• 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:
    The invention relates to a coupling for a turbomachine, comprising a first and a second disc (17, 18) joined along an axis (AX), and extending in majority respectively from a first and from a second side ( C1, C2) of a median plane (PM) normal to the axis (AX), the first and second discs (17, 18) being provided with first and second teeth (19, 21 respectively) engaging each other across the midplane (PM) to form a curvy bond. According to the invention: - several first teeth (19) each have a first protuberance (19b) projecting towards the axis (AX) extending from the second side (C2); - Several second teeth (21) each have a second protuberance (21b) projecting towards the axis of rotation (AX) extending from the first side (C1); - The first protrusions (19b) are spaced from the second protrusions (21b) along the axis (AX); - At least one blocking member is attached to bear against first and second protrusions (21b) for axially blocking the first element (17) relative to the second element (18).
    公开号:FR3085409A1
    申请号:FR1857740
    申请日:2018-08-29
    公开日:2020-03-06
    发明作者:Clement Raphael LAROCHE
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    COUPLING FOR CURVIC TYPE TURBOMACHINE WITH LOCK
    DESCRIPTION
    TECHNICAL AREA
    The invention relates to the coupling of two rotary elements such as discs carrying blades in a turbomachine engine or the like such as a turbojet engine, by means of a “curvic” type connection.
    PRIOR STATE OF THE ART
    In such an engine, outside air is admitted into an inlet sleeve to pass through a blower comprising a series of rotary blades before splitting into a central primary flow and a secondary flow surrounding the primary flow.
    The primary flow then passes through a high pressure compressor before arriving in a combustion chamber, after which it expands by successively passing through a high pressure turbine and a low pressure turbine before being evacuated generating after energy recovery for the drive of the blower and generating thrust. The secondary flow is propelled directly backwards by the blower to also generate a thrust.
    To allow energy recovery, the high pressure turbine is linked in rotation with the high pressure compressor to drive it in rotation, and the blower is linked in rotation with the low pressure turbine by which it is driven in rotation, the most of the thrust being generated by the blower.
    The compressor or turbine parts of such an engine most often comprise several stages formed by rotary elements secured in rotation to each other to rotate about an axis of rotation AX of the engine.
    In this context, FIG. 1 shows a high pressure turbine 1 comprising a part 2 including a first stage 3 and a second stage 4 downstream of the first stage with respect to the direction of flow of the flow. The first stage 3 comprises a first disc 6 carrying a first series of vanes 7, the second stage comprising a second disc 8 carrying a second series of vanes 9. A distributor 11 formed from a series of fixed vanes 12 is interposed between the first series of moving blades and the second series of moving blades. Each disc has a central opening and has vanes at its outer periphery.
    As can be seen in this FIG. 1, the first disc 6 is attached to the second disc 8 along the axis AX, and it is coupled in rotation to this first disc by a link of the “curvic coupling” type, also called dog clutch or link trapezoidal toothing.
    The connection of the two discs which appears more clearly in FIGS. 2 and 3 comprises first trapezoid teeth 13 carried by the first disc 6 which are oriented towards the second disc 8, and second trapezoid teeth 14 carried by the second disc while being oriented to the first disc 6.
    In the case of Figures 2 and 3, the first and the second disc are uncoupled by being spaced from each other, which allows their teeth to appear. When the arrangement is in service as in the case of FIG. 1, the discs are coupled by the fact that they are applied one against the other, the first teeth being engaged with the second teeth according to an assembly of creneaumortaise type. allowing to transfer a couple from one disc to another.
    The choice of a coupling by curvic link notably allows the discs to center independently of each other around the axis of rotation during operation, while effectively transferring a torque from one disc to the other . This coupling also makes it possible to facilitate the assembly and disassembly of the rotor of which the disks which compose it form part while having a limited bulk.
    However, if one of the discs loses one of the blades which it carries, the axial forces to which it is subjected become unbalanced, as illustrated diagrammatically in FIG. 4. In practice, the disc having lost one or more blades then tends to tilt relative to its nominal orientation, which can lead to uncoupling of the two discs, illustrated in FIG. 5. In the event of uncoupling, the disc can enter an overspeed state which can lead to its explosion and / or its output from the engine.
    The object of the invention is to provide a solution making it possible to avoid uncoupling of an interdisc link of the curvic type, in particular in the event of the loss of a blade.
    STATEMENT OF THE INVENTION
    To this end, the subject of the invention is a coupling for a turbomachine between a first element and a second element which extend around an axis while being engaged with each other along the axis, each element comprising teeth which extend axially to be engaged axially in a respective concavity of the other element, characterized in that it comprises at least one blocking member which cooperates with blocking means carried by the teeth of the first and of the second element for axially locking the first element relative to the second element.
    With this solution, the uncoupling of the first and second elements is prevented in the axial direction, which is particularly effective in avoiding overspeed phenomena which can lead to damage to the rotor of the turbomachine in the event of separation between these two elements in operation . In addition, the size of the locking means is limited by the fact that they are as close as possible to the coupling teeth.
    The subject of the invention is also a coupling thus defined, in which:
    - Several teeth of the first element each have a first retention face;
    - Several teeth of the second element each have a second retention face;
    - The at least one blocking member extending between the first and the second retention faces to axially block the first element relative to the second element.
    The invention also relates to a coupling thus defined, in which the first retention faces and the second retention faces are planar and in contact with the locking member. The invention also relates to a coupling thus defined, in which each retention face is formed by a protuberance extending a tooth, and in which each protuberance has a rectilinear shape of radial orientation directed towards the axis.
    The invention also relates to a coupling thus defined, in which the locking member is a split ring.
    The invention also relates to a coupling thus defined, in which certain first and second teeth are devoid of protuberance.
    The invention also relates to a coupling thus defined, in which the blocking member comprises a cylindrical bottom extended externally by a rib engaging between the first and second retention faces.
    The invention also relates to a coupling thus defined, in which the cylindrical bottom of the locking member is extended axially by a first and by a second flank which are axially extended respectively by a first and by a second cylindrical rim, this first and this second cylindrical rim respectively pressing against a first and against a second cylindrical internal face respectively of the first and of the second element.
    The invention also relates to a coupling thus defined, in which the cylindrical flanges each carry an annular seal.
    The invention also relates to a turbine comprising a coupling thus defined.
    The invention also relates to a turbomachine comprising a turbine thus defined.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Figure 1 already described is a sectional view of a portion of known high pressure turbine;
    FIG. 2 already described is a perspective view of a known curvy type connection portion;
    FIG. 3, already described, is a diagrammatic flat view of a connection portion of known curvic type;
    FIG. 4 already described is a side view showing an imbalance in the distribution of forces in a known curvy connection in the event of the loss of a blade;
    Figure 5 already described is a perspective view showing a uncoupling of a known curvy link;
    Figure 6 is a schematic flat view of a curvy connecting portion according to the invention;
    Figure 7 is a schematic sectional view of a curvy connection according to the invention;
    Figure 8 is a perspective view of a curvy connecting portion according to the invention;
    Figure 9 is a perspective view of a portion of second teeth of the connection according to the invention;
    Figure 10 is a perspective view of a half curvy link according to the invention;
    Figure 11 is a perspective view of a portion of first toothing of the connection according to the invention with a variant of the locking member;
    Figure 12 is a partial sectional view of the connection according to the invention showing the section of the variant locking member;
    Figure 13 is a sectional view of the variant organ shown alone.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
    The basic idea of the invention is to take advantage of the alternating overlapping of the teeth of the curvy connection to maintain an annular blocking member by protuberances protruding from the teeth radially towards the axis.
    In FIG. 6, a schematic flat view of a portion of a connection 16 of the curvic type according to the invention ensures the coupling of a first disc 17 with a second disc 18 which rotate around an axis AX in being joined to each other along this axis.
    The first disc 17 carries on one of its faces a first toothing extending along a crown centered on the axis AX, this first toothing being formed by first regularly spaced trapezoidal teeth 19 which are oriented towards the second disc 18.
    The second disc 18 carries on one of its faces a toothing extending along a crown centered on the axis AX, this second toothing being formed by second trapezoidal teeth 21 regularly spaced apart and oriented towards the first disc 17.
    Each tooth 19 of the first disc 17 has a trapezoidal main profile 19a oriented axially and directed towards the second disc, and a protrusion 19b which protrudes from one end of this main profile 19a and extends towards the axis AX. Similarly, each tooth 21 of the second disc 18 has a main trapezoidal profile 21a oriented axially and directed towards the first disc, and a protrusion 21b which protrudes from one end of this main profile and extends towards the axis AX .
    The first disc 17 is coupled in rotation with the second disc 18 by interlocking the main profiles 19a, 21a with each other which constitute the teeth proper, and by means of which a torque is transferred from a disc towards each other when the assembly is in service. Each tooth is thus engaged in a concavity delimited by the interval separating two consecutive teeth from the other disc.
    Each first protrusion 19b defines a trapezoidal profile 19a of a first tooth 19 belonging to the first disc and which is oriented towards the axis AX, a cylindrical internal face 22 being common to the first teeth 19. Similarly, each second protrusion 21b defines a trapezoidal profile 21a of a second tooth 21 belonging to the second disc and which is oriented towards the axis AX, a cylindrical internal face 23 being common to the second teeth 21.
    As shown in Figures 6 and 7, each first protrusion 19b forms a first retention face 19c flat and normal to the axis AX facing the first disc 17, and similarly each second protrusion 21b forms a second retention face 21c plane and normal to the axis AX facing the second disc 18.
    The first retention faces 19c and the second retention faces 21c are arranged alternately on either side of a median plane PM normal to the axis AX. This median plane PM corresponds to the mean plane of the coupling: the first disc 17 is situated essentially on a first side C1 of the plane PM, and the second disc is located essentially on a second side C2 of the plane PM, opposite to the first . The faces 19c all extend in a region located on the second side C2 and the faces 21c all extend in a region located on the first side C1.
    The first trapezoidal profiles cross the median plane PM, so that the first retention faces 19c extend from the second side C2. And similarly, the second trapezoidal profiles 21a cross the median plane PM, so that the second retention faces 21c extend from the first side C1.
    The first retention faces 19c are spaced from the second retention faces 21c along the axis AX, so as to delimit between them a circumferential groove, the bottom of which is constituted by the cylindrical internal faces 22 and 23. This groove receives a member 24 which, in the example of the figures, is an annular ring for locking the connection.
    As can be seen in particular in FIGS. 8 and 9, each first protuberance 19b has a rectilinear shape and extends radially towards the axis AX, and similarly each second protuberance 21b has a rectilinear shape and extends radially towards the axis AX.
    When the assembly is mounted as in FIGS. 8 and 10, the rod 24 extends between the first and the second protuberances arranged in staggered rows. The rod 24 is thus interposed axially between the first retention faces 19c and the second retention faces 21c in order to block them relative to each other along the axis AX, forming with them a locking opposing any separation of the first disc from the second disc.
    The rod 24 is also blocked radially: on the one hand by the internal faces 22 and 23 against which it is in abutment and which oppose its radial expansion by centrifugal effect.
    The assembly constituted by the rod 24 and the protuberances 19b, 21b thus forms a stable locking of the curvic connection which prohibits the axial disengagement of the latter, while being removable for example for an engine maintenance operation or for its mounting.
    In the example of the figures, each tooth is provided with a protuberance, but only a part of the teeth can be provided with such protrusions, for example one tooth in two or one tooth in three. In practice, the connection comprises a minimum of three first protrusions extending three first teeth and three second protrusions extending three second teeth.
    Once the first disc 17 has been fitted against the second disc 18, to engage the first toothing with the second toothing, an operator engages one end of the rod 24 in the annular groove delimited by the protrusions 19b, 21b, and it pushes this rod radially in this groove until it is fully housed there.
    The locking member 24 has here a general shape of a split ring, of rectangular section, having two ends slightly spaced from each other.
    This rod 24 is advantageously made of a material having an appropriate flexibility to allow an operator to tighten it and deploy it radially so as to engage it between the protrusions.
    In the example of the figures, the locking member is a single annular rod engaged in the groove delimited by the retention faces. The connection according to the invention can also be blocked by several locking members each coming to be positioned between several first and second retention faces.
    These locking members are then located circumferentially one after the other in the groove delimited by the retention faces, being held by the support exerted by the retention faces and by centrifugal effect when the engine is running. These locking members may be in the form of several portions of complementary rods whose ends are contiguous or spaced from each other when they are in place.
    The fact of using one or more locking members generally forming an internal ring interposed axially between the protrusions ensures that the discs retain the possibility of being centered independently of each other on the axis AX, while ensuring that they cannot uncouple.
    In a variant illustrated in FIGS. 11 and 12, the blocking member 24 has a section, not rectangular, but having a shape corresponding approximately to that of the letter W, to form a seal opposing the passage of fluid through the gaps present between the first teeth and the second teeth when they are engaged in one another. Such a gap appears in FIG. 12 where it is identified by IN.
    As can be seen in FIG. 12, the variant of member 24 comprises a central rib in the form of a crown carried by a bottom extended by two flanks each terminated by a rim or flap.
    The central rib 26 has the shape of a flat crown of rectangular section extending in the median plane PM when the assembly is mounted, and it protrudes radially outwards from a bottom 27 in the form of a cylindrical wall. being located at mid-length of this bottom 27, the assembly being coaxial with the axis AX.
    The bottom 27 which delimits the internal face of the member 24 extends for half of the first side C1, and for half of the second side C2. This bottom 27 is extended on the first side C1 by a first frustoconical flank 28 which is itself extended by a first cylindrical rim 29, or flap, coming to bear on a first cylindrical internal face 22 of the first disc 17, from which the first teeth 19.
    Similarly, this bottom 27 is extended on the second side C2 by a second frustoconical flank 31 which is itself extended by a cylindrical rim
    32, or flap bearing on a second cylindrical internal face 23 of the second disc 18 from which the second teeth 21 start.
    The locking member 24 of the variant of FIGS. 11 to 13 has a shape of revolution around the axis AX, and it is symmetrical with respect to the plane PM when observed in place, that is to say when he is engaged in the connection to block it. It also has a general shape of a split ring with sufficient flexibility to allow its mounting.
    The first cylindrical flange 29 has an external face, also cylindrical, which is provided with a groove in which a first O-ring is installed.
    33. Similarly, the second cylindrical rim 32 has at its cylindrical external face a groove in which a second O-ring 34 is mounted.
    Thanks to these seals 33, 34, when the locking member 24 is in place, it establishes a sealed continuity from the internal face 22 of the first disc 17 to the internal face 23 of the second disc 18, sealingly covering the teeth 19 and 21 engaged in each other. Under these conditions, air can no longer pass through the interstices IN located at the heads of the teeth.
    The mounting of this variant of member 24 is analogous to the mounting of the locking member of FIGS. 8 and 9: once the two discs 17 and 18 have been joined, an operator grasps the member 24 by tightening it on it - even to temporarily reduce its external diameter. The operator then places this member 24 at the level of the plane PM, then engages its central rib 26 between the first teeth 19 and the second teeth 21, until the flanges 29 and 32 carrying the seals 33 and 34 come to bear on the internal faces 22 and 23 over the entire circumference of this member 24.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Coupling for a turbomachine between a first element (17) and a second element (18) which extend around an axis (AX) while being engaged with each other along the axis (AX) , each element (17, 18) comprising teeth (19, 21) which extend axially to be engaged axially in a respective concavity of the other element, characterized in that it comprises at least one locking member (24 ) which cooperates with locking means carried by the teeth (19, 21) of the first and second element (17, 18) to axially block the first element (17) relative to the second element (18).
    [2" id="c-fr-0002]
    2. Coupling according to claim 1, in which:
    - Several teeth (19) of the first element (17) each have a first retention face (19c);
    - Several teeth (21) of the second element (18) each have a second retention face (21c);
    - The at least one blocking member extending between the first and the second retention faces (19c, 21c) for axially blocking the first element (17) relative to the second element (18).
    [3" id="c-fr-0003]
    3. Coupling according to claim 2, wherein the first retention faces (19c) and the second retention faces 21c) are planar and in contact with the locking member (24).
    [4" id="c-fr-0004]
    4. Coupling according to claim 2 or 3, in which each retention face (19c, 21c) is formed by a protuberance (19b, 21b) extending a tooth (19, 21), and in which each protuberance (19b, 21b) has a rectilinear shape of radial orientation directed towards the axis (AX).
    [5" id="c-fr-0005]
    5. Coupling according to claim 3 or 4, wherein the locking member (24) is a split ring.
    [6" id="c-fr-0006]
    6. Coupling according to claim 3, in which some of the first and second teeth (19, 21) are devoid of protuberance.
    [7" id="c-fr-0007]
    7. Coupling according to one of claims 3 to 6, wherein the locking member (24) comprises a cylindrical bottom (27) extended externally by a rib (26) engaging between the first and second retention faces ( 19c, 21c).
    [8" id="c-fr-0008]
    8. Coupling according to claim 7, in which the cylindrical bottom (27) of the locking member (24) is extended axially by a first and by a second flank (28, 31) which are axially extended respectively by a first and by a second cylindrical rim (29, 32), this first and this second cylindrical rim (29, 32) pressing respectively against a first and against a second cylindrical internal face (22, 23) respectively of the first and of the second element (17 , 18).
    [9" id="c-fr-0009]
    9. Coupling according to claim 8, in which the cylindrical flanges (29, 32) each carry an annular seal (33, 34).
    [10" id="c-fr-0010]
    10. Turbine comprising a coupling according to one of the preceding claims.
    [11" id="c-fr-0011]
    11. A turbomachine comprising a turbine according to claim 10.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3617452A1|2020-03-04|Coupling for turbomachine, corresponding turbine and turbomachine
    CA2794837C|2018-01-02|Unshrouded fan for turbomachine
    CA2854679C|2019-09-17|Impeller for a turbomachine
    EP1517005A1|2005-03-23|Gas turbine sealing joint having lamellar structure
    EP1607582A1|2005-12-21|Mounting of a gas turbine combustor with integrated turbine inlet guide conduit
    FR2918409A1|2009-01-09|Rotating part i.e. fan, for turbine engine of aircraft, has blade with circumferential projection detected in continuity of adjacent platform forming sector, where projection participates in definition of inter-blade surface
    FR2860031A1|2005-03-25|TURBINE WHEEL FOR TURBOMACHINE AND METHOD FOR MOUNTING SUCH A WHEEL
    FR3029960A1|2016-06-17|AUBES WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE
    EP2366061B1|2017-03-22|Turbine wheel with an axial retention system for vanes
    EP3109406A1|2016-12-28|Axial turbomachine compressor casing
    FR2927685A1|2009-08-21|SEAL RING ASSEMBLY AND TURBINE ENGINE COMPRISING SUCH AN ASSEMBLY
    WO2012056161A1|2012-05-03|Set of rotor discs for a turbomachine
    FR3073001A1|2019-05-03|TURBINE DISK ASSEMBLY
    FR3085413A1|2020-03-06|COUPLING FOR CURVIC TYPE TURBOMACHINE WITH LOCK
    FR3085411A1|2020-03-06|COUPLING FOR CURVIC TYPE TURBOMACHINE WITH LOCK
    FR3072122B1|2019-09-27|TURBOMACHINE WHEEL
    EP3667015A1|2020-06-17|Holding device for dismantling a turbomachine blade wheel, and method using it
    FR3029961A1|2016-06-17|AUBES WHEEL WITH BECQUETS FOR A TURBOMACHINE TURBINE
    FR3085410A1|2020-03-06|COUPLING FOR CURVIC TYPE TURBOMACHINE WITH LOCK
    EP3265654B1|2019-01-09|Bladed integrated disk comprising a shortened hub and a supporting element
    FR3073560A1|2019-05-17|MONOBLOC WHEEL TURBOMACHINE AIRCRAFT
    FR3060051A1|2018-06-15|TURBINE FOR TURBOMACHINE
    FR3093541A1|2020-09-11|Double Rotor Aircraft Gas Turbine
    FR3106615A1|2021-07-30|Turbomachine assembly
    FR3096397A1|2020-11-27|REMOVABLE PION ON TURBOMACHINE DISTRIBUTOR
    同族专利:
    公开号 | 公开日
    CN110872957A|2020-03-10|
    FR3085409B1|2020-12-11|
    US20200072054A1|2020-03-05|
    EP3617452B1|2021-05-19|
    EP3617452A1|2020-03-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR902004A|1943-02-09|1945-08-16|Tech Studien Ag|Rotor, composed of elements of revolution arranged one beside the other and assembled axially to each other by threaded bolts for turbomachines, in particular for steam and gas turbines|
    US2672013A|1950-06-30|1954-03-16|Curtiss Wright Corp|Gas turbine cooling system|
    US20150322961A1|2012-07-18|2015-11-12|Siemens Aktiengesellschaft|A rotor for a radial compressor and a method for construction thereof|
    DE102014225975A1|2014-01-16|2015-07-16|MTU Aero Engines AG|Connecting device for rotor sections of a turbomachine and method for connecting|
    KR101842798B1|2016-11-10|2018-03-27|두산중공업 주식회사|Gas Turbine|
    DE19857554A1|1998-12-14|2000-06-15|Rolls Royce Deutschland|Connection arrangement of two running disks of an axial flow machine|
    US8870544B2|2010-07-29|2014-10-28|United Technologies Corporation|Rotor cover plate retention method|
    US9109450B2|2012-06-14|2015-08-18|United Technologies Corporation|Rotor assembly with interlocking tabs|
    EP2971695B1|2013-03-11|2020-11-04|United Technologies Corporation|Gas turbine shaft coupling and method|
    WO2014197074A2|2013-03-14|2014-12-11|United Technologies Corporation|Curvic seal for gas turbine enigne|US11174735B2|2019-12-23|2021-11-16|General Electric Company|Patch rings and methods of use|
    DE102020209471A1|2020-07-28|2022-02-03|MTU Aero Engines AG|Torsion-proof clamp assembly of a turbomachine|
    法律状态:
    2019-07-22| PLFP| Fee payment|Year of fee payment: 2 |
    2020-03-06| PLSC| Search report ready|Effective date: 20200306 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 3 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1857740A|FR3085409B1|2018-08-29|2018-08-29|COUPLING FOR TURBOMACHINE TYPE CURVIC WITH LOCKING|FR1857740A| FR3085409B1|2018-08-29|2018-08-29|COUPLING FOR TURBOMACHINE TYPE CURVIC WITH LOCKING|
    US16/549,491| US20200072054A1|2018-08-29|2019-08-23|Curvic type coupling for turbomachine with locking|
    EP19193884.4A| EP3617452B1|2018-08-29|2019-08-27|Coupling for turbomachine, corresponding turbine and turbomachine|
    CN201910801091.1A| CN110872957A|2018-08-29|2019-08-28|Curved coupling with locking feature for a turbomachine|
    [返回顶部]