation of this line of low pressure shafts and in particular of the reducer, it is necessary to transmit the torque but, at the same time, obtain a certain flexibility in the input shaft of the reducer so as not to disturb the operation of this line of shafts and internal elements of the reducer, but also to ensure proper alignment of the internal elements of the reducer.
    The flexibility values of the input shaft can be very high and the solution originally imagined was to make bellows on the shaft. However, to respect such high flexibility values, it would have been necessary to provide several adjacent bellows, which would result in excessive radial and axial dimensions and would prohibit its integration into the turbomachine.
    The present invention provides a simple, effective and economical solution to this problem by means of an optimized connection system between two trees or portions of trees.
    PRESENTATION OF THE INVENTION The invention proposes a turbomachine with an aircraft reducer, comprising a first shaft and a second shaft having the same axis of rotation, the second shaft being driven in rotation via a reducer by the first shaft, the first shaft. being connected to the reduction gear by a connection system comprising elastically deformable means giving the connection system a certain flexibility in operation, said deformable means comprising at least one annular bellows extending around said axis, characterized in that said deformable means comprise besides an annular pin with a substantially U-shaped section, which extends around said axis. The invention thus proposes to benefit from the combined advantages of the two technologies to give flexibility to the connection system. The U-shaped pin provides flexibility in the radial direction relative to the axis and makes it possible to limit the axial size of the system. The bellows give the flexibility in axial direction and in bending.
    The turbomachine according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: - the U-shaped pin defines an annular opening which opens in the axial direction; - The connection system comprises a portion of said first shaft and an input shaft for coupling this portion to said reduction gear; - The portion of said first shaft is formed in one piece with said first tree and comprises said at least one bellows; in other words, the invention proposes to integrate the bellows or bellows into the first shaft, which is for example a turbine or low pressure compressor shaft in the case mentioned above; this eliminates the connecting grooves of the shaft or of the shaft portion carrying the bellows to the low pressure shaft; - The portion of said first shaft has a generally tubular shape around said axis, and comprises a downstream part comprising said at least one bellows and a substantially cylindrical upstream part which is at least partly surrounded by said input shaft; - The upstream substantially cylindrical part comprises, preferably at an upstream end, splines for coupling to said input shaft; - Said input shaft forms said pin and comprises an external annular branch for coupling to said reduction gear, and an internal annular branch for coupling to the portion of said first shaft; the deformable means are therefore carried by the two shafts, the pin being formed by the input shaft and the bellows or the bellows being carried by the second shaft (the shaft of the low pressure compressor in the aforementioned example); - The branches are interconnected by an annular core having a thinning of thickness at its connection to said external branch; - The external branch has a downstream end located near an upstream end of said at least one bellows, and / or a diameter which is greater than an external diameter of said at least one bellows; this configuration makes it possible to limit the size, in particular axial, of the connection system; - At least one or some of the bellows can be surrounded by said external branch, to further limit the size of the system; - The internal branch extends upstream beyond the core and carries external annular wipers which cooperates by labyrinth effect with the internal periphery of an annular cover carried by said second shaft; this cover can participate in the sealing of the lubrication enclosure in which the gear unit is housed; - the number of bellows is more than two; - Said pin is located on one side of said reducer and said at least one bellows is located on the other side of said reducer and / or passes axially through said reducer; - The connection system comprises a portion of said first shaft and an input shaft comprising first splines for coupling this portion to the reducer; - Said substantially cylindrical upstream part comprises second splines for coupling to said input shaft; - Said at least one bellows extends radially between a diameter substantially equal to that of said first grooves and a diameter substantially equal to that of said second grooves; - Said first shaft is a low pressure compressor shaft.
    The present invention also relates to a method for mounting a turbomachine as described above, comprising the steps consisting in: - connecting said second shaft, which is a fan shaft, to an output shaft of said reduction gear and engaging axially on said blower shaft of the bearings as well as their support, - engage an input shaft axially inside said reducer, until the splines of this shaft cooperate with the splines of a sun gear reducer, - mount this assembly in an intermediate casing and fix it to this casing by appropriate means, - mounting means for supplying oil to said bearings, and - engaging said first shaft by axial translation in said input shaft until they are coupled by splines and fix the said bearing support to the intermediate casing.
    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: - the figure 1 is a schematic view in axial section of a turbomachine with an aircraft reducer, - FIG. 2 is a half schematic view on a larger scale of part of FIG. 1 and represents the technique prior to the invention, - Figure 3 is a view similar to that of Figure 2 and shows a schematic embodiment of the invention, - Figure 4 is an enlarged view of part of Figure 3 and illustrates a more concrete example of the invention, and - Figures 5 to 9 are views similar to that of Figure 3 and illustrate steps for mounting the turbomachine.
    DETAILED DESCRIPTION
    Referring to FIG. 1, a turbomachine 1 with reducer is seen, which conventionally comprises a blower S, a low pressure compressor 1a, a high pressure compressor 1b, a combustion chamber 1c, a high pressure turbine 1d and a low pressure turbine 1e. The rotors of the high pressure compressor 1b and the high pressure turbine 1d are connected by a high pressure shaft 5 and form with it a high pressure body (HP). The rotors of the low pressure compressor 1a and of the low pressure turbine 1e are connected by a low pressure shaft 4 and form with it a low pressure body (BP). The shaft 3 of the blower S is driven by means of a reduction gear 7 by the BP shaft 4
    The HP 5 and BP 4 shafts extend along an axis which is the axis of rotation of the turbomachine 1. In the following description, the concepts of longitudinal or radial, and interior or exterior, relate to this axis and the concepts of upstream and downstream refer to the flow of gases in the turbomachine.
    The turbomachine 1 comprises structural casings. The HP body is held by two structural casings: the inter-compressor casing and the inter-turbine casing, and the BP body is held by at least two structural casings: the intermediate casing 2 and the inter-turbine casing and / or the casing exhaust 6.
    The intermediate casing 2 supports bearings of the BP 4 turbine shaft which are housed in a front or upstream enclosure denoted E1. The exhaust casing 6 supports bearings of the BP turbine shaft 4 which are housed in a rear or downstream enclosure denoted E2.
    The reduction gear 7 is here of the epicyclic type. Figure 2 very schematically shows the size of the reducer. The reduction gear 7 comprises an input shaft 8 extending upstream of the BP shaft 4 and which is guided by a downstream bearing 10.
    More specifically, the input shaft 8 comprises an axial end, here upstream, engaged in the reducer 7 and meshed with a sun gear of the reducer, which is itself meshed with the satellites of the reducer. The input shaft 8 has its downstream end which is meshed with a shaft 15 of the low pressure compressor which is itself meshed with the shaft 4. The bearing 10 extends here around the shaft 15.
    The torque at the output of the reducer 7 is transmitted to the fan shaft 3, by a conventional connection, such as for example a fixing of this fan shaft on the planet carrier forming an output shaft of the reducer, in the case of an epicyclic reducer. In the case of a planetary gearbox, the fan shaft would be driven by the crown. The reducer is placed inside the front E1 lubrication enclosure. The E1 enclosure has fixed walls and movable walls. The fixed walls of the enclosure E1 comprise an internal wall of the stream of the primary flow, an upstream bearing support 11 and a downstream bearing support 12. The supports 11 and 12 extend towards the interior of the turbomachine and respectively carry the bearings 13, and the bearing 10. They provide the structure between the casings and the fixed outer rings of the bearings. The movable walls of the enclosure E1 include the input shafts 8 and the fan 3. The bearings 10, 13, 14 are housed in the enclosure E1. Seals, not visible in the diagrams, are provided between the fixed and movable walls and are, for example, labyrinth seals, brush seals, segmented radial seals, etc.
    The bearings 10, 13 and 14 as well as the reduction gear 7 are lubricated for their proper functioning. The oil is supplied by suitable means such as sprinklers, oil supply lines, etc. The bearing support 11 includes ventilation holes which allow ventilation air from the enclosure. The enclosure E1 is configured so that the air-oil mixture, which forms an oil mist inside the enclosure, is contained in the latter., Between the rotor and stator walls of the enclosure, for example here at the upstream and downstream ends of the enclosure, seals (such as labyrinths) are placed to contain the oil, and an air circuit pressurizes these seals to avoid oil leaks. The sealing means can be between a movable wall and a fixed wall of the enclosure or between two movable walls, as is the case for sealing between two shafts, and in particular between the shafts 3, 8 (visible in Figure 3). A gas flow is taken from the LP or HP compressor of the turbomachine and supplies all the seals of the enclosure E1. Chamber E1 is then pressurized (air enters continuously, repelling oil that could have come out of the seals by capillary action) and the bearings operate in a medium of oil and mixed air. The oil remains contained in the lubrication circuit. The bearings are supplied by a supply tube 25 and recovery is provided by a specific recovery tube generally placed at a low point of the enclosure. To avoid overpressure of the enclosure, and to allow a constant flow of incoming air, the interior of the enclosure is vented at a pressure lower than the pressure of the air entering the seals. This air laden with oil particles, which is exhausted at a pressure well, must first be treated to recover almost all of the oil it carries. For this, the oiled air will be brought to an oil separator which will separate the air from the oil it carries and will reject the oiled air outside the engine. This is the principle of removing oil from an enclosure.
    FIG. 2 represents the technique prior to the invention in which the input shaft 8 of the reduction gear 2 comprises elastically deformable means, here with bellows 16, conferring a certain flexibility on the shaft 8 and therefore on the connection system between the shafts 4, 15 and the reduction gear 7.
    However, to respect the high flexibility values of the shaft 8, it would be necessary to provide several adjacent bellows, which would result in excessive radial and axial bulk and would prohibit its integration into the turbomachine.
    FIG. 3 illustrates an embodiment of the invention in which the connection system between the shafts 4, 15 and the reduction gear 7 comprises deformable means with bellows 16 and with pin 17.
    Or the bellows 16 are here carried by a shaft portion 15a of the shaft 15, which is advantageously formed in one piece with the latter. The pin 17 is formed by the input shaft 8 and extends radially between the shaft portion 15a and the reducer 7.
    The bellows 16 can extend on one side of the reducer 7, here downstream, and the hairpin link can extend on the other side of the reducer, here upstream. As can be seen in FIG. 3, the bellows can extend partially radially inside the reducer 7.
    We now refer to FIG. 4 which represents a more concrete example of embodiment of the invention.
    The portion 15a of the shaft 15 has a generally tubular shape around the axis of the turbomachine, and comprises a downstream part 15ab comprising the bellows or bellows 16 and an upstream portion 15aa which is substantially cylindrical which is at least partly surrounded by the input shaft 8. This upstream part 15aa comprises, at an upstream end, coupling grooves 18 which are engaged in coupling grooves 19 complementary to the input shaft 8.
    In the example shown, the number of bellows 16 is greater than two. The bellows are preferably identical.
    The portion 15a comprises an external diameter defined by the maximum diameter DM of the bellows 16, and an internal diameter defined by the minimum diameter Dm of these bellows. The downstream part 15ab is connected to the rest of the shaft 15 by a cylindrical wall of maximum diameter DM, and the upstream part 15aa has a diameter Dm. The input shaft 8 comprises an external annular branch 8b for coupling to the reduction gear 7, and an internal annular branch 8a for coupling to the portion 15a of the shaft 15. The external branch 8b thus comprises grooves 20 of coupling to the solar gearbox and its internal branch 8a includes the aforementioned grooves 19.
    The branches 8a, 8b are connected together by an annular core 21 located upstream and having a thinning of thickness 22 at its connection to the external branch 8a. The core 21 may have in section a radial orientation, extending from downstream upstream radially outward.
    As can be seen in the drawings, the external branch 8b has a downstream end situated near an upstream end of the bellows 16. This external branch 8b has a diameter which is greater than the diameter DM. In the case where the number of bellows 16 is large, as in the example shown, or if these bellows have a large cumulative axial dimension, they can be housed in part at least in the annular space E delimited by the external branch 8b .
    Preferably, the internal branch 8a extends upstream beyond the core 21 and carries external annular wipers 23 which cooperate by labyrinth effect with the internal periphery of an annular cover 24 carried by the blower shaft 3 (see Figure 3). The wipers 23 thus form means of sealing the enclosure E1, here between the shafts 3 and 8.
    Reference is now made to FIGS. 5 to 9 which represent steps in mounting the turbomachine.
    The first step illustrated in FIG. 5 consists in connecting the blower shaft 3 to the output shaft of the reduction gear and in axially engaging on the blower shaft the bearings 13, 14 as well as their support 11. The shaft d input 8 of the reducer is then engaged axially inside the reducer, until its grooves 20 cooperate with those of the solar of the reducer (FIG. 6). The assembly is then mounted in the intermediate casing 2 of the turbomachine and is fixed to this casing by suitable means, for example by means of flanges 2a and a series of screw-nuts (FIG. 7).
    Means 25 for supplying oil to the enclosure E1 for lubricating the reduction gear 7 are then fitted (FIG. 8).
    Finally, the shafts 4 and 15 are engaged in axial translation from the downstream, the shaft 15 being intended to be engaged in the shaft 8 until their grooves 18, 19 engage with each other. The bearing support 12 is then fixed to the intermediate casing 2 by appropriate means, for example by means of flanges 2b and a series of screw-nuts (Figure 9).
    The deformable means according to the invention give optimized flexibility to the connection system between the shafts 4, 15 and the reduction gear 7, in particular in the axial, radial and bending directions. For example, the radial flexibility can be of the order of 2 × 10'8 m / N to 2.10'5 m / N and preferably 2.10'6 m / N, and the angular flexibility of the order of 4.10'5 at 3.10'7 and preferably 3x10'6 rad / Nm
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbomachine (1) with an aircraft reducer, comprising a first shaft (15) and a second shaft (3) having the same axis of rotation, the second shaft being driven in rotation via a reducer (7) by the first shaft , the first shaft being connected to the reduction gear by a connection system comprising elastically deformable means giving the connection system a certain flexibility in operation, said deformable means comprising at least one annular bellows (16) extending around said axis, characterized in that said deformable means further comprises an annular pin (17) of substantially U-shaped section, which extends around said axis.
    [2" id="c-fr-0002]
    2. Turbomachine (1) according to claim 1, wherein said pin (17) is located on one side of said reducer (7) and said at least one bellows (16) is located on the other side of said reducer and / or passes axially through said reducer.
    [3" id="c-fr-0003]
    3. Turbomachine (1) according to claim 1 or 2, wherein the connection system comprises a portion (15a) of said first shaft (15) and an input shaft (8) having first splines (20) for coupling of this portion to the reducer (7).
    [4" id="c-fr-0004]
    4. A turbomachine (1) according to claim 3, wherein the portion (15a) of said first shaft (15) has a generally tubular shape around said axis, and comprises a downstream part (15ab) comprising said at least one bellows (16) and an upstream portion (15aa) substantially cylindrical which is at least partially surrounded by said input shaft (8), said upstream portion (15aa) substantially cylindrical comprising second splines (18) for coupling to said input shaft ( 8).
    [5" id="c-fr-0005]
    5. A turbomachine (1) according to all of claims 3 and 4, wherein said at least one bellows (16) extends radially between a diameter (Dm) substantially equal to that of said first grooves (18) and a diameter ( DM) substantially equal to that of said second grooves (20).
    [6" id="c-fr-0006]
    6. Turbomachine (1) according to one of claims 3 to 5, in which said input shaft (8) forms said pin (17) and comprises an external annular branch (8b) for coupling to said reduction gear (7), and an internal annular branch (8a) for coupling to the portion (15a) of said first shaft (15).
    [7" id="c-fr-0007]
    7. A turbomachine (1) according to claim 6, in which the branches (8a, 8b) are interconnected by an annular core (21) having a thinning of thickness (22) at its connection to said external branch ( 8b).
    [8" id="c-fr-0008]
    8. A turbomachine (1) according to claim 7, in which the internal branch (8a) extends upstream beyond the core (21) and carries external annular wipers (23) which cooperate by labyrinth effect with the inner periphery of an annular cover (24) carried by said second shaft (3).
    [9" id="c-fr-0009]
    9. Turbomachine (1) according to one of the preceding claims, wherein said first shaft (15) is a low pressure compressor shaft.
    [10" id="c-fr-0010]
    10. Method for mounting a turbomachine according to one of the preceding claims, comprising the steps consisting in: - connecting said second shaft (3), which is a fan shaft, to an output shaft of said reduction gear (7) and axially engage bearings (13, 14) and their support (11) on said fan shaft, - engage an input shaft (8) axially inside said reduction gear, until splines (20) of this shaft cooperate with splines of a solar gearbox, - mount this assembly in an intermediate casing (2) and fix it to this casing by appropriate means, - mount means (25) for supplying oil to said bearings , and - engaging said first shaft (15) by axial translation in said input shaft (8) until they are coupled by splines (18, 19) and fixing said support (11) of the bearings (13, 14) to the intermediate casing (2).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20210087977A1|2021-03-25|
    CA3085815A1|2019-06-27|
    EP3728817A1|2020-10-28|
    RU2020120146A|2022-01-24|
    WO2019122740A1|2019-06-27|
    CN111566329A|2020-08-21|
    FR3075874B1|2019-11-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2979121A1|2011-08-18|2013-02-22|Snecma|MECHANICAL TRANSMISSION DEVICE FOR THE ROTATION DRIVE OF THE CONTRAROTATIVE PROPELLERS OF A DOUBLE PROPELLER TURBOPROPULSOR.|
    US20170159608A1|2015-12-07|2017-06-08|General Electric Company|Compliant shaft for turbine engines|
    EP3179056A2|2015-12-07|2017-06-14|United Technologies Corporation|Gear driven turbofan|
    FR3075860B1|2017-12-22|2019-11-29|Safran Aircraft Engines|DYNAMIC SEAL BETWEEN TWO ROTORS OF AN AIRCRAFT TURBOMACHINE|
    FR3086343B1|2018-09-24|2020-09-04|Safran Aircraft Engines|TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT|
    FR3107313B1|2020-02-14|2022-01-14|Safran Aircraft Engines|Tapered flexible input shaft|
    FR3108947A1|2020-04-01|2021-10-08|Safran Aircraft Engines|REDUCER MODULE FOR AN AIRCRAFT TURBOMACHINE|
    法律状态:
    2018-11-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-06-28| PLSC| Publication of the preliminary search report|Effective date: 20190628 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1763045A|FR3075874B1|2017-12-22|2017-12-22|REDUCING TURBOMACHINE FOR AN AIRCRAFT|
    FR1763045|2017-12-22|FR1763045A| FR3075874B1|2017-12-22|2017-12-22|REDUCING TURBOMACHINE FOR AN AIRCRAFT|
    EP18842431.1A| EP3728817A1|2017-12-22|2018-12-20|Aircraft turbomachine with reduction gearset|
    RU2020120146A| RU2020120146A|2017-12-22|2018-12-20|TURBOMACHINE WITH REDUCER FOR AIRCRAFT|
    PCT/FR2018/053443| WO2019122740A1|2017-12-22|2018-12-20|Aircraft turbomachine with reduction gearset|
    CA3085815A| CA3085815A1|2017-12-22|2018-12-20|Aircraft turbomachine with reduction gear|
    CN201880082577.8A| CN111566329A|2017-12-22|2018-12-20|Aircraft turbine with a retarder|
    US16/954,355| US20210087977A1|2017-12-22|2018-12-20|Aircraft turbomachine with reduction gearset|
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