• 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:
    Leitgitter (10) of a turbomachine, wherein the guide grid (10) has a cast or rotated base body (11) and on the base body (11) via a generative manufacturing process applied vanes (12).
    公开号:CH715037A2
    申请号:CH5572019
    申请日:2019-04-25
    公开日:2019-11-29
    发明作者:Wurm Claudius
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a guide vane of a turbomachine and a method for producing the same.
    A turbomachine, such as a compressor or a turbine, has a rotor and a stator. The rotor of a turbomachine is bladed with several moving blades. The stator of a turbomachine includes a housing and typically a guide vane with several guide vanes.
    Baffles of turbomachines are either milled from the solid or completely cast according to practice. Such guide grids have both geometric and functional restrictions.
    There is a need for a new type of baffle for a turbomachine, which can be designed geometrically more freely and can be provided with other functions.
    Proceeding from this, the present invention has for its object to provide a novel guide grill of a turbomachine and a method for producing the same.
    This object is achieved by a guide vane of a turbomachine according to claim 1.
    The guide vane according to the invention has a cast or turned base body and guide vanes applied to the base body by means of a generative manufacturing process.
    Such a guide vane in hybrid construction or mixed construction with a cast or rotated base body and with guide vanes constructed via a generative or additive manufacturing process can provide novel blade geometries for the guide vanes. Further functions, e.g. be provided for sound absorption, heat protection or the like.
    The base body can be a separate base body specially for the guide grill. The base body can also be provided by another, already existing component of the turbocharger, e.g. from an insert or a heat protection of the turbocharger.
    According to an advantageous development, the guide vanes consist of a nickel-based alloy or a titanium-based alloy or a cobalt-based alloy. The guide vanes preferably consist of a nickel-chromium-iron alloy with niobium and molybdenum as well as with aluminum and titanium. These materials are particularly preferred both from a manufacturing perspective and from a functional perspective.
    The method for producing the guide vane according to the invention is defined in claim 4. The method comprises at least the following steps: providing the cast or rotated base body. Roughen the base body provided. Preheat the roughened body. Assembly of the guide vanes on the roughened and preheated base body using a generative manufacturing process. The guide vane according to the invention can be produced particularly advantageously with such a method.
    As already stated above, the base body can be a separate base body especially for the guide grill. The base body can also be provided by another, already existing component of the turbocharger, e.g. from an insert or a heat protection of the turbocharger.
    According to an advantageous development, the roughening of the base body is carried out over the full area such that the roughened base body has a roughness Rz between 25 and 32. The roughening of the base body with a roughness between margin no. 25 and margin no. 32 is particularly preferred in order to subsequently build up the guide vanes using the additive manufacturing process.
    According to an advantageous development, the roughened base body is preheated to a temperature between 200 ° C and 600 ° C. Preheating the roughened base body to a temperature in this temperature range over the entire surface is also particularly preferred for the subsequent assembly of the guide vanes via the additive manufacturing process.
    [0015] Preferred developments of the invention result 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 to this. It shows:
    Fig. 1 shows a section of a guide grill.
    [0016] The invention relates to a guide vane of a turbomachine. The invention further relates to a method for producing such a guide vane.
    Fig. 1 shows a section of a guide vane 10 of a turbomachine. The guide grid 10 can be a guide grid of a compressor or a guide grid of a turbine.
    The guide vane has a base body 11 and a plurality of guide vanes 12.
    The main body 11 of the guide vane 10 according to the invention is a cast or rotated main body. The base body 11 can be a separate base body specifically for the guide vane 10. The basic body
    CH 715 037 A2 can also be provided by another, already existing component of the turbocharger, e.g. from an insert or a heat protection of the turbocharger.
    The base body 11 preferably consists of an aluminum-silicon alloy, preferably of an AlSi alloy of the 4000 series. Other materials can also be used for the base body 11.
    The guide vanes 12 of the guide vane 10 are a generative manufacturing method applied or built up on the base body 11, which consist in particular of a nickel alloy or a titanium-based alloy or a cobalt-based alloy.
    As nickel-based alloys e.g. Hastelloy X, IN625; IN718; IN939 are used. As titanium-based alloys, e.g. TÌAI6V4, TiAI6Nb7 are used. As cobalt base alloys e.g. CoCr, MAR-M509 are used.
    Particularly preferably, the guide vanes 12 of the guide grid 10 consist of a nickel-chromium-iron alloy with components of niobium, molybdenum, aluminum and titanium.
    In order to provide such a guide vane 10, a cast or rotated base body 11 is first provided. As already stated, the base body 11 can be a separate base body especially for the guide grill. The base body 11 can also be provided by another, already existing component of the turbocharger, e.g. from an insert or a heat protection of the turbocharger. The base body 11 provided is then roughened. The roughened base body is then preheated. The guide vanes 12 are built up on the roughened and preheated base body by means of a generative manufacturing process.
    The roughening of the cast or turned base body is carried out over the entire surface, preferably by shot peening. A roughness of Rz 25 to Rz 32 is then set on the base body 11.
    After roughening the base body 11, the same is preheated, preferably over the entire surface to a temperature between 200 ° C and 600 ° C.
    The guide vanes 12 are built up on the roughened and preheated base body, namely via the generative or additive manufacturing process.
    Before the actual construction of the guide vanes 12 using the additive manufacturing process, the roughened and preheated base body is further heated, at least at those points at which the guide vanes are built, using an energy source, preferably using a laser.
    The laser or the energy source is preferably operated with a power between 400 W and 1000 W in order to further heat the corresponding areas of the base body before the actual construction of the guide vanes.
    Only after this further heating of the roughened and preheated base body with the aid of the energy source, in particular the laser, is the actual construction of the guide vanes 12 then carried out using the additive manufacturing method, and preferably in that a first layer made of a metallic powder Nickel-chromium-iron alloy is applied to the corresponding sections of the base body 11 and then melted using a laser. This takes place layer by layer in order to gradually build up the guide vanes 12.
    It is also possible to further heat the base body 11 after roughening and preheating over the entire area via the energy source, in particular via the laser, and then to apply a coating over the entire area to the base body, preferably made of the nickel-chromium-iron alloy material thus also to provide a functional layer 14 in those sections 13 of the base body 11 which are formed or positioned between the guide vanes 12. For example, a section can be formed in the sections 13 between adjacent guide vanes 12, which serves for sound absorption. Furthermore, 12 holes and grooves for flow guidance can be formed in the sections 13 between adjacent guide vanes.
    Reference symbol list [0032]
    guide grid
    body
    vane
    section
    functional layer
    CH 715 037 A2
    权利要求:
    Claims (15)
    [1]
    claims
    1. Guide vane (10) of a turbomachine, characterized in that the guide vane (10) has a cast or turned base body (11) and guide vanes (12) applied to the base body (11) via a generative manufacturing process.
    [2]
    2. Guide vane according to claim 1, characterized in that the guide vanes (12) consist of a nickel-based alloy or a titanium-based alloy or a cobalt-based alloy.
    [3]
    3. guide vane according to claim 2, characterized in that the base body (11) consists of an aluminum-silicon alloy.
    [4]
    4. Guide vane according to one of claims 1 to 3, characterized in that the guide vanes (12) consist of a nickel-chromium-iron alloy with niobium and molybdenum as well as with aluminum and titanium.
    [5]
    5. guide vane according to claim 4, characterized in that the base body (11) consists of an AISi alloy of the 4000 series.
    [6]
    6. A method for producing a guide vane according to one of claims 1 to 5, with the following steps providing the cast or rotated base body (11);
    Roughening the base body (11) provided;
    Preheating the roughened base body (11);
    Building up the guide vanes (12) using a generative manufacturing process on the roughened and preheated base body (11).
    [7]
    7. The method according to claim 6, characterized in that the roughening of the base body (11) is carried out by shot peening.
    [8]
    8. The method according to claim 6 or 7, characterized in that the roughening of the base body (11) is carried out such that the roughened base body (11) has a roughness Rz between 25 and 32.
    [9]
    9. The method according to any one of claims 6 to 8, characterized in that the base body (11) is roughened over the entire surface.
    [10]
    10. The method according to any one of claims 6 to 9, characterized in that the roughened base body (11) is preheated over the entire surface.
    [11]
    11. The method according to any one of claims 6 to 10, characterized in that the roughened base body (11) is preheated to a temperature between 200 ° C and 600 ° C.
    [12]
    12. The method according to any one of claims 6 to 11, characterized in that prior to assembly of the guide vanes (12), the preheated base body (11) at least at those locations of the base body (11) at which the guide blades (12) are built up with the aid an energy source, in particular a laser, is further heated.
    [13]
    13. The method according to claim 12, characterized in that the energy source, in particular the laser, is operated with a power between 400 W and 1000 W.
    [14]
    14. The method according to claim 12 or 13, characterized in that the
    [15]
    15. The base body (11) after the roughening and preheating is heated over the entire area via the energy source, and that a coating is then applied over the entire area to the base body (11), so that in those sections (13) of the base body (11) that between the guide vanes (12) are positioned to provide a functional layer (14).
    CH 715 037 A2
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2361720B1|2012-12-12|Method for repairing and/or upgrading a component, especially of a gas turbine
    DE102014208801A1|2015-11-12|Seal, method for producing a seal and turbomachine
    DE60124042T2|2007-05-03|Self-cleaning brazing material
    WO2007085230A1|2007-08-02|Guide blade segment of a gas turbine and method for its production
    CH701554A2|2011-01-31|Soldering and materials for repair of a component.
    EP2082826B1|2017-02-22|Methods of repairing engine components
    DE102007050142A1|2009-04-23|Method of making a blisk or bling, component and turbine blade made therewith
    CH705750A1|2013-05-15|A process for the production of components or portions, which consist of a high-temperature superalloy.
    WO2016087140A1|2016-06-09|Method for producing a rotor blade, and blade obtained by such a method
    DE10337094A1|2005-03-03|Inlet lining for gas turbines and method for producing the same
    EP2038083B1|2017-09-13|Method for repairing and/or replacing individual elements of a gas turbine component
    DE102015207017A1|2016-10-20|Method for producing covered wheels
    EP2808488A1|2014-12-03|TiAl blade with surface modification
    EP3501721A1|2019-06-26|Method for joining components and device
    DE102018112562A1|2019-11-28|Grille of a turbomachine and method for producing the same
    EP2766149B1|2016-02-10|Method for repairing surface damage to a flow engine component
    EP3238863A1|2017-11-01|Method for producing a rotor blade for a fluid flow engine
    DE102017200749A1|2018-07-19|Layer system with two intermediate layers and methods
    EP2781622A1|2014-09-24|Generative method particularly for producing a coating, device for carrying out the method, coating and a component manufacturing method and a component
    EP3508690A1|2019-07-10|Turbine blade and method for its manufacture
    DE102013214781B3|2015-02-26|Method for repairing a pick-up hook for guide vanes
    WO2010149141A2|2010-12-29|Method for producing and/or repairing a blade for a turbo-machine
    DE102019217434A1|2021-05-12|Process for the layer-by-layer additive manufacturing of a composite material
    EP3248727A1|2017-11-29|Turbine blade and method of manufacture the turbine blade
    DE102006061448A1|2008-06-26|Method for producing a blisk or a bling and component produced therewith
    同族专利:
    公开号 | 公开日
    US20190358756A1|2019-11-28|
    RU2019116080A|2020-11-24|
    JP2019203507A|2019-11-28|
    DE102018112562A1|2019-11-28|
    KR20190134484A|2019-12-04|
    CN110529193A|2019-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018112562.3A|DE102018112562A1|2018-05-25|2018-05-25|Grille of a turbomachine and method for producing the same|
    [返回顶部]