• 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) with a counter-rotating turbine for an aircraft, the turbomachine comprising a contra-rotating turbine (22), a first rotor (22a) of which is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor having turbine wheels (36a) interposed between turbine wheels (38a) of the second rotor, the turbomachine further comprising a mechanical reduction gear (42) with planetary gear which comprises a sun gear (44) driven in rotation by said second shaft, a crown (40) driven in rotation by said first shaft, and a holder satellites (46) fixed to a stator housing (28) of the turbomachine situated downstream of the counter-rotating turbine with respect to a direction of flow of the gases in the turbomachine, the turbomachine further comprising bearings (56) of guiding the second shaft relative to the first shaft, and a bearing for guiding the second shaft relative to said stator housing, characterized in that said bearings are all located downstream of the trailing edge of the last turbine wheel of the counter-rotating turbine and upstream of the reducer.
    公开号:FR3087223A1
    申请号:FR1859403
    申请日:2018-10-10
    公开日:2020-04-17
    发明作者:Ghislain Albert Levisse Paul；Olivier BELMONTE；Yanis BENSLAMA
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TURBOMACHINE WITH A CONTRAROTATIVE TURBINE FOR AN AIRCRAFT
    TECHNICAL AREA
    The present invention relates 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 to increase the efficiency of a turbine without increasing its speed is to use a counter-rotating turbine. The low pressure turbine is then replaced by a turbine with two rotors, 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 a direction opposite to rotation and is connected to a second turbine shaft. The first rotor has turbine wheels interposed between turbine 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 meshing with a mechanical reduction gear with planetary gear.
    The reduction gearbox couples the fast rotor and the slow rotor, thus allowing a transfer of power from the fast rotor to the slow rotor. We take advantage of the higher yields of a fast turbine while transferring a large part of the power from the turbine to the blower without passing through a reduction gear but through a shaft.
    This architecture is complex due to its mechanical integration: the mechanical reduction gear is located downstream of the turbomachine, radially inside a stator casing called the exhaust casing.
    In the state of the art, this positioning of the reduction gear involves placing numerous bearings and oil recovery chambers inside the exhaust casing. Furthermore, the gearbox is located in a relatively hot area, which requires substantial thermal protection. The space located inside the exhaust casing is therefore particularly constrained, which implies working as much as possible on the integration of the reducer and reducing its installation radius.
    Existing integration solutions are particularly complex because there are many inter-shaft bearings that are particularly difficult to lubricate. The radial loads from the turbines are liable to pass through the gear unit, which is extremely detrimental for the good behavior of the gear unit. Finally, the size is not optimized, in particular with the presence of bearings under the planetary or solar gearbox, which limits the radial integration of the gearbox.
    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.
    The invention provides a contra-rotating turbine turbomachine for an aircraft, the turbomachine comprising a contra-rotating turbine 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 comprises is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft, the first rotor comprising turbine wheels interposed between turbine wheels of the second rotor, the turbomachine further comprising a mechanical reduction gear with planetary gear which comprises a solar driven in rotation by said second shaft, a ring driven in rotation by said first shaft, and a planet carrier fixed to a stator casing of the turbomachine located downstream of the counter-rotating turbine relative to a direction of gas flow in the turbomachine, the turbomachine further comprising a bearing for guiding the second shaft relative to u first shaft, and a bearing for guiding the second shaft relative to said stator housing, characterized in that said bearings are all located downstream of a trailing edge of the wheel most downstream of the counter-rotating turbine and upstream of the reducer.
    This solution is advantageous for several reasons. First of all, from a simplification and mounting point of view, since the number of bearings is limited and may be only two, namely one for guiding the second shaft relative to the first shaft and another for guiding the second shaft relative to the stator housing. Furthermore, from a space and integration point of view, they are also simplified because of the number and the position of the bearings. These bearings are actually located in the same zone located downstream of the counter-rotating turbine and upstream of the reduction gear. They are thus positioned to facilitate the transmission of forces from the first shaft to the stator housing, avoiding stressing the gearbox. In addition, the reducer is essentially connected to three members, only one of which is said to be “rigid”, the other two being said to be “flexible”. Indeed, in the above configuration, due to the position of the bearings and the limitation of their number, the first shaft forms a flexible member for connection to the reducer, as is the case with the second shaft. Only the planet carrier, which is connected to the stator housing, can be considered as a rigid member.
    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:
    said second shaft is guided by a single bearing relative to said first shaft, and by a single bearing relative to said stator housing,
    - each level is a single level or double level,
    said second shaft is guided by a ball bearing with respect to said first shaft,
    said ball bearing comprises an outer ring fixed directly to a tubular cylindrical portion of said second shaft, and
    - said ball bearing has an internal ring fixed directly or by means of an annular pedestal with i-section to a tubular cylindrical portion of said first shaft,
    - said second shaft is guided by a roller bearing with respect to said stator housing,
    said roller bearing comprises an internal ring fixed directly to a tubular cylindrical portion of said second shaft, and an external ring fixed by an annular bearing support to said stator housing,
    - seals, for example at a labyrinth, are located upstream of said bearings, on the one hand between the first and second shafts, and on the other hand between the second shaft and the stator housing,
    said seals are configured to ensure the sealing of a lubrication enclosure delimited in particular by said first shaft as well as the planet carrier of said reducer, and
    - Said bearings are at least partially nested axially one in the other or one in the other.
    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 counter-rotating turbine according to the invention,
    FIG. 2 is a diagrammatic view on a larger scale and in more detail of the downstream part of the turbomachine of FIG. 1,
    FIG. 3 is a view similar to that of FIG. 2 and further illustrating the seals, and
    - Figure 4 is a schematic view in axial section and on an even larger scale of bearings of an alternative embodiment of the turbomachine.
    DETAILED DESCRIPTION
    FIG. 1 very schematically represents a turbomachine 10 with a counter-rotating turbine 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 24 designates an intermediate casing located between the compressors 14 and 16, and the reference 26 designates a turbine casing (of the TVF type) located between the turbines 20 and 22. Finally, the reference 28 designates an exhaust casing (of the TRF type). These casings form the structure of the turbomachine: they support the bearings which guide the rotating shafts and are linked to the suspensions of the turbomachine.
    The rotor of the high pressure turbine 20 rotates the rotor of the high pressure compressor 14 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 and are interposed between the wheels 22aa of the rotor 22a (Figures 1 and 2).
    Each turbine wheel comprises an annular row of blades which each have an aerodynamic profile comprising a lower surface and an upper surface which join to form a leading edge and a trailing edge of the gases in the turbine stream.
    The first shaft 36 rotates the blower 12 as well as the rotor of the low pressure compressor 14. This first shaft 36 is further meshed with a ring 40 of a mechanical reducer 42 with planetary gear better visible in Figure 2. For this , the first shaft comprises a tubular cylindrical portion 36a which extends downstream to the interior of the exhaust casing 28 and which comprises at its downstream end an annular ferrule 36b with an L-shaped section. This ferrule 36b comprises an annular wall 36ba extending radially outward from the downstream end of the portion 36a, and a cylindrical wall 36bb extending axially upstream from the outer periphery of the wall 36ba. The wall 36bb comprises an internal toothing (not visible) of engagement with an external toothing of the crown 40 of the reducer
    42. These teeth can be straight.
    The ferrule 36b defines around the portion 36a an annular space at least partially housing the reduction gear 42.
    The second shaft 38 is meshed with the sun 44 or planetary of the reduction gear 42 and comprises a tubular cylindrical portion 38a extending around and at a radial distance from the portion 36a of the shaft 36. The downstream end of the portion 38a is engaged in the reduction gear 42 and includes an external gear teeth with an internal teeth of the sun 44. These teeth can be straight.
    The reduction gear 42 further comprises satellites (not visible) meshed respectively with the sun 44 and the crown 40 and carried by a planet carrier 46 which is fixed to the exhaust casing 28.
    The exhaust casing 28 comprises a central hub 28a at least partially surrounding the reduction gear 42, as well as an outer ring 28b which surrounds the hub 28a and which is connected to the latter by a series of arms 28c substantially radial with respect to to the longitudinal axis of the turbomachine. The ring 28b is fixed at its upstream end by a flange to a casing 48 extending around the counter-rotating turbine 22, and the hub 28a is fixed at its downstream end to an exhaust cone 50.
    The first shaft 36 is centered and guided upstream by bearings 52, 54 mounted between the first shaft 36 and the intermediate casing 24. A first of these bearings is for example an upstream roller bearing 52, and a second of these bearings is for example a downstream ball bearing 54.
    The first shaft 36 is also centered and guided downstream by a single bearing 56 which is arranged between the first and second shafts 36, 38 and more precisely between their portions 36a, 38a. In the example shown, it is a ball bearing 56 whose inner ring 56a is fixed directly to the portion 36a and the outer ring 56b is fixed directly to the portion 38a. The bearing 56 is located downstream of the turbine 22 (that is to say downstream of the trailing edge 22ba1 of the wheel most downstream of the turbine 22) and upstream of the reduction gear 42, and is closer to the upstream end of the exhaust casing 28 than to its downstream end.
    In the variant shown in FIG. 4, the outer ring 56b is fixed directly to the portion 38a and the inner ring 56a is fixed to the portion 36a by means of an annular pedestal 72 with an i-section. This pedestal 72 has two coaxial annular walls and extending one inside the other, these walls being connected to each other by a radial annular wall.
    In addition to being guided by the bearing 56 with respect to the shaft 36, the shaft 38 is also guided by another (single) bearing 58 with respect to the exhaust casing 28. In the example shown, this is a roller bearing 58 whose inner ring 58a is fixed directly to the portion 38a and whose outer ring 58b is fixed to the inner periphery of an annular bearing support 60 whose periphery external is fixed to the exhaust casing 28 and more specifically at its upstream end. The bearing 58 is located downstream of the turbine 22 (that is to say downstream of the trailing edge 22ba1 of the wheel most downstream of the turbine 22) and upstream of the reduction gear 42, and is closer to the upstream end of the exhaust casing 28 than to its downstream end.
    Each bearing ring can be fixed to a shaft or a portion of a shaft (or a pedestal wall) by tightening this ring against a cylindrical shoulder, this tightening being obtained for example by a nut screwed onto this shaft or portion of tree (or pedestal wall). The pedestal can itself be attached in the same way to a tree or a portion of a tree.
    As in the example shown, the bearings 56, 58 may be close to one another and preferably extend at least partially around one another. This avoids an overhang. The bearing 56 here has a smaller diameter than that of the bearing 58.
    In the example shown, the bearing support 60 and the satellite carriers 46 meet or are formed in one piece and are fixed by the same external annular flange 62 to an annular flange upstream of the exhaust casing 28.
    FIG. 3 shows an example of positioning of seals 64, 66. The reduction gear 42 as well as the bearings 56, 58 are in fact lubricated by oil and are located in an annular lubrication enclosure which must be kept sealed to avoid that the oil pollutes the rest of the turbomachine.
    The lubrication enclosure extends around the portion 36a and is thus delimited radially on the inside by this portion 36a. It is delimited downstream by the radial wall 36ba of the ferrule 36b and radially outside by the cylindrical wall 36bb of the ferrule as well as by the satellite carriers 46 and the bearing support 60. Its upstream end is here closed by sealingly by the seals 64, 66 which are preferably of the labyrinth type.
    A labyrinth seal comprises two elements extending one inside the other, one of these elements carrying a layer of abradable material and the other of these elements comprising annular wipers capable of cooperating by friction. and abrasion with the abradable layer to limit the radial clearances between the elements.
    In the example shown, two seals 64 are arranged between the shafts 36, 38. They are located upstream of the bearing 56, substantially in line with the downstream end of the turbine 22. Two other seals 66 are arranged between the shaft 38 and the bearing support 60. They are located upstream of the bearing 58, substantially in line with the downstream end of the turbine 22. At least some of these seals 64, 66 are downstream of the cone 22ba2 for connecting the wheels 22ba from turbine 22 to shaft 38.
    The oil can be brought into the enclosure through radial through holes 68 provided in the portions 36a, 38a of the shafts 36, 38 near the bearings 56, 58. An oil injector 70 can be mounted inside the first shaft 36 so as to spray oil on the internal cylindrical surface of the shaft 36. This oil will join the bearing 56 by passing through the orifices 68 of the portion 36a, and may then join the bearing 56 by passing through the orifices of the portion 38a, simply by the effects of the centrifugal force in operation. The oil is prevented from leaving the enclosure by the seals 66, 68 and can join the reduction gear 42 downstream which is also lubricated by its own lubrication system (not shown).
    Thus, the shaft 38 which can rotate at a so-called fast speed, drives the sun gear 44 of the reduction gear and thus supplies energy to the first shaft 36, which is itself driven by the turbine 22. The bearing (stop) inter-shaft 56 makes it possible to minimize the axial clearances between the wheels of the turbine 22 because the two shafts move in the same way. The control of the radial clearances is carried out by means of the roller bearing 58 which makes it possible to radially block the shaft 38 in order to control the clearances at the external periphery of the turbine wheels. The bearing 58 makes it possible to ensure that the shaft 38 meshed with the reducer 42 remains perfectly straight in order to control as much as possible the misalignments of the reducer.
    Furthermore, the positioning of the bearings presented here facilitates oil recovery, because one can take advantage of the presence of the bearing support 60 to facilitate oil recovery. In addition, the inter-shaft bearing 56 can be lubricated from the inside of the shaft 36 using the injector 70. The reduction gear 42 can be lubricated with the same nozzle as the roller bearing 58 because they are both located around the tree 38.
    Finally, placing the two bearings 56, 58 substantially in the same transverse plane perpendicular to the axis of the turbomachine makes it possible to maximize the radial embedding of the shaft 36 and also makes it possible to free up space under the reduction gear 42. In Indeed, the objective of this configuration is to limit the radial size under the exhaust casing 28 in order to be able to reduce its internal diameter. The internal diameter of the exhaust casing 28 is directly dependent on the external diameter of the reducer 42, itself dependent on the original internal diameter of the solar
    44. Consequently, any space that can be gained under the sun 44 improves the overall size of the area. In this configuration, it is possible to consider locally lowering the pitch diameter of the reduction gear 42 by reducing the external diameter of the shaft 38 and the diameter of the shaft 36.
    Figure 3 also shows a variant in which the ferrule 36b of the shaft 36 is connected to the portion 36a by grooves 71. The ferrule 36b and more precisely its wall 36ba comprises at its internal periphery internal rectilinear grooves 71 d coupling to external rectilinear grooves 71 provided at the external periphery and downstream of the portion 36a of the shaft 36.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Turbomachine (10) with counter-rotating turbine for an aircraft, the turbomachine comprising a contra-rotating turbine (22), a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36 ), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine wheels (36a) interposed between turbine wheels ( 38a) of the second rotor, the turbomachine further comprising a mechanical reduction gear (42) with planetary gear which includes a sun gear (44) driven in rotation by said second shaft, a crown (40) driven in rotation by said first shaft, and a planet carrier (46) fixed to a stator housing (28) of the turbomachine situated downstream of the counter-rotating turbine with respect to a direction of flow of gases in the turbomachine, the turbomachine comprising a bearing (56) for guid age of the second shaft relative to the first shaft, and a bearing (58) for guiding the second shaft relative to said stator housing, characterized in that said bearings are all located downstream of a trailing edge (22ba1) of the wheel the most downstream of the counter-rotating turbine and upstream of the reduction gear.
    [2" id="c-fr-0002]
    2. The turbomachine (10) according to claim 1, wherein said second shaft (38) is guided by a single bearing (56) relative to said first shaft (36), and by a single bearing (58) relative to said housing. stator (28).
    [3" id="c-fr-0003]
    3. Turbomachine (10) according to claim 2, wherein each bearing (56, 58) is a single bearing or double bearing.
    [4" id="c-fr-0004]
    4. A turbomachine (10) according to claim 2 or 3, wherein said second shaft (38) is guided by a ball bearing (56) relative to said first shaft (36).
    [5" id="c-fr-0005]
    5. A turbomachine (10) according to claim 4, wherein said ball bearing (56) comprises an outer ring (56b) fixed directly to a tubular cylindrical portion (38a) of said second shaft (38).
    [6" id="c-fr-0006]
    6. Turbomachine (10) according to claim 4 or 5, wherein said ball bearing (56) comprises an internal ring (56a) fixed directly or by means of an annular pedestal (72) with i-section at a tubular cylindrical portion (36a) of said first shaft (36).
    [7" id="c-fr-0007]
    7. Turbomachine (10) according to one of the preceding claims, in which said second shaft (38) is guided by a roller bearing (58) relative to said stator housing (28).
    [8" id="c-fr-0008]
    8. A turbomachine (10) according to claim 7, wherein said roller bearing (58) comprises an internal ring (58a) fixed directly to a tubular cylindrical portion (38a) of said second shaft (38), and an external ring (58b ) fixed by an annular bearing support (60) to said stator housing (28).
    [9" id="c-fr-0009]
    9. Turbomachine (10) according to one of the preceding claims, in which seals (66, 64), for example at labyrinth, are located upstream of said bearings (56, 58), on the one hand between the first and second shafts (36, 38), and on the other hand between the second shaft and the stator housing (28).
    [10" id="c-fr-0010]
    10. Turbomachine (10) according to claim 9, in which said seals (66, 68) are configured to ensure the tightness of a lubrication enclosure delimited in particular by said first shaft (36) as well as the planet carrier (46 ) of said reducer (42).
    [11" id="c-fr-0011]
    11. Turbomachine (10) according to one of the preceding claims, in which said bearings (56, 58) are at least partially axially nested one in the other or in each other.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20200116104A1|2020-04-16|
    FR3087223B1|2020-10-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1577491A1|2004-03-19|2005-09-21|ROLLS-ROYCE plc|Turbine engine arrangements|
    EP2199568A2|2008-12-19|2010-06-23|General Electric Company|Geared differential speed counter-rotatable low pressure turbine|
    WO2015189524A1|2014-06-11|2015-12-17|Snecma|Lubrication device for a turbine 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|
    CN112989500B|2021-04-23|2021-07-23|中国空气动力研究与发展中心高速空气动力研究所|Inlet flow-dividing stability-expanding design method suitable for contra-rotating lift fan|
    法律状态:
    2019-09-19| PLFP| Fee payment|Year of fee payment: 2 |
    2020-04-17| PLSC| Publication of the preliminary search report|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
    FR1859403A|FR3087223B1|2018-10-10|2018-10-10|TURBOMACHINE WITH CONTRAROTARY TURBINE FOR AN AIRCRAFT|FR1859403A| FR3087223B1|2018-10-10|2018-10-10|TURBOMACHINE WITH CONTRAROTARY TURBINE FOR AN AIRCRAFT|
    US16/596,609| US20200116104A1|2018-10-10|2019-10-08|Turbine engine with a contra-rotating turbine for an aircraft|
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