• 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 rotor (10), with a radially inner shaft (11), with a hub body (12) which adjoins the shaft (11) radially on the outside, with rotor blades (13) which, starting from the hub body (12), extend at least radially extend outwardly and optionally in the direction of the shaft (11) radially inward, and with vibration dampers (14) formed integrally on the hub body (12) and / or on the rotor blades (13) in order to dampen operational vibrations of the turbomachine rotor (10) .
    公开号:CH716014A2
    申请号:CH00222/20
    申请日:2020-02-24
    公开日:2020-09-30
    发明作者:Bornhorn Alfons；Spengler Sebastian；Weihard Stefan；Wurm Claudius；Leitenmeier Christoph；Aurahs Lutz
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbomachine rotor. The invention also relates to a method for producing such a turbo-engine rotor.
    [0002] Fluid flow machines such as turbines or compressors have stator-side assemblies and rotor-side assemblies. The rotor-side assemblies of a turbomachine include what is known as the turbomachine rotor, which has a shaft, a hub body and rotor blades which extend at least radially outward from the hub body.
    [0003] The rotor blades of a turbo-engine rotor are exposed to heavy loads during operation. For example, the blades of a turbo-machine rotor can be exposed to oscillations or vibrations during operation, which can lead to failure of the rotor blades. It is therefore already known from practice to install vibration-damping elements on a turbomachine rotor.
    [0004] DE 10 2009 010 502 A1 shows a turbo-engine rotor in which a damping wire extends between adjacent rotor blades. This damping wire serves as a vibration damper.
    [0005] US 2017/0191366 A1 discloses another turbo-engine rotor in which a slotted damper pin is used as a vibration damper between adjacent rotor blades.
    In fluid flow machine rotors known from the prior art, the vibration dampers are each designed as separate assemblies that must be manufactured separately and then installed on the fluid flow machine rotor. This is a disadvantage. There is a need to provide vibration damping on a turbomachine rotor more simply.
    Proceeding from this, the present invention is based on the object of creating a novel turbomachine rotor and a method for producing the same.
    [0008] This object is achieved by a turbo-engine rotor according to claim 1.
    The turbomachine rotor according to the invention comprises at least one radially inner shaft, a hub body which adjoins the shaft radially on the outside, rotor blades which, starting from the hub body, extend at least outwards and preferably radially inwards in the direction of the shaft, and integrally the hub body and / or formed on the rotor blades vibration dampers in order to dampen operational vibrations of the turbo engine rotor.
    The invention proposes integrally forming vibration dampers on the hub body and / or on the rotor blades of the turbomachine rotor in order to dampen oscillations and vibrations of the turbomachine rotor. The vibration dampers are therefore no longer separate assemblies that have to be manufactured separately and then installed or assembled, but rather integral vibration dampers that do not have to be manufactured separately and then assembled, but rather in the manufacture of the turbomachine rotor as an integral one Part of being trained.
    According to an advantageous development of the invention, friction vibration dampers are integrally formed on the hub body between adjacent rotor blades, which have friction surfaces extending in the radial direction and in the circumferential direction. As an alternative or in addition, deformation vibration dampers, which extend between adjacent rotor blades and have a curved contour, are integrally formed on the rotor blades radially outward from the hub body on outer rotor blade sections. Alternatively or additionally, friction vibration dampers and / or deformation vibration dampers are formed integrally on the rotor blades radially on the inside from the hub body and radially outside from the shaft on inner rotor blade sections. Alternatively or additionally, the rotor blades have sections of different strength. Such vibration dampers are particularly suitable for integral training.
    According to an advantageous development of the invention, the turbomachine rotor is monolithic or in one piece, in particular by an additive manufacturing process, in particular by 3D printing. The entire turbomachine rotor is monolithic and is therefore designed in one piece or in one piece. The same can be easily built using an additive manufacturing process, including the vibration dampers, which are integrally formed on the hub body and / or on the rotor blades.
    The method according to the invention for producing the turbomachine rotor is defined in claim 10.
    Preferred developments of the invention emerge from the subclaims and the following description. Embodiments of the invention are explained in more detail with reference to the drawing, without being restricted thereto. It shows:<tb> Fig. 1 <SEP> a highly schematic section from a first turbo-machine rotor;<tb> Fig. 2 <SEP> the detail II of FIG. 1;<tb> Fig. 3 <SEP> shows a highly schematic section from a second turbo-machine rotor;<tb> Fig. 4 <SEP> shows a highly schematic section from a third turbo-machine rotor;<tb> Fig. 5 <SEP> shows a highly schematic section from another turbo-machine rotor.
    Fig. 1 shows a highly schematic section of a turbo engine rotor 10 in the area of a radially inner shaft 11, a hub body 12 and blades 13. The shaft 11 is used to support the turbo engine rotor 10. The hub body 12 closes radially on the outside of the shaft 11 and surrounds the same outside at least in sections. The blades 13 are used to guide the flow of a medium and for this purpose have a flow inlet edge, a flow outlet edge and flow guide surfaces extending between the flow inlet edge and the flow outlet edge, which in particular form a suction side and a pressure side. The rotor blades 13 extend with outer rotor blade sections 13a, which serve to guide the flow, starting from the hub body 12 radially outwards, and with inner rotor blade sections 13b, which do not serve to guide the flow, starting from the hub body 12 in the direction of the shaft 11 radially inwards.
    On the turbomachine rotor 10, namely in Fig. 1 on the hub body 12, vibration dampers 14 are integrally formed in order to compensate for operational oscillations or vibrations of the turbomachine rotor 10, in particular those of the blades 13.
    As can be seen from detail II of FIG. 1 (see FIG. 2), a friction vibration damper 15, which provides the vibration damper 14, is formed integrally on the hub body 12 between two adjacent rotor blades 13 for this purpose. In the area of this friction vibration damper 15, the hub 12 is interrupted and therefore not continuously cohesively or materially formed, so that friction surfaces 16, 17 are formed which rub against one another during operation to dampen vibrations. These friction surfaces 16, 17 extend on the one hand in the radial direction and on the other hand in the circumferential direction. Corresponding sections of the hub 12 that are not cohesively or materially connected and therefore loosely adjoining one another overlap.
    As the detail II of Fig. 1 (see Fig. 2) can be seen, the respective frictional vibration damper 15 is preferably positioned eccentrically between the adjacent blades 13 viewed in the circumferential direction, the division ratio being selected depending on the vibration to be damped can.
    Fig. 3 shows a further highly schematic section of a turbo engine rotor 10 according to the invention in the area of the hub 12 and from the hub 12 outwardly extending blade sections 13a of the blades 13. In the embodiment according to the invention shown in Fig. 3 are integral to the Rotating blades 13, namely the outer rotating blade sections 13 a, are formed in each case between adjacent rotating blades 13, deformation vibration dampers 18 which provide the respective vibration damper 14. These deformation vibration dampers 18 engage on both sides with a material fit or material connection on the rotor blades 13, between which they extend, the deformation vibration dampers 18 having a curved or corrugated contour when viewed in the circumferential direction.
    In Fig. 3, seen in the radial direction, between the blades 13, integrally formed on the same, several deformation vibration dampers 18, their radial position and / or contour are adapted to the vibration modes of the particular vibration to be damped. In the event of an oscillation or vibration of the rotor blades 13, the deformation vibration damper 18 is subject to deformation and thus dampens the oscillation.
    Fig. 4 shows a section of another turbo engine rotor 10 according to the invention, again in the area of the shaft 11, the hub 12 and blades 13, wherein in the embodiment of FIG. 4, a vibration damper 14 is again integrally formed on the turbo engine rotor 10, and on the inner rotor blade sections 13b of the rotor blades 13, which do not serve to guide the flow. The vibration damper 14 shown in FIG. 4 is designed as a deformation vibration damper 18. The same can also be designed as a friction vibration damper.
    It should be pointed out again at this point that the inner rotor blade sections 13b of the guide vanes 13 extending between the shaft 11 and the hub 12 are not used to guide the flow. Only the outer rotor blade sections 13a of the rotor blades 13, which extend outwardly in the radial direction away from the hub body 12, are used for such flow guidance.
    Therefore, the inner rotor blade sections 13b extending between the hub body 12 and the shaft 11 can also be referred to as stiffening struts, which serve to stiffen the structure of the turbo engine rotor 10 between the shaft 11 and the hub body 12. Such stiffening struts can also be offset in the circumferential direction with respect to the flow-guiding rotor blade sections 13 a of the rotor blades 13.
    5 shows a section from a further turbo-engine rotor 10 according to the invention in the region of a rotor blade 13. For vibration damping, the rotor blade 13 has sections 19, 20 of different strength as vibration damper 14. This can be a section 20 or cavities that are filled with a different material structure than the sections 19 of the rotor blade 13 which surround the cavities. This also makes it possible to dampen oscillations and vibrations on the rotor blades 13 of the turbo-engine rotor 10.
    As already stated, the turbomachine rotor 10 is preferably a monolithic or one-piece or one-piece structure. The same is preferably produced using an additive manufacturing method, in particular by 3D printing.
    Details of the 3D printing of metallic components that are built up in layers by melting layers or layers of metal powder onto one another are familiar to the person skilled in the art addressed here. In order to melt the metal powder, it is exposed in particular via a laser beam.
    If the friction vibration dampers described above are to be formed during 3D printing, at least one metal powder layer is not exposed at least in sections and therefore not melted, so as not to form a cohesive or material connection here. In an analogous manner, sections or cavities 20 can be formed in the area of the rotor blades 13 which are filled with metal powder and then have different or different strengths than those sections 19 which surround the powder-filled cavities 20. In this way, vibration dampers 14 can accordingly be designed advantageously and simply during 3D printing.
    The turbo machine rotor 10 according to the invention can be a rotor of a turbine or a compressor. The turbine or the compressor can be an assembly of a turbocharger. The invention can also be used in other turbo-machine rotors, for example in compressors, steam turbines and aircraft engines.
    List of reference symbols
    10 turbo engine rotor 11 shaft 12 hub body 13 rotor blade 13a outer rotor blade section 13b inner rotor blade section 14 vibration damper 15 friction vibration damper 16 friction surface 17 friction surface 18 deformation vibration damper 19 section 20 section
    权利要求:
    Claims (12)
    [1]
    1. Turbomachine rotor (10),with a radially inner shaft (11),with a hub body (12) which connects radially on the outside of the shaft (11),with rotor blades (13) which, starting from the hub body (12), extend at least radially outwards and optionally in the direction of the shaft (11) radially inwards,with vibration dampers (14) formed integrally on the hub body (12) and / or on the rotor blades (13) in order to dampen operational vibrations of the turbomachine rotor (10).
    [2]
    2. Turbomachine rotor according to claim 1, characterized in that integral on the hub body (12) between each adjacent rotor blades (13) as vibration damper (14) friction vibration damper (15) are formed, which have friction surfaces (16, 17) extending in the radial direction and in the circumferential direction .
    [3]
    3. Turbomachine rotor according to claim 2, characterized in that the frictional vibration damper (15) is positioned eccentrically between the adjacent rotor blades (13), seen in the circumferential direction.
    [4]
    4. Turbomachine rotor according to one of claims 1 to 3, characterized in that integral to the blades (13) radially outward from the hub body (12) on outer blade sections (13a) as a vibration damper (14) each between adjacent blades (13) extending deformation vibration damper (18) are formed which have a curved contour.
    [5]
    5. Turbomachine rotor according to claim 4, characterized in that, viewed in the radial direction, several deformation vibration dampers (18) are formed, the radial position and / or contour of which are adapted to the vibration modes of a vibration to be damped.
    [6]
    6. Turbomachine rotor according to one of claims 1 to 5, characterized in that integral on the rotor blades (13) radially inside from the hub body (12) and radially outside from the shaft (11) on inner rotor blade sections (13b) as vibration damper (14) friction vibration damper ( 15) are formed.
    [7]
    7. Turbomachine rotor according to one of claims 1 to 6, characterized in that integral on the rotor blades (13) radially inward from the hub body (12) and radially outward from the shaft (11) on inner rotor blade sections (13b) as vibration damper (14) deformation vibration damper ( 18) are formed.
    [8]
    8. Turbomachine rotor according to one of Claims 1 to 7, characterized in that the rotor blades (13) have sections (19, 20) of different strength.
    [9]
    9. Turbomachine rotor according to one of claims 1 to 8, characterized in that the same is formed monolithically or in one piece.
    [10]
    10. The method for manufacturing a turbo-engine rotor according to one of claims 1 to 9, characterized in that the same is manufactured by an additive manufacturing method, in particular by 3D printing.
    [11]
    11. The method according to claim 10, characterized in that the friction vibration dampers (15) are formed in that, in the additive manufacturing process, at least one metal powder layer is not exposed and not melted at least in sections.
    [12]
    12. The method according to claim 10, characterized in that the sections (19, 20) of different strength are formed in that, in the additive manufacturing process, at least one metal powder layer is not exposed in sections and is not melted in order to form metal powder-filled cavities.
    类似技术:
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    同族专利:
    公开号 | 公开日
    KR20200111114A|2020-09-28|
    CN111706401A|2020-09-25|
    JP2020153371A|2020-09-24|
    DE102019106734A1|2020-09-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5257908A|1991-11-15|1993-11-02|Ortolano Ralph J|Turbine lashing structure|
    US5373922A|1993-10-12|1994-12-20|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Tuned mass damper for integrally bladed turbine rotor|
    DE102009010502B4|2009-02-25|2012-08-23|Siemens Aktiengesellschaft|Turbine blade, turbine blade and turbine|
    US8616848B2|2009-12-14|2013-12-31|Siemens Energy, Inc.|Turbine blade damping device with controlled loading|
    US20170191366A1|2016-01-05|2017-07-06|General Electric Company|Slotted damper pin for a turbine blade|
    DE102016204255A1|2016-03-15|2017-09-21|Siemens Aktiengesellschaft|Component for a turbomachine and method for its production|
    DE102016222869A1|2016-11-21|2018-05-24|MTU Aero Engines AG|A blade arrangement|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102019106734.0A|DE102019106734A1|2019-03-18|2019-03-18|Turbomachine rotor and method of making the same|
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