• 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 (10) of an aircraft with mechanical reduction gear (42) and with counter-rotating turbine (22), comprising a fan (12) driven in rotation by a fan shaft (39), a mechanical reduction gear (42) with planetary gear, a gas generator comprising a counter-rotating turbine (22), a first turbine shaft (36) of which is coupled to an input shaft (36a) of the reduction gear and to a journal (90), and of which a second shaft (38) of the turbine is coupled to the fan shaft, characterized in that the guiding of the reduction gear input shaft is ensured by a first ball bearing (60), the guiding of the journal is ensured by a second roller bearing (48), and the guiding of the first shaft (36) is ensured in particular by a third roller bearing (52) interposed axially between said first and second bearings.
    公开号:FR3087226A1
    申请号:FR1859406
    申请日:2018-10-10
    公开日:2020-04-17
    发明作者:Ghislain Albert Levisse Paul；Olivier BELMONTE；Olivier Formica；Francois Gallet
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    AIRCRAFT TURBOMACHINE WITH A MECHANICAL REDUCER AND A CONTRAROTATIVE TURBINE
    TECHNICAL AREA
    The present invention relates in particular to a turbomachine with a counter-rotating turbine for an aircraft.
    STATE OF THE ART
    Conventionally, an aircraft turbomachine comprises from upstream to downstream, in the direction of flow of the gases, a blower, a low pressure compressor, a high pressure compressor, an annular combustion chamber, a high pressure turbine and a low pressure turbine. The rotor of the low pressure compressor is driven by the rotor of the low pressure turbine, and the rotor of the high pressure compressor is driven by the rotor of the high pressure turbine.
    From an engine performance and consumption point of view, it is advantageous to maximize the rotation speed of the low pressure turbine as this allows better efficiency of the turbine to be obtained. However, increasing the speed of rotation of the turbine implies increasing the centrifugal forces which it undergoes, and therefore greatly complicates its design.
    One suggestion for increasing the efficiency of the turbine without increasing its speed of rotation consists in equipping the turbomachine with a counter-rotating turbine, as described in document FR-A1-2 942 273. The low pressure turbine is then replaced by a turbine with two rotors of which a first rotor is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor is configured to rotate in an opposite direction of rotation and is connected to a second shaft of rotation turbine. The first rotor has wheels interposed between wheels of the second rotor.
    A low pressure turbine can have a maximum rotation speed of 4,000 revolutions per minute in a conventional architecture where the turbine directly drives the blower to 10,000 revolutions per minute in an architecture where the turbine drives the blower via a reducer. Its replacement by a counter-rotating turbine whose rotors rotate respectively at maximum speeds of 3,000 and 7,000 rpm allows a relative speed of 10,000 rpm (3000 +7000) while having an absolute speed in a low range of the aforementioned speed interval.
    This counter-rotating turbine thus comprises a slow rotor and a fast rotor, the slow rotor driving the blower and the fast rotor driving the low pressure compressor and meshing with a mechanical reduction gear with planetary gear.
    The reducer connects the fast rotor and the slow rotor, thus allowing a transfer of power from the fast rotor to the slow rotor. This provides the benefits of a fast low pressure compressor, while providing energy to the blower.
    This architecture is complex due to its mechanical integration: the mechanical reducer is located upstream from the low pressure compressor.
    In the state of the art, this positioning of the reducer involves placing numerous bearings and oil recovery chambers inside the low pressure compressor. Furthermore, the two shafts of the counter-rotating turbine extend along and inside the engine, from downstream of the turbomachine where the counter-rotating turbine is located, upstream of the turbomachine where the reducer. These trees pass through very constrained areas. Finally, the assembly and disassembly of such an engine is particularly complex.
    STATEMENT OF THE INVENTION
    The present invention provides an improvement to the technology described above, which represents a simple, effective and economical solution to at least some of the problems mentioned above.
    According to a first aspect, the invention relates to a system for fixing a shaft of a counter-rotating turbine for an aircraft turbomachine, characterized in that it comprises:
    a first substantially tubular turbine shaft extending along and around an axis X, this first turbine shaft comprising at a free end, called the upstream end by reference to the flow of gases in the turbomachine, an upstream portion screw connection with external thread, and a downstream coupling portion,
    a compressor journal which is mounted on said free upstream end of the first turbine shaft and is configured to cooperate with said coupling portion so as to be rotatably integral with the first turbine shaft, and
    - a journal blocking nut on the first turbine shaft, this nut comprising an upstream gripping section configured to be engaged with a screwing / unscrewing tool of the nut, and an intermediate screwing section with configured internal thread to cooperate with said upstream portion, said nut being configured to bear axially on said pin when it is in a screwed and tight position, and to be held radially by pressing on said pin and / or said first turbine shaft when it is in a completely unscrewed position.
    The invention thus provides a concrete and reliable solution for mounting / dismounting a turbomachine with a counter-rotating turbine. The nut is designed to facilitate this mounting. It is able to cooperate with the surrounding parts to trap it in a cavity during an assembly / disassembly phase, which is particularly advantageous for this type of assembly and disassembly operations, which can often be carried out blind. The nut preferably remains trapped in the cavity until the first tree is removed. Its arrangement makes it possible to have two coaxial shafts with very close diameters while allowing disassembly by functional sub-assemblies.
    The system according to the invention may include one or more of the characteristics below, taken in isolation from each other or in combination with each other:
    - at least one of the elements among the nut and the first shaft comprises a portion or a retaining section capable of cooperating with the other of the elements to ensure the radial retention of the nut in the unscrewed position,
    - the said journal is integral in rotation with an input shaft of a mechanical reduction gear with planetary gear,
    - a second turbine shaft extends coaxially inside said first shaft and comprises at its upstream end a coupling portion with a fan shaft,
    - at least one bearing is mounted between said journal and / or said input shaft, on the one hand, and said fan shaft, on the other hand,
    - Said journal comprises a cylindrical wall which is complementary to said coupling portion, and a radial wall of the journal which comprises or carries a first cylindrical rim oriented downstream and delimiting an annular space configured to receive oil from at least one nozzle, the radial wall comprising a series of through orifices at the bottom of this space so as to allow the passage of oil from downstream to upstream of the radial wall, inside an enclosure lubrication of at least one bearing,
    - said nut comprises external annular wipers of a first labyrinth seal,
    said first seal provides a seal for said enclosure in which said at least one bearing is located,
    - said radial wall comprises or carries a second cylindrical rim oriented upstream and delimiting an annular space configured to receive oil leaving said orifices and to convey this oil axially upstream,
    said at least one bearing comprises an internal ring comprising or carrying a third cylindrical rim oriented downstream and at least partially surrounding said second rim, and delimiting an annular space configured to receive oil conveyed by said second rim, the internal ring comprising channels for circulation of this oil up to bearings of said at least one bearing,
    - Said radial wall comprises or carries a third cylindrical rim oriented upstream and comprising external annular wipers of a second labyrinth seal, these wipers cooperating with a layer of abradable material carried by an outer ring of said at least a step.
    The present invention also relates to an aircraft turbomachine, comprising a system as described above.
    According to a second aspect, the invention relates to an aircraft turbomachine with mechanical reducer and counter-rotating turbine, comprising:
    - a fan driven in rotation by a fan shaft,
    - a mechanical reduction gear with planetary gear,
    - a gas generator comprising a counter-rotating turbine, a first turbine shaft of which is coupled to the fan shaft as well as to an output shaft of the reduction gear, and of which a second turbine shaft is coupled to an inlet shaft of the reducer as well as a journal of a low pressure compressor of the gas generator, characterized in that:
    - the guiding of the reduction gear input shaft is ensured by a first ball bearing located downstream of the reduction gear, between this input shaft and an input casing,
    the trunnion is guided by a second roller bearing mounted between this trunnion and an intermediate casing of the turbomachine, and
    - The guidance of the first shaft is ensured in particular by a third roller bearing interposed axially between said first and second bearings, and located between this first shaft and said input shaft.
    The invention thus provides an optimal arrangement of the bearings in a turbomachine with a counter-rotating turbine and a reduction gear.
    The turbomachine according to the invention may include one or more of the characteristics below, taken in isolation from one another or in combination with each other:
    - the guiding of the fan shaft and the output shaft is ensured by an upstream bearing (fourth bearing) with rollers and by a downstream bearing (fifth bearing) with ball bearings, these bearings being located upstream of the reduction gear, between the fan and output shafts, on the one hand, and the inlet casing, on the other hand,
    said first bearing has an average diameter greater than the average diameter of said second bearing, which is itself greater than the average diameter of said third bearing,
    - said pin is engaged on said first shaft and immobilized axially thereon by means of a first nut screwed onto said first shaft,
    - said fan shaft and said output shaft are immobilized axially on said second shaft by means of a second nut screwed onto said second shaft,
    - Said first shaft is connected at its downstream end to a first turbine rotor, and said second shaft is connected at its downstream end to a second turbine rotor, said first turbine rotor comprising wheels interposed between wheels of the second rotor turbine, and
    - Said first and second turbine rotors are surrounded by a casing, one downstream end of which comprises a flange for fixing to an exhaust casing of the turbomachine.
    The invention also relates to a method for dismantling a turbomachine as described above, comprising the steps of:
    a) disassembly and removal of an inlet cone of the turbomachine, located upstream and in the center of the fan,
    b) unscrewing the second nut by means of a tool inserted inside said second shaft from the upstream end of the turbomachine,
    c) disassembly of said second shaft and removal of this second shaft from the downstream end of the turbomachine,
    d) unscrewing the first nut by means of a tool inserted inside said first shaft from the upstream end of the turbomachine, and
    e) disassembly of said first shaft and removal of this first shaft from the downstream end of the turbomachine.
    Step c) may comprise the disassembly and removal of the exhaust casing, then the disassembly and removal of at least part of said second rotor, on the one hand, and said second shaft, on the other hand, the removal of at least a portion of said second rotor and of said second shaft being produced simultaneously or successively, and
    Step e) may comprise the disassembly and removal of at least a portion of said first rotor, on the one hand, and said first shaft, on the other hand, the removal of at least a portion of said first rotor and said first tree being produced simultaneously or successively,
    Said first nut can be mounted on said first shaft and is intended to remain on this first shaft after it is unscrewed in step d).
    DESCRIPTION OF THE FIGURES
    The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings in which:
    FIG. 1 is a schematic view in axial section of a turbomachine with a reduction gear and a counter-rotating turbine according to the invention,
    FIG. 1a is a schematic view in axial section, on a larger scale and in more detail, of part of the turbomachine of FIG. 1,
    FIGS. 2a and 2b are schematic views in axial section and on a larger scale of a fastening system according to the invention,
    - Figures 3 to 9 are views similar to that of Figure 1 and illustrate steps of a disassembly process according to the invention,
    - Figures 4a, 7a, 8a and 9a are views similar to that of Figure 1a as part of the process steps.
    DETAILED DESCRIPTION
    FIG. 1 very schematically represents a turbomachine 10 with a counter-rotating turbine and with a reduction gear for an aircraft.
    This turbomachine 10 comprises from upstream to downstream, in the direction of flow of the gases, a fan 12, a low pressure compressor 14, a high pressure compressor 16, an annular combustion chamber 18, a high pressure turbine 20 and a turbine counter-rotating 22.
    The reference 23 designates an inlet casing situated between the blower 12 and the compressor 14. The reference 24 designates an intermediate casing situated between the compressors 14 and 16, and the reference 26 designates a turbine casing (of the TVF type) situated between the turbines 20 and 22. Finally, the reference 28 designates an exhaust casing (of the TRF type).
    The rotor of the high pressure turbine 20 rotates the rotor of the high pressure compressor 16 by a high pressure shaft 30 which is centered and guided in rotation by bearings, such as an upstream bearing 32 with balls and a downstream bearing 34 to rollers. The bearing 32 is mounted between an upstream end of the shaft 30 and the intermediate casing 24, and the bearing 34 is mounted between a downstream end of the shaft 30 and the turbine casing 26.
    The counter-rotating turbine 22 comprises a first rotor 22a whose wheels 22aa are configured to rotate in a first direction of rotation and are connected to a first turbine shaft 36, and a second rotor 22b whose wheels 22ba are configured to rotate in one direction opposite in rotation and are connected to a second turbine shaft 38. The wheels 22ba are interposed between the wheels 22aa.
    The first and second rotors 22a, 22b are surrounded by a casing 29, one downstream end of which comprises a flange for fixing to the exhaust casing 28.
    The first shaft 36 extends axially inside the shaft 30 and rotates the rotor of the low pressure compressor 14. This first shaft 36 is also coupled to an input shaft 36a which is meshed with a solar or planetary of a mechanical reduction gear 42 with planetary gear. The input shaft 36a is thus integral in rotation with the shaft 36.
    The second shaft 38 extends axially inside the shaft 36 and drives the fan 12 in rotation. This shaft 38 is coupled to a fan casing 39 as well as to an output shaft 38a which is meshed with the reduction gear crown 42.
    The reduction gear 42 further comprises satellites meshed respectively with the sun and the crown and carried by a satellite carrier 42a which is fixed to the input casing 23.
    The first shaft 36 is centered and guided upstream by a bearing 48 mounted between the first shaft 36 and the intermediate casing 24, and downstream by a bearing 50 shown between the first shaft 36 and the turbine casing 26.
    The second shaft 38 is centered and guided upstream by a bearing 52 mounted between the second shaft 38 and the first shaft 36, and downstream by a bearing 54 shown between the second shaft 38 and the exhaust casing 28 .
    The bearings 50 and 54 are roller in the example shown.
    The fan shaft 39 and the output shaft 38a are guided by an upstream bearing 56 with rollers and by a downstream bearing 58 with balls. These bearings 56, 58 are located upstream of the reduction gear 42, between the fan 39 and outlet 38a shafts, on the one hand, and the inlet casing 23, on the other hand. Downstream of the reduction gear 42, a bearing 60 rotates the input shaft 36a and is mounted between this shaft and the input casing 23.
    Figure 1a is an enlarged and more detailed view of the zone Z of Figure 1 and allows a better view of the bearings 48, 52 and 60 and their respective positions.
    The second shaft 38 comprises at an upstream end an upstream portion 62 of screwing with external thread and a downstream portion 64 of coupling with external rectilinear grooves.
    The fan shaft 39 and the output shaft 38a are fixed to each other or formed in one piece and include a downstream end which comprises a downstream portion 66 of coupling with internal rectilinear grooves. The portions 64, 66 are configured to cooperate together by complementarity of shapes in order to secure in rotation the shafts 38a, 39 and 38.
    This downstream end of the fan 39 and outlet 38a shafts comprises an annular flange 68 oriented radially inwards and intended to be clamped axially (directly or indirectly) against a cylindrical shoulder of the shaft 38, by means of a nut. 70 with internal thread screwed on the portion 62 from upstream. This nut 70 is called a “second” nut because it is attached to the second shaft 38.
    The portion 66 further comprises a downstream wall 72 extending radially outward and carrying at its outer periphery an internal ring 52a of the roller bearing 52.
    The first shaft 36 comprises an upstream end which comprises a downstream portion 84 of coupling with external rectilinear grooves, an intermediate screwing portion 86 with external thread, and an upstream retaining portion 88 substantially cylindrical, these portions 84, 86, 88 being better visible in Figures 2a and 2b.
    A journal 90 of the low pressure compressor 14 is mounted on the upstream end of the first shaft 36 and comprises rectilinear internal grooves configured to cooperate with the coupling portion 84 to be integral in rotation with the first shaft 36.
    A nut 92 for locking the journal 90 called “first” nut because it is attached to the first shaft 36, comprises an upstream gripping section 92a configured to be engaged with a screwing / unscrewing tool of the nut, a section screwing intermediate 92b with internal thread configured to cooperate with the intermediate portion 86, and a downstream retaining section 92c which is here substantially cylindrical (FIGS. 2a and 2b).
    FIG. 2a shows the nut 92 in its screwed and tight position for blocking the journal 90. The nut 92 bears axially on the journal 90 and immobilizes it axially on the shaft 36. FIG. 2b shows the nut 92 in its completely unscrewed position, when the threads of the nut and of the portion 86 are not engaged one in the other. In this position, the nut 92 is held radially by pressing its downstream section 92c on the journal 90 and / or the first shaft 36. In the example shown, the nut 92 is also held radially by pressing its section 92b on portion 88 of tree 36.
    The nut 92 comprises external annular wipers 92d of a first labyrinth seal. In the clamping position of FIG. 2a, the wipers 92d are surrounded by an annular layer 94 of abradable material and its able to cooperate by friction in operation with it. In the example shown, the layer 94 is carried by a cylindrical rim 52aa oriented towards the downstream of the inner ring 52a of the bearing 52.
    The journal 90 comprises a cylindrical coupling wall 90a comprising the internal splines for coupling to the shaft 36, as well as a radial wall 90b which extends radially outwards from the upstream end of the wall 90a and which comprises or carries a first cylindrical rim 90ba oriented downstream and internally delimiting an annular space E1 configured to receive oil from at least one nozzle 96 (FIG. 1a).
    The radial wall 90b has a series of through holes 90bb1 at the bottom of this space E1 so as to allow the passage of oil from downstream to upstream, inside a lubrication enclosure of the bearing 52.
    The orifices 90bb1 open upstream in another annular space E2 which is part of the lubrication enclosure and which is delimited internally by a second cylindrical rim 90bc oriented upstream from the wall 90b, or from an attached element on the wall 90b.
    As is better visible in FIG. 2b, the upstream end of this rim 90bc surrounds the downstream end of the rim 52aa of the inner ring 52a, and is itself surrounded by the downstream end of another cylindrical rim 52ab downstream of the inner ring 52a. The flanges 52aa, 52ab define between them another annular space E3.
    The oil sprayed by the nozzle into space E1 is intended to circulate in the orifices 90bb1 to reach space E2. This oil then flows due to centrifugal forces along the rim 90bb then the rim 52ab, in space E3. It then reaches channels 52ac of the internal ring 52a visible in FIG. 2b, in order to join the bearings of the bearing 52 and ensure their lubrication.
    The first seal formed by the wipers 92d and the layer 94 seals the lubrication enclosure of the bearing 52, which is also ensured by a second seal visible in FIG. 1a and provided between a another cylindrical rim 90bc oriented upstream from the radial wall 90b, which extends around the rim 90bb, and an outer ring 52b of the bearing 52. This second seal comprising external annular wipers carried by the rim 90bc and cooperating with a layer of abradable material carried by the outer ring 52b.
    At its outer periphery, the pin 90 comprises a first annular ring 97 of generally frustoconical shape, flared downstream, and carrying or forming at its outer periphery an inner ring of the bearing 48, the outer ring of which is carried by or formed at the internal periphery of an annular bearing support 98 fixed to the intermediate casing 24. A labyrinth seal 99 may also be provided between the ferrule 97 and the intermediate casing 24.
    At its outer periphery, the journal 90 further comprises a second annular ferrule 100 of generally frustoconical shape, flared upstream, and carrying a radially external annular flange for fixing to the rotor of the low pressure compressor 14, on the one hand, thus than the input shaft 36a of the reducer, on the other hand.
    The input shaft 36a comprises a downstream end which is configured, on the one hand, to form or carry the inner ring 60a of the bearing 60, and the outer ring 52b of the bearing 52, and on the other hand, to be fixed to the trunnion
    90, and in particular to the aforementioned ferrule 100. This downstream end of the shaft 36a is thickened and can resemble a trunnion.
    In the example shown, the input shaft 36a comprises an external cylindrical track 36aa for mounting the internal ring 60a of the bearing 60, the external ring of which is fixed to an annular bearing support 101 secured to the input casing 23 , and an internal cylindrical track receiving or forming the outer ring 52b of the bearing 52.
    FIG. 1a thus makes it possible to see that the bearings 60, 52 and 48 are close to each other and arranged with respect to each other to optimize the overall dimensions of the assembly.
    The bearing 60 has an average diameter greater than the average diameter of the bearing 48, which is itself greater than the average diameter of the bearing 52. The average diameter is measured at the geometric center of the rolling elements of the bearing. The bearing 52 is interposed axially between the bearing 60, located upstream, and the bearing 48, located downstream.
    The first nut 70 is located upstream of the bearing 60 and the second nut 92 is located between the bearings 52, 48.
    FIGS. 3 and following illustrate steps of a method according to the invention for dismantling the turbomachine 10.
    A first step illustrated in FIG. 3 consists in removing an inlet cone 104 (visible in FIG. 1) from the turbomachine 10. This inlet cone 104 is centered on the axis of the turbomachine 10 and is fixed on the blower hub 12, by screws. These screws are unscrewed and the cone 104 is removed from upstream, which gives access to the interior of the second shaft 38 and in particular to the second nut 70.
    The next step illustrated in FIGS. 4 and 4a therefore consists in unscrewing and removing the second nut 70. The withdrawal of this nut 70 makes it possible to dissociate the shaft 38, on the one hand, from the fan shaft 39 and from the 'output shaft 38a, on the other hand, and therefore to consider withdrawal of the shaft 38 by axial translation from downstream of the turbomachine.
    Before considering the removal of the shaft 38, it is necessary to disassemble the exhaust casing 28. The latter is therefore disconnected from the casing 29, then removed (Figure 5).
    The removal of the shaft 38 can be carried out at the same time as the last wheel 22ba of the rotor 22b of the turbine 22, or independently of this wheel. This wheel 22ba is dissociated from the rest of the rotor 22b and is then removed in FIG. 6, so as to allow the removal of the shaft 38 (FIGS. 7 and 7a).
    The removal of the shaft 38 allows access to the nut 92. This nut 92 is unscrewed and remains on the first shaft 36 due to its captive nature or trapped in a cavity during an assembly / disassembly phase . Unscrewing the nut 92 makes it possible to separate the shaft 36 from the journal 90 (FIGS. 8 and 8a).
    The next step is then to remove the shaft 36 by axial translation from the downstream end of the turbomachine (Figures 9 and 9a). The nut 92 can then bear radially on the cylindrical rim 52aa of the inner ring 52a of the bearing, which ensures its radial retention and guarantees correct positioning of the nut for the re-assembly of the turbomachine 10. As a variant, can also leave the nut 92 in radial abutment on the rim of the journal 90 opposite the splines 84, and still remove the shaft 36.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Aircraft turbomachine (10) with mechanical reducer (42) and counter-rotating turbine (22), comprising:
    - a blower (12) rotated by a blower shaft (39),
    - a mechanical reduction gear (42) with planetary gear,
    - a gas generator comprising a counter-rotating turbine (22), a first turbine shaft (36) of which is coupled to an input shaft (36a) of the reduction gear and to a journal (90) of a low pressure compressor ( 14) of the gas generator, and a second turbine shaft (38) of which is coupled to the fan shaft as well as to an output shaft (38a) of the reduction gear, characterized in that:
    - the guiding of the input shaft of the reduction gear is ensured by a first ball bearing (60) located downstream of the reduction gear (42), between this input shaft and an input casing (23),
    the trunnion is guided by a second roller bearing (48) mounted between this trunnion and an intermediate casing (24) of the turbomachine, and
    - The first shaft (36) is guided in particular by a third roller bearing (52) interposed axially between said first and second bearings, and located between this first shaft and said input shaft.
    [2" id="c-fr-0002]
    2. Turbomachine (10) according to claim 1, in which the guiding of the fan shaft (39) and of the output shaft (36a) is ensured by an upstream roller bearing (56) and by a downstream bearing ball bearings (58), these bearings being located upstream of the reduction gear (42), between the fan and output shafts, on the one hand, and the inlet casing (23), on the other hand.
    [3" id="c-fr-0003]
    3. Turbomachine (10) according to claim 1 or 2, wherein said first bearing (60) has an average diameter greater than the average diameter of said second bearing (48), which is itself greater than the average diameter of said third bearing (52 ).
    [4" id="c-fr-0004]
    4. Turbomachine (10) according to one of the preceding claims, wherein said pin (90) is engaged on said first shaft (36) and immobilized axially thereon by means of a first nut (92) screwed onto said first tree.
    [5" id="c-fr-0005]
    5. A turbomachine (10) according to claim 4, in which said fan shaft (39) and said output shaft (38a) are immobilized axially on said second shaft (38) by means of a second nut (70) screwed onto said second tree.
    [6" id="c-fr-0006]
    6. Turbomachine (10) according to one of the preceding claims, wherein said first shaft (36) is connected at its downstream end to a first turbine rotor (22a), and said second shaft (38) is connected at its end downstream to a second turbine rotor (22b), said first turbine rotor having wheels (22aa) interposed between wheels (22ba) of the second turbine rotor.
    [7" id="c-fr-0007]
    7. Turbomachine (10) according to the preceding claim, wherein said first and second rotors (22a, 22b) of turbine (22) are surrounded by a housing (29) of which a downstream end comprises a flange for fixing to a housing exhaust (28) of the turbomachine.
    [8" id="c-fr-0008]
    8. Method for dismantling a turbomachine (10) according to at least claim 5, comprising the steps of:
    a) disassembly and removal of an inlet cone (104) of the turbomachine, located upstream and in the center of the fan (12),
    b) unscrewing the second nut (70) by means of a tool inserted inside said second shaft (38) from the upstream end of the turbomachine,
    c) disassembly of said second shaft (38) and removal of this second shaft from the downstream end of the turbomachine,
    d) unscrewing the first nut (92) by means of a tool inserted inside said first shaft (36) from the upstream end of the turbomachine, and
    e) disassembly of said first shaft (36) and removal of this first shaft from the downstream end of the turbomachine.
    [9" id="c-fr-0009]
    9. Method according to claim 8, the turbomachine being as defined in claim 7, in which
    - step c) includes the disassembly and removal of the exhaust casing (28), then the disassembly and removal of at least part of said second
    5 rotor (22b), on the one hand, and said second shaft (38), on the other hand, the withdrawal of at least part of said second rotor and said second shaft being carried out simultaneously or successively, and
    - Step e) comprises the disassembly and removal of at least part of said first rotor (22a), on the one hand, and said first shaft (36), on the other hand, the
    [10" id="c-fr-0010]
    10 removal of at least part of said first rotor and said first shaft being produced simultaneously or successively,
    10. The method of claim 8 or 9, wherein said first nut (92) is mounted on said first shaft (36) and is intended to remain on this first shaft after it is unscrewed in step d).
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    WO2021116557A1|2021-06-17|Recovery of lubricating oil from a reduction gear of an aircraft turbine engine
    同族专利:
    公开号 | 公开日
    US20200116081A1|2020-04-16|
    FR3087226B1|2020-10-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2641333A1|1989-01-03|1990-07-06|Gen Electric|DOUBLE FLOW TURBOREACTOR COMPRISING A CONTRAROTATIVE TURBINE FOR THE DRIVE OF THE BLOWER|
    FR2641331A1|1989-01-03|1990-07-06|Gen Electric|HIGH DILUTION RATE DOUBLE FLOW TURBOREACTOR COMPRISING A BLOWER DRIVE TURBINE PARTIALLY FITTED TO THE BLOWER BY A GEAR TRANSMISSION|
    FR2942273A1|2009-02-18|2010-08-20|Snecma|DOUBLE FLOW MOTOR WITH CONTRAROTATIVE TURBINE WHEELS|
    US10968834B2|2019-06-28|2021-04-06|Pratt & Whitney Canada Corp.|Shaft assembly for aircraft engine|
    GB201917774D0|2019-12-05|2020-01-22|Rolls Royce Plc|Gas turbine engine arrangement|
    GB201917773D0|2019-12-05|2020-01-22|Rolls Royce Plc|High power epicyclic gearbox and operation thereof|
    GB201917764D0|2019-12-05|2020-01-22|Rolls Royce Plc|Reliable gearbox for gas turbine engine|
    法律状态:
    2019-09-19| PLFP| Fee payment|Year of fee payment: 2 |
    2020-04-17| PLSC| Search report ready|Effective date: 20200417 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 3 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1859406A|FR3087226B1|2018-10-10|2018-10-10|AIRCRAFT TURBOMACHINE WITH MECHANICAL REDUCER AND CONTRAROTATING TURBINE|FR1859406A| FR3087226B1|2018-10-10|2018-10-10|AIRCRAFT TURBOMACHINE WITH MECHANICAL REDUCER AND CONTRAROTATING TURBINE|
    US16/597,505| US20200116081A1|2018-10-10|2019-10-09|Aircraft Turbomachine with Mechanical Reducer and Contrarotative Turbine|
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