• 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 turbine wheel for a turbomachine, comprising a disc (14) carrying blades. Each blade (122) includes an upstream radial wall (130) and a downstream radial wall (128) extending inwardly from the platform (124) of the blade (122). Inter-blade cavities each house a member (132, 156) for sealing and damping vibrations. According to the invention, each member comprises at least one transverse partition (146) arranged at an axial distance from a downstream portion (142) (or upstream, respectively) of the member (132, 156) and vis-à-vis axial axis of two upstream radial walls (130) (or downstream, respectively) so as to obstruct an air flow entering the cavity between the two upstream radial walls (130) (or downstream, respectively).
    公开号:FR3027949A1
    申请号:FR1460648
    申请日:2014-11-04
    公开日:2016-05-06
    发明作者:Sebastien Congratel；Franck Boisnault；Patrice Jean-Marc Rosset
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a turbine wheel for a turbomachine, and a turbomachine such as a turbojet engine or a turboprop aircraft equipped with such a wheel. It also relates to a sealing member and vibration damping for use with a turbine wheel and a turbomachine above. Typically, a high-pressure turbine wheel 10 of a turbomachine, as represented in FIG. 1, comprises a disc 14 carrying vanes 16 regularly distributed around the axis of the wheel and whose feet 18 are engaged in grooves substantially The blade roots 18 may be of fir-tree or dovetail type and the grooves of the disk 14 have shapes complementary to those of the blade roots 18 and define between them teeth or ribs 20.
    [0002] Each blade 16 comprises a blade 22 connected at its radially inner end to a platform 24, which is itself connected to a foot 18 by a stalk 26. The upstream end and the downstream end of each platform 24 are respectively connected to an upstream radial wall extending radially inwards and to a downstream radial wall 28 extending radially inwards. In the mounting position (FIGS. 1 and 2), the platforms 24 of the blades 16 are arranged circumferentially end to end so as to form an internal annular wall for the flow of a primary air flow coming from a chamber of combustion. Similarly, the upstream radial walls 28 and downstream 30 are arranged circumferentially opposite. It is known to mount members 32 for sealing and damping vibrations (commonly called "candies") in the inter-blade cavities. More particularly, each inter-blade cavity is defined radially outwardly by the inner faces of two circumferentially facing platforms 24, radially inwardly by a rib 20 of the disc 14, axially by two upstream and downstream transverse radial walls 28 whose ends are arranged vis-à-vis circumferentially, and circumferentially by the stilts 26 of the blades 16. As shown in Figure 2, the inner faces of two consecutive platforms 24 together define a frustoconical surface portion. This portion of frustoconical surface has a section perpendicular to the axis of the wheel being reduced downstream.
    [0003] In operation, it is particularly important to guarantee the inter-blade seal between two consecutive downstream radial walls 28 as well as the inter-platform seal 24. However, in operation, the sealing members 32 and vibration damping each undergo an upstream displacement due to the frustoconical shape of the platforms 24 of blades 16 and the centrifugal force which causes a loss of contact between the sealing members 32 and the downstream radial walls 28. Similarly , air can also flow between the downstream ends of the platforms 24. This loss of sealing induces a recirculation of hot air inside the platforms 24 towards the ribs 20 of the disc 14 which can be damaged. If the problem of displacement of the sealing members 32 is apparent in the case presented above, it is understood that the same difficulty can arise in the case of a frustoconical vein section reducing upstream and when one wants to maintain the seal upstream. Likewise, more generally, a leakage fault can also be observed in the case of a cylindrical vein because of manufacturing tolerances and positioning defects of said members 32.
    [0004] The invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above. For this purpose, it proposes a turbine wheel for a turbomachine, comprising a blade carrying blades each having a platform carrying a blade connected by a stilt to a foot, each blade comprising an upstream radial wall and a downstream radial wall. extending inward from the platform of the blade, the blade roots being engaged in grooves in the periphery of the disk so that the radial walls of the blades and the platforms of the blades are arranged circumferentially end to end and delimit inter-blade cavities radially inside the platforms each housing an inter-blade sealing member and vibration damping having a bottom wall intended to be applied on the inner faces of two plates -consecutive forms and extending at its periphery by an edge falling inward of which a downstream portion (or upstream) is intended to be applied on two downstream radial walls (or upstream, respectively), characterized in that each member comprises at least one transverse partition arranged at an axial distance from said downstream portion (or upstream, respectively) of the member and facing axially of two upstream radial walls ( or downstream, respectively) in order to prevent an air flow entering the cavity between the two upstream (or downstream) radial walls, respectively. The invention thus proposes adding a transverse partition to the sealing and damping members of the vibrations so that the air flowing in the gap between two upstream (or downstream) radial walls respectively impacts the partition, which induces a displacement of the body downstream (or upstream, respectively) and ensures a contact between the member and the downstream radial walls (or upstream, respectively) inter-blades.
    [0005] According to another characteristic of the invention, the inner faces of the platforms define a frustoconical surface section perpendicular to the axis of the wheel being reduced downstream (or upstream, respectively).
    [0006] Thus, the application of an air flow on the partition makes it possible to counter the movement of the member upstream (downstream, respectively) so that the inter-blade seal can be guaranteed. between the downstream radial walls (or upstream, respectively) and the downstream end platforms of the blades. According to yet another characteristic of the invention, said partition of each member projects radially towards the inside with respect to the fallen edge. Thus, compared to a partition not extending radially inwards with respect to the fallen edge, the force applied to the partition is thus greater for the same air flow. Preferably, the dropped edge is formed of two lateral flanks 15 extending axially each along the sides of two adjacent stilts, said partition extends from one side to the other. Said partition is advantageously arranged axially substantially in the middle of the platforms. According to another characteristic of the invention, each member 20 comprises an upstream portion (or downstream, respectively) comprising at least one air passage opening. Said upstream portion (or downstream, respectively) may also comprise two notches opening towards the inside, arranged on either side of a tongue. According to another characteristic of the invention, at least one of the members comprises a first aforementioned partition and a second transverse partition arranged axially between two consecutive upstream (or downstream, respectively) radial walls and the first partition. The invention also relates to a turbomachine, such as a turbojet or a turboprop, characterized in that it comprises a turbine comprising at least one turbine wheel as described above. The invention also relates to a sealing member and vibration damping, in particular for a turbine wheel of the type described above, comprising a bottom wall extending by a peripheral flanged edge having two flanks vis-à-vis and two end portions, one of which comprises two open slots on the opposite side to the bottom wall. The invention will be better understood and other details, advantages and features of the invention will appear on reading the following description given by way of non-limiting example, with reference to the accompanying drawings, in which: FIG. schematic partial perspective view of a turbine wheel according to the known technique; Figure 2 is a schematic perspective view and side of a blade of a turbine wheel housing a sealing member and vibration damping; Figure 3 is a schematic perspective view of a sealing member and vibration damping according to the prior art; Figure 4 is a partial schematic perspective view and from upstream of a turbine wheel according to the invention; Figure 5 is an isolated schematic perspective view of a sealing member according to the invention; Figure 6 is a schematic perspective view of another embodiment of a sealing member according to the invention. FIG. 1 having already been described previously, reference is now made to FIG. 2 which represents a sealing member 32 according to the known technique intended to be mounted in an inter-blade cavity 16. More specifically, each member 32 comprises a wall base 30 36 extending over its entire periphery by a falling edge 38 or peripheral edge extending substantially radially inwards. The falling edge 38 of each member 32 comprises an upstream portion 40 and a downstream portion 42 as well as two lateral flanks 44 connecting the upstream 40 and downstream 42 portions. Each member 32 for sealing and damping the vibrations has a complementary external shape. that of the faces of the walls defining an inter-blade cavity so that the sealing member 32 can be applied on these faces and provide a seal at the junction between the platforms 24 and the upstream radial walls. 28 and downstream 30. As can be seen (in FIG. 2), during operation, the sealing member 32 moves upstream under the effect of the centrifugal force and the frustoconical shape of the internal faces of the plates. forms 254 with section reducing downstream. It follows a loss of contact of the members 32 with the downstream radial walls 28 and the downstream ends of the platforms 24. In the following description made in connection with the invention, the parts similar to those described above have a reference whose number is increased by a hundred. According to the invention, the sealing members 132 and vibration damping each comprise a transverse partition 146 extending inwardly from the bottom wall 138 and substantially on either side of the flanks 144. Each partition 146 extends inwardly projecting from the fallen edge 138 or peripheral edge. Each partition 146 has a substantially rectangular planar shape and is inclined at an angle α of between -45 ° and 45 ° with respect to a radial plane. The upstream portion 140 of each member 146 comprises a tongue 148 extending radially inwardly projecting relative to the remainder of the upstream portion 140. The upstream portion 140 of the dropped edge 138 also comprises a notch 150 opening radially towards the 148. In operation, air can circulate in the gap separating two upstream radial walls 130 and in the notches 150 of the upstream portion of the member 132 and then impact the partition 146, which avoids the displacement of the member 132 upstream. In practice, it is understood that the notches 150 must be sized to allow the passage of a sufficient air flow 5 which depending on the inclination of the partition 146 allows to maintain the downstream portion 150 of the body support on the downstream radial walls 128 and thus ensure a perfect inter-blade seal. The notches 150 extend substantially radially. As shown in FIG. 5, a tongue 152 extends radially inwardly from the downstream portion 142 but does not include a notch on either side of the tongue 152 as for the upstream portion. In another variant of the member 156 shown in FIG. 6, the downstream portion 142 of the dropped edge 138 also comprises two notches 154 154 opening radially inwards on either side of the tongue 152. The notches 154 upstream and downstream each comprise a portion of reduced section opening into a portion of greater section and rounded substantially circular shape. This rounded shape gives greater flexibility to the tabs 18, 152. Advantageously, the tabs 148, 152 are elastically deformable and can be elastically prestressed on the upstream radial walls 130 and downstream 128 so as to ensure a radial retention of the member 132. in the cavity. In addition, in this variant, the member 156 comprises a second transverse partition 158 extending between the two lateral flanks 144 and 25 arranged axially between the first partition 146 and the upstream portion 140 of the fallen edge 138. The radial dimension of the first partition 146 is greater than the radial dimension of the second partition 158 so that the air firstly impacts the second partition 158 and then the first partition 146.
    [0007] In the embodiments shown in FIGS. 4 to 6, the first partition 146 is formed axially substantially in the middle of the member 132, 156 and substantially in the middle of the platforms 124.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Impeller wheel for a turbomachine, comprising a disk (14) carrying blades (116) each having a platform (124) carrying a blade (122) connected by a stilt (126) to a foot (118), each blade (122) comprising an upstream radial wall (130) and a downstream radial wall (128) extending inwardly from the blade deck (124) (122), the blade feet (118) being engaged in grooves in the periphery of the disk (14) so that the radial walls (130, 128) of the blades (116) and the platforms (124) of the blades (122) are arranged circumferentially end to end and delimit inter-blade cavities radially inside the platforms (124) each housing an inter-blade and vibration damping member (132, 156) having a bottom wall for application to the faces two consecutive platforms (124) extending at its periphery by a fallen edge (138) towards the inside. which a downstream portion (or upstream) is intended to be applied to two consecutive downstream radial walls (128) (or upstream, respectively), characterized in that each member comprises at least one transverse partition (146) arranged at an axial distance of said downstream portion (142) (or upstream, respectively) of the member (132, 156) and in axial vis-à-vis of two consecutive upstream radial walls (130) (or downstream, respectively) so as to obstruct a flow of air entering the cavity between the two upstream radial walls (130) (or downstream, respectively).
    [0002]
    2. Turbine wheel according to claim 1, characterized in that the inner faces of the platforms (124) define a frustoconical surface section perpendicular to the axis of the wheel being reduced downstream (or upstream, respectively ).
    [0003]
    3. Turbine wheel according to claim 1 or 2, characterized in that said partition (146, 158) of each member extends projecting radially inwardly with respect to the fallen edge (138).
    [0004]
    Turbine wheel according to one of claims 1 to 3, characterized in that the falling edge (138) is formed of two lateral flanks (144) extending axially each along the sides of two adjacent stilts (126). said partition (146, 158) extends from one side to the other.
    [0005]
    5. Wheel according to one of claims 1 to 4, characterized in that said partition (146, 158) is arranged axially substantially in the middle of the platforms (124).
    [0006]
    6. Turbine wheel according to one of claims 1 to 5, characterized in that each member (124) comprises an upstream portion (or downstream, respectively) comprising at least one air passage opening.
    [0007]
    7. Turbine wheel according to claim 6, characterized in that said upstream portion (or downstream, respectively) comprises two notches (150, 154) opening towards the inside, arranged on either side of a tongue (148). ). 15
    [0008]
    8. Wheel according to one of the preceding claims, characterized in that at least one of the members (132, 156) comprises a first partition (146) above and a second partition (158) transverse arranged axially between two radial walls. upstream (130) (or downstream, respectively) consecutive and the first partition (146). 20
    [0009]
    9. Turbomachine, such as a turbojet or a turboprop, characterized in that it comprises a turbine comprising at least one turbine wheel according to one of claims 1 to 8.
    [0010]
    Vibration sealing and damping member (132, 156) comprising a bottom wall (136) extending by a dropped edge (138) having two facing flanks (144) and two portions end of which one comprises two notches (150) opening on the opposite side to the bottom wall (136).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US10125615B2|2018-11-13|
    FR3027949B1|2019-07-26|
    US20160123157A1|2016-05-05|
    GB2532142A|2016-05-11|
    GB201519677D0|2015-12-23|
    GB2532142B|2021-03-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2963382A1|2010-08-02|2012-02-03|Snecma|Turbine wheel for turboshaft engine e.g. turbojet of airplane, has shock absorbers covered with thin layer of hard material on platforms of blades and comprising axial sealing units limiting or preventing passage of air between stilts|
    FR2972759A1|2011-03-15|2012-09-21|Snecma|Wheel for rotor of low pressure turbine in e.g. turbojet of airplane, has annular part defining radial plane to axially support blades and align blades with disk, and tightly maintained against downstream faces of teeth by downstream plate|
    FR2981979A1|2011-10-28|2013-05-03|Snecma|TURBINE WHEEL FOR A TURBOMACHINE|FR3082231A1|2018-06-11|2019-12-13|Safran Aircraft Engines|TURBOMACHINE WHEEL|
    FR3100836A1|2019-09-12|2021-03-19|Safran Aircraft Engines|MOBILE BLADES FOR TURBINE|US4473337A|1982-03-12|1984-09-25|United Technologies Corporation|Blade damper seal|
    US5228835A|1992-11-24|1993-07-20|United Technologies Corporation|Gas turbine blade seal|
    US5803710A|1996-12-24|1998-09-08|United Technologies Corporation|Turbine engine rotor blade platform sealing and vibration damping device|
    US5924699A|1996-12-24|1999-07-20|United Technologies Corporation|Turbine blade platform seal|
    FR2840352B1|2002-05-30|2005-12-16|Snecma Moteurs|MASTING THE LEAK AREA UNDER A DAWN PLATFORM|
    FR2915510B1|2007-04-27|2009-11-06|Snecma Sa|SHOCK ABSORBER FOR TURBOMACHINE BLADES|
    US9303519B2|2012-10-31|2016-04-05|Solar Turbines Incorporated|Damper for a turbine rotor assembly|ES2891030T3|2017-10-27|2022-01-25|MTU Aero Engines AG|Combination to seal a gap between the blades of a turbomachinery and reduce vibrations of the blades of the turbomachinery|
    CN107780973A|2017-12-05|2018-03-09|贵州智慧能源科技有限公司|Turbine structure and its turbine damping piece|
    DE102018203093A1|2018-03-01|2019-09-05|MTU Aero Engines AG|A combination for sealing a gap between turbomachinery blades and for reducing vibrations of the turbomachinery blades|
    FR3107082A1|2020-02-06|2021-08-13|Safran Aircraft Engines|Turbomachine wheel|
    US20210332711A1|2020-04-27|2021-10-28|Raytheon Technologies Corporation|Rotor assembly|
    法律状态:
    2015-11-04| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-06| PLSC| Publication of the preliminary search report|Effective date: 20160506 |
    2016-11-08| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1460648|2014-11-04|
    FR1460648A|FR3027949B1|2014-11-04|2014-11-04|TURBINE WHEEL FOR A TURBOMACHINE|FR1460648A| FR3027949B1|2014-11-04|2014-11-04|TURBINE WHEEL FOR A TURBOMACHINE|
    US14/931,443| US10125615B2|2014-11-04|2015-11-03|Turbine wheel for a turbine engine|
    GB1519677.7A| GB2532142B|2014-11-04|2015-11-06|Turbine wheel for a turbine engine|
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