• 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:
    Radial turbine rotor (10), having a rotor main body (11); and with integrally formed on the rotor base body (11) blades (12); wherein the rotor base body (11) has a cavity structure (13).
    公开号:CH712770A2
    申请号:CH00871/17
    申请日:2017-07-05
    公开日:2018-01-31
    发明作者:Wurm Claudius
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a radial turbine rotor and a method for producing the same.
    Fig. 1 shows a cross section through a known from the prior art radial turbine rotor 1. The radial turbine rotor 1 has a rotor base 2 and a plurality of integrally formed on the rotor base 2 blades 3. The blades 3 have surfaces designed as suction and pressure sides that serve to guide the flow. In radial turbine rotors known from practice, the basic rotor body 2 of the radial turbine rotor 1 is designed as a solid component. Such a rotor base body 2 with the rotor blades 3 integrally formed thereon is preferably produced by casting, in particular by means of an investment casting process.
    Based on this, the present invention seeks to provide a novel radial turbine rotor and method for manufacturing the same.
    This object is achieved by a radial turbine rotor according to claim 1. According to the invention, the basic rotor body has a cavity structure.
    The rotor base body of the radial turbine rotor according to the invention has a hollow structure. Such a hollow structure enables the weight of the radial turbine rotor to be reduced compared to the radial turbine rotors known from the prior art.
    A radial turbine rotor with a lower weight can be accelerated and decelerated significantly faster. As a result, the dynamics of the radial turbine rotor or of a turbine having the radial turbine rotor can be significantly improved. This is particularly advantageous if the radial turbine rotor is part of an exhaust gas turbocharger. A radial turbine rotor with a lower mass also allows bearings of the radial turbine rotor to be designed more cost-effectively. Furthermore, so-called containment protection of the turbine, which is intended to prevent fragments of the radial turbine rotor from bursting into the environment when the radial turbine rotor bursts, is less difficult. In the case of a lighter radial turbine rotor, in the event of its bursting, the energy to be intercepted is lower, so that the containment protection can be carried out more easily and cost-effectively.
    According to an advantageous development of the invention, the cavity structure is stiffened by at least one web. In this way, an optimally adapted rigidity of the radial turbine rotor can be provided despite the reduced weight.
    According to an advantageous development of the invention, openings are formed on a front side and / or on a rear side of the rotor base outside of flow-guiding surfaces, through which openings the cavity structure is accessible from the outside. On the one hand, these openings ensure that the radial turbine rotor can be manufactured easily, and they also serve to set a defined roughness on the inner surfaces of the cavity.
    According to an advantageous development of the invention, a defined average roughness Ra is set on inner surfaces of the cavity structure, which is between 2 µm and 10 µm. This average roughness RA on the inner surfaces of the cavity structure, which differs from the average roughness RA on the flow-guiding surfaces of the rotor blades, is particularly preferred for providing a radial turbine rotor with optimal concentricity properties.
    The method for producing the radial turbine rotor according to the invention is defined in claim 6.
    Preferred further 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:
    1 shows a cross section through a radial turbine rotor according to the prior art;
    2 shows a cross section through a first radial turbine rotor according to the invention;
    3 shows a cross section through a second radial turbine rotor according to the invention; and FIG. 4: a cross section through a third radial turbine rotor according to the invention.
    The invention relates to a radial turbine rotor, in particular a radial turbine rotor for a turbocharger. The invention further relates to a method for producing such a radial turbine rotor.
    2 shows a cross section through a radial turbine rotor 10 according to the invention. The radial turbine rotor 10 has a rotor base body 11 and also a plurality of rotor blades 12 which are integrally formed on the rotor base body 11 Cavity structure 13 introduced. This cavity structure 13 can be formed by a single cavity or also by a plurality of cavities separated from one another by webs or partitions.
    3 shows a cross section through a further radial turbine rotor 10 according to the invention, the cavity structure 13 in FIG. 3 being stiffened by a web 14 extending in the axial direction. This web 14 extends
    CH 712 770 A2 in FIG. 3 in the axial direction between a front side 15 and a rear side 16 of the basic rotor body 11 of the radial turbine rotor 10 according to the invention.
    Additionally or alternatively to the web 14 extending in the axial direction, further webs can stiffen the cavity structure 13, which can extend transversely, in particular perpendicularly, to the web 14.
    In the embodiment of FIG. 4, a radial turbine rotor 10 is shown, in which openings 17, 18 are formed in the region of the front 15 and in the region of the rear 16 of the rotor base body 11 on non-flow-guiding surfaces, that is to say outside the flow-guiding surfaces which the cavity structure 13 is accessible from the outside. Such openings 17, 18 have advantages in connection with the manufacture or manufacture of the radial turbine rotor 10 according to the invention.
    According to a preferred embodiment of the invention it is provided that a defined roughness is set on inner surfaces 19 of the cavity structure 13, the average roughness Ra being between 2 pm and 10 pm.
    The invention further relates to a method for producing such a radial turbine rotor 10. The rotor base body 11 is together with the blades 12 integrally formed on the rotor base body 11 to form the cavity structure 13 and in FIG. 4 to form the openings 17, 18 Generative manufacturing process produced as a monolithic component, a generative manufacturing process also being referred to as an additive manufacturing process.
    In the additive manufacturing process residual material, for example a residual granulate of a powder bed, which collects in the additive manufacturing process in the cavity structure 13, can be removed from the cavity structure 13 via the openings 17, 18. The openings 17, 18 can also be used as inspection openings to examine material properties or to carry out quality control. The openings 17, 18 can be closed again after the inspection.
    Furthermore, the openings 17, 18 are suitable for subsequently setting the defined average roughness Ra on the inner surfaces 19 of the cavity structure 13. For example, the roughness can be set using a mechanical method, for example by means of vibratory grinding, in which case grinding wheels are then introduced into the cavity structure 13 via the openings 17, 18 and executed. Furthermore, the roughness can be set using a physico-chemical method in which, in order to set the average roughness on the inner surfaces 19 of the cavity structure 13, a liquid medium is introduced into the cavity structure 13 via the openings 17 and is carried out therefrom.
    The invention accordingly proposes a radial turbine rotor 10, the basic rotor body 11 of which has a cavity structure 13. The cavity structure 13 can be stiffened via at least one web 14. Bores 17, 18 on non-flow-guiding surfaces of the radial turbine rotor 10, through which the cavity structure 13 is accessible from the outside, are used to remove residual material and to set the defined roughness on inner surfaces of the cavity structure 13.
    Reference symbol list [0022]
    Radial turbine rotor
    Rotor body
    blade
    Radial turbine rotor
    Rotor body
    blade
    cavity structure
    web
    front
    back
    opening
    opening
    Inner surface
    CH 712 770 A2
    权利要求:
    Claims (9)
    [1]
    claims
    1. Radial turbine rotor (10), with a rotor base body (11);
    Blades (12) integrally formed on the rotor base body (11);
    characterized in that the basic rotor body (11) has a cavity structure (13).
    [2]
    2. Radial turbine rotor according to claim 1, characterized in that the cavity structure (13) has one or more cavities.
    [3]
    3. Radial turbine rotor according to claim 1 or 2, characterized in that the cavity structure (13) is stiffened by at least one web (14).
    [4]
    4. Radial turbine rotor according to one of claims 1 to 3, characterized in that openings (17, 16) are formed on a front (15) and / or on a rear (16) of the rotor base body (11) outside of flow-guiding surfaces, via which the cavity structure (13) is accessible from the outside.
    [5]
    5. Radial turbine rotor according to one of claims 1 to 4, characterized in that a defined average roughness Ra is set on inner surfaces (19) of the cavity structure (13), which is between 2 µm and 10 µm.
    [6]
    6. A method for producing a radial turbine rotor (10) according to one of claims 1 to 5, characterized in that the same is produced via a generative manufacturing process as a monolithic component.
    [7]
    7. The method according to claim 6, characterized in that in the additive manufacturing process residual material is discharged via the openings (17, 18) from the cavity structure (13).
    [8]
    8. The method according to claim 6 or 7, characterized in that the defined average roughness Ra is set via the openings (17, 18) on the inner surfaces (19) of the cavity structure (13).
    [9]
    9. The method according to claim 8, characterized in that the roughness is set via a mechanical method and / or a physico-chemical method.
    CH 712 770 A2
    CH 712 770 A2
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    同族专利:
    公开号 | 公开日
    JP6843711B2|2021-03-17|
    KR20180010151A|2018-01-30|
    CN107642382A|2018-01-30|
    DE102016213238A1|2018-01-25|
    JP2018013127A|2018-01-25|
    CH712770B1|2021-12-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPS5925083B2|1979-07-30|1984-06-14|Nissan Motor|
    JPS61215401A|1985-03-20|1986-09-25|Yanmar Diesel Engine Co Ltd|Turbine wheel for supercharger|
    DE102006048784A1|2006-10-12|2008-04-17|Man Diesel Se|Compressor for a turbocharger and method for its cooling|
    KR101960715B1|2012-08-02|2019-03-22|한화파워시스템 주식회사|Method for manufacturing a impeller and Method for manufacturing a turbine wheel|
    DE102012215895A1|2012-09-07|2014-03-13|Robert Bosch Gmbh|Paddle wheel for a turbomachine and method for producing a turbine wheel for a turbomachine|
    DE102013226664A1|2013-12-19|2015-06-25|Continental Automotive Gmbh|Turbine rotor and method of manufacturing the turbine rotor|
    JP2016037901A|2014-08-07|2016-03-22|日立金属株式会社|Impeller|
    DE102016213296A1|2016-07-20|2018-01-25|Man Diesel & Turbo Se|Turbomachine and method for producing the same|
    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
    DE102016213238.5A|DE102016213238A1|2016-07-20|2016-07-20|Radial turbine rotor and method of making same|
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