• 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:
    Guide vane arrangement (1) for a turbomachine, with several guide vanes (2) arranged next to one another in the circumferential direction of the guide vane arrangement, each guide vane (2) having an inner shroud (4) on which the guide vanes (2) are connected to one another, with the inner shroud ( 4) a first bore (7) and a second bore (8) are made in each of the guide vanes (2) in such a way that the first bore (7) of the inner shroud (4) of the respective guide vane (2) with the one in the inner shroud (4 ) a second bore (8) introduced in the circumferential direction to a first side (9) directly adjacent to a first side (9) is aligned, and the second bore (8) of the inner shroud (4) of the respective guide vane (2) with the one in the inner shroud ( 4) a first bore (7) introduced in the circumferential direction directly adjacent to a second side (10) directly adjacent guide vane (2) is aligned, and through the aligned bores (7, 8) Adjacent guide vanes (2) extend connecting elements by means of which the respective directly adjacent guide vanes (2) are connected in the region of the inner shrouds (4) of the same.
    公开号:CH712765B1
    申请号:CH00694/17
    申请日:2017-05-29
    公开日:2021-03-31
    发明作者:Mokulys Thomas；Schloter Markus；Zerzau Mathias；Sinz Claus
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a guide vane arrangement of a turbomachine.
    A turbomachine typically has at least one rotor-side rotor blade arrangement composed of rotor blades positioned next to one another in the circumferential direction, as well as at least one stator-side guide vane arrangement composed of several guide vanes positioned next to one another in the circumferential direction. A rotor blade arrangement composed of a plurality of rotor blades positioned next to one another in the circumferential direction is also referred to as a rotor blade ring and a guide vane arrangement composed of a plurality of guide vanes positioned next to one another in the circumferential direction is also referred to as a guide vane ring. The present invention relates to a guide vane arrangement with a plurality of guide vanes arranged next to one another in the circumferential direction of the guide vane arrangement. Each guide vane has an airfoil and an inner shroud, the inner shroud typically adjoining a hub of a rotor of the turbomachine. The guide vanes are connected to one another at their inner shrouds. The guide vanes are typically received or held in a guide vane ring via radially outer vane roots.
    For connecting the guide vanes of a guide vane arrangement to the inner shrouds, different approaches are known from the prior art. For example, in the case of relatively small guide vanes, the vane blades of which have a maximum radial extension of 400 mm, the inner shrouds of adjacent guide vanes are typically connected to one another via caulking wires. In the case of larger guide blades, the blade blades of which have an extension of more than 400 mm in the radial direction, the inner shrouds of adjacent guide blades are typically connected by welding.
    The variants known from practice for connecting adjacent guide vanes in a guide vane arrangement in the area of their inner shrouds are therefore dependent on the size of the guide vanes. There is a need for a guide vane arrangement in which the guide vanes can be connected to one another in a uniform manner in the area of their inner shrouds, regardless of their size.
    Proceeding from this, the invention is based on the object of creating a novel guide vane arrangement of a turbomachine. This object is achieved by a guide vane arrangement of a turbomachine according to claim 1. According to the invention, a first bore and a second bore are made in each of the inner shrouds of the guide vanes in such a way that the first bore of the inner shroud of the respective guide vane is aligned with the second bore introduced into the inner shroud of a guide vane immediately adjacent to a first side as seen in the circumferential direction, and that the second bore of the inner shroud of the respective guide vane is aligned with the first bore made in the inner shroud of a guide vane, seen in the circumferential direction, which is immediately adjacent to a second side. Connecting elements extend through the aligned bores of directly adjacent guide vanes, via which the respective directly adjacent guide vanes are connected in the area of the inner shrouds of the same.
    The present invention proposes a guide vane arrangement of a turbomachine, in which the inner shrouds of adjacent guide vanes are connected to each other in a completely new way, through a concept that can be used across all sizes regardless of the size of the guide vanes. This enables a particularly advantageous connection of the guide vanes of a guide vane ring in the area of the inner shrouds of the guide vanes.
    According to a first development of the guide vane arrangement according to the invention, the respective first hole is a through hole and the respective second hole is a threaded hole, the respective connecting element being a screw with a screw head portion in the respective first hole and with a screw thread portion in the respective second bore extends. The first development of the invention is particularly preferred since it enables a particularly simple connection of guide vanes in the area of their inner shrouds.
    According to a second, alternative development of the guide vane assembly according to the invention, the respective first hole is a through hole and the respective second hole is a through hole, the respective connecting element being a screw with a screw head portion in one of the holes and with a screw thread portion in the other of the bores, which receives a nut cooperating with the screw thread portion, extends. With this development of the invention, too, adjacent guide vanes can be easily connected to one another in the area of their inner shrouds in the sense of a counter screw connection.
    According to a third, also alternative development of the guide vane arrangement according to the invention, the respective first bore is a through bore and the respective second bore is a through bore, wherein the respective connecting element is a wedge pin or cylinder pin with a section in one of the bores and with another Section is jammed in the other of the holes. This alternative also allows a simple connection of adjacent guide vanes in the area of their inner shrouds.
    The holes and connecting elements described here can in principle also be used to connect the guide vane ring on the outside, when using guide vanes with an integral foot (or outer shroud) instead of an outer ring. The bores preferably extend perpendicular to the boundary surfaces of the inner shrouds that are adjacent to one another. This is particularly preferred for the connection of adjacent guide vanes in the area of their inner shrouds.
    Preferably, the center axes of the bores close with a tangent to the respective circumferential position of the respective inner shroud. The angle required for this results from the number of blades in the guide vane arrangement and is in the range between 1 ° and 6 °, preferably an angle between 2 ° and 5 °, particularly preferably an angle between 3 ° and 4 °. This ensures that the aligned bores in the inner shrouds, despite their straight extension, approximately follow the circulation of the guide vane arrangement in the area of the inner shrouds and thus enable the connection of adjacent guide vanes in the area of their inner shrouds.
    Preferably, the inner shroud of the respective guide vane on the first side, seen in the circumferential direction, covers the first bore introduced into the inner shroud of the guide vane immediately adjacent on this first side, and on the second side, seen in the circumferential direction, directly into the inner shroud on this second side adjacent guide vane drilled second hole. Connecting elements are kept captive in this way.
    The shroud screw connection can be used regardless of the type of external fastening, so that blades with an integral foot and shroud can also be used.
    Preferred developments of the invention emerge from the dependent claims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted thereto. 1 shows a perspective view of a guide vane arrangement according to the invention; 2 shows a cross section through a first guide vane arrangement according to the invention in the area of two inner shrouds without connecting elements; 3 shows a cross section through a second guide vane arrangement according to the invention in the area of two inner shrouds without connecting elements; and FIG. 4 shows a cross section through a third guide vane arrangement according to the invention in the area of two inner shrouds without connecting elements.
    The present invention relates to a guide vane arrangement of a turbomachine, for example a compressor or a turbine.
    1 shows a perspective arrangement of a guide vane arrangement 1, designed as a guide vane ring, comprising a plurality of guide vanes 2 (i), i = 1-N positioned next to one another in the circumferential direction of the guide vane arrangement. Each guide vane 2 has an airfoil 3 extending in the radial direction, with an inner shroud 4 of the respective guide vane 2 at a radially inner end of the airfoil 3 and a blade root, which is not explicitly shown, of the respective guide vane 2 at a radially outer end of the respective airfoil 3 Guide vane 2 is formed. With its blade root, each guide vane 2 is inserted into a so-called guide vane ring 6 of the guide vane arrangement 1 and held in the same. Adjacent guide vanes 2 are connected to one another at their inner shrouds 4.
    FIG. 2 shows a cross section through the guide vane arrangement 1 of FIG. 1 in the area of inner shrouds 4 of two directly adjacent guide vanes 2 (i) and 2 (i + 1). A first bore 7 and a second bore 8 are made in the inner shroud 4 of each of the guide vanes 2 (i), 2 (i + 1). These two bores 7, 8 are made in the inner shrouds 4 of the guide vanes 2 in such a way that the first bore 7 of the inner shroud 4 of the guide vane 2 (i) with the guide vane in the inner shroud 4 of the guide vane, viewed in the circumferential direction, directly adjacent to a first side 9 2 (i + 1), the second bore 8 introduced is aligned, whereas the second bore 8 of the inner shroud 4 of the guide vane 2 (i) is aligned with the guide vane 2 (i-1) which is directly adjacent to a second side 10 in the circumferential direction in the inner shroud 4. (not shown in Fig. 2) introduced first bore 7 is aligned.
    The inner shroud 4 of the guide vane 2 (i) covers on the first side 9 seen in the circumferential direction in the inner shroud 4 of the guide vane 2 (i + 1) immediately adjacent to this first side 9 and the first bore 7 introduced in the circumferential direction seen from the second side 10, the second bore 8 made in the inner shroud 4 of the guide vane 2 (i-1) immediately adjacent to this second side 10 (not shown in FIG. 2).
    It is therefore within the meaning of the invention to introduce a first bore 7 and a second bore 8 into the inner shrouds 4 of the guide vanes 2 of a guide vane arrangement 1, which are introduced into the guide vanes 2, namely into the inner shrouds thereof, that in Area of directly adjacent guide vanes 2 and thus directly adjacent inner shrouds 4, first bores 7 and second bores 8 are aligned with one another.
    Connecting elements (not shown) extend through aligned bores 7, 8 of directly adjacent guide vanes 2 or directly adjacent inner shrouds 4, via which the respective immediately adjacent guide vanes 2 are connected in the region of their inner shrouds 4.
    In the embodiment of Fig. 2, the respective first bore 7 of the respective inner shroud 4 of the respective guide vane 2 is designed as a through hole and the respective second bore 8 of the respective inner shroud 4 of the respective guide vane 2 is designed as a threaded hole. In this case, a screw is used as the connecting element, which extends with its respective screw head section into the respective first bore 7 designed as a through hole and with its respective screw thread section into the respective second bore 8.
    After the connection of two immediately adjacent guide vanes 2 in the area of their inner shrouds 4, another guide vane 2 is pushed into the guide vane ring 6 in the radial direction, with its inner shroud 4 then the previously formed screw connection between two guide vanes 2 or the respective aligned bores 7 , 8 covered on one side. Even if a connection between the guide vanes 2 should therefore loosen in the area of their inner shrouds 4, it is ensured that the corresponding connecting elements are held in their position in the area of the inner shrouds 4. Accordingly, the same cannot get into the area of the rotor of the turbomachine and damage it.
    Fig. 3 shows a variant of the guide vane arrangement according to the invention, in which both the first bore 7 and the second bore 8, which is introduced into the inner shroud 4 of the respective guide vane 2, is designed as a through hole. In this case, screws are also preferably used as connecting elements, the respective screw extending with a screw head into one of the respective bores 7 or 8 and with its screw thread section extending into the respective other bore 8 or 7, which then has a receives cooperating nut with the respective screw thread section.
    A further variant of the guide vane arrangement according to the invention is shown in FIG. 4, with the bores 7, 8 in FIG. 4 again being designed as through bores in accordance with FIG. 3, but as wedge-shaped bores. Connecting elements designed as wedge pins or cylindrical pins then interact with these bores, each wedge pin extending through two aligned bores 7, 8 of directly adjacent shrouds 4 of directly adjacent guide vanes 2. These bores 7, 8 have a conical or funnel-like or frustoconical contour in cross section.
    On the sides 9, 10 of the inner shrouds, on which in the area of the guide vanes 2 and the inner shrouds 4, a directly adjacent guide vane with its respective inner shroud 4 is connected, the boundary surfaces of the inner shrouds 4, inclined relative to the axial direction, extend the bores 7, 8 run perpendicular to these boundary surfaces of the inner shrouds 4.
    The central axes of the bores 7, 8 form an angle between 1 ° and 6 °, preferably between 2 ° and 5 °, particularly preferably between 3 ° and 4 °, with a tangent to the respective circumferential position of the respective inner shroud 4, so that the aligned bores 7, 8, which run in a straight line, approximately follow the orbit of the guide vanes 2 in the area of their inner shrouds 4. The angle required for this results from the number of blades in the guide blade arrangement.
    The invention therefore proposes a completely new type of connection between guide vanes 2 of a guide vane arrangement 1 in the area of its inner shrouds 4 (or also on its outer shrouds). In the inner shrouds 4 of the guide vanes 2, two bores are preferably made, whereby on the sides 9, 10 of the inner shroud 4 of each guide vane 2, two bores 7, 8 of directly adjacent guide vanes and thus directly adjacent inner shrouds 4 are aligned, through which the Guide vanes 2 extend in the area of their inner shrouds 4 connecting elements which, due to their position, are covered by the inner shroud 4 of other adjacent guide vanes 2, so that the connecting elements do not fall out of the bores 7, 8 and into can reach the area of a rotor of the turbomachine.
    The invention can be used in different fluid flow machines of different sizes, both in turbines and in compressors. The invention is particularly preferably used in a guide vane arrangement for a steam turbine.
    权利要求:
    Claims (6)
    [1]
    1. Guide vane arrangement (1) for a turbomachine,with several guide vanes (2) arranged next to one another in the circumferential direction of the guide vane arrangement, each guide vane (2) having an inner shroud (4) on which the guide vanes (2) are connected to one another,characterized in thata first bore (7) and a second bore (8) are made in the inner shroud (4) of the guide vanes (2) in such a way that the first bore (7) of the inner shroud (4) of the respective guide vane (2) with the in the inner shroud (4) of a second bore (8) introduced in the circumferential direction to a first side (9) directly adjacent to a guide vane (2) is aligned, and the second bore (8) of the inner shroud (4) of the respective guide vane (2) is aligned with the in the inner shroud (4) of a guide vane (2) directly adjacent to a second side (10), seen in the circumferential direction, is aligned first bore (7), and thatconnecting elements extend through the aligned bores (7, 8) of directly adjacent guide vanes (2), via which the respective directly adjacent guide vanes (2) are connected in the area of the inner shrouds (4) of the same.
    [2]
    2. Guide vane arrangement according to claim 1, characterized in that the inner shroud (4) of the respective guide vane (2) on the first side (9) seen in the circumferential direction, the guide vane (9) directly adjacent to this first side (9) in the inner shroud (4). 2) first bore (7) and on the second side (10), seen in the circumferential direction, covers the second bore (8) made in the inner shroud (4) of the guide vane (2) immediately adjacent to this second side (10).
    [3]
    3. Guide vane arrangement according to claim 1 or 2, characterized in that the respective first bore (7) is a through bore and the respective second bore (8) is a threaded bore, and that the respective connecting element is a screw that extends with a screw head portion in the respective first bore (7) and with a screw thread portion in the respective second bore (8).
    [4]
    4. Guide vane arrangement according to claim 1 or 2, characterized in that the respective first bore (7) is a through bore and the respective second bore (8) is a through bore, and that the respective connecting element is a screw which is with a screw head portion in a of the bores (7, 8) and with one screw thread section into the other of the bores (8, 7), which receives a nut cooperating with the screw thread section.
    [5]
    5. Guide vane arrangement according to claim 1 or 2, characterized in that the respective first bore (7) is a through bore and the respective second bore (8) is a through bore, and that the respective connecting element is a wedge pin or cylinder pin with a section in one of the bores (7, 8) and with another section in the other of the bores (8, 7) is jammed.
    [6]
    6. Guide vane arrangement according to one of claims 1 to 5, characterized in that the first and second bores (7, 8) extend perpendicular to the boundary surfaces of the inner shrouds (4) adjoining one another.
    类似技术:
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    CH705377A1|2013-02-15|A process for reconditioning a rotor of a turbomachine.
    WO2005010323A1|2005-02-03|Device for fixing the blade root on a turbomachine
    EP3390784B1|2020-04-01|Continuous flow machine having multiple guide vane stages and method for partially disassembling a continuous flow machine of this type
    WO2018082837A1|2018-05-11|Housing arrangement for a turbomachine, and method for assembling a housing arrangement of this type
    EP3015652A1|2016-05-04|Rotor blade for a turbine
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    同族专利:
    公开号 | 公开日
    KR20180013752A|2018-02-07|
    JP6991007B2|2022-01-12|
    CH712765A2|2018-01-31|
    JP2018017236A|2018-02-01|
    CN107664044A|2018-02-06|
    DE102016113912A1|2018-02-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPS52143311A|1976-05-24|1977-11-29|Toshiba Corp|Movable blade connecting apparatus of turbo machinery|
    JPH10196308A|1997-01-10|1998-07-28|Mitsubishi Heavy Ind Ltd|Integrated segment structure stationary blade and manufacture therefor|
    EP0903467B1|1997-09-17|2004-07-07|Mitsubishi Heavy Industries, Ltd.|Paired stator vanes|
    US6158104A|1999-08-11|2000-12-12|General Electric Co.|Assembly jig for use with integrally covered bucket blades|
    EP1707743A1|2005-03-18|2006-10-04|Siemens Aktiengesellschaft|Segment with minimum two blades, turbine element and method to mount a segment|
    US7591634B2|2006-11-21|2009-09-22|General Electric Company|Stator shim welding|
    DE102010041808B4|2010-09-30|2014-10-23|Siemens Aktiengesellschaft|Blade segment, turbomachinery and process for their preparation|
    JP5342579B2|2011-02-28|2013-11-13|三菱重工業株式会社|Stator blade unit of rotating machine, method of manufacturing stator blade unit of rotating machine, and method of coupling stator blade unit of rotating machine|
    法律状态:
    2018-07-31| PFA| Name/firm changed|Owner name: MAN ENERGY SOLUTIONS SE, DE Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102016113912.2A|DE102016113912A1|2016-07-28|2016-07-28|Guide vane arrangement of a turbomachine|
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