• 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:
    A method for producing a toroidal core for the casting production of a nozzle ring of an axial turbine, wherein elements are mounted on an outer support element, which corresponds to an outer cover ring of a nozzle ring to be produced, and on an inner support element which corresponds to an inner cover ring of a nozzle ring to be produced, the guide vanes of the produced Corresponding to the nozzle ring, wherein the assembly of the outer support member, the inner support member and the elements mounted on the support elements are encapsulated with a ceramic material, being removed from the encapsulated arrangement, the support members and the elements mounted on the support elements and then a remaining blank the ceramic material for providing the toroidal core is hardened, and wherein on the elements which correspond to the guide vanes of the nozzle ring to be produced, prior to encapsulation of the arrangement with the ceramic material on Set pieces are mounted, which define a defined transition radius between the vanes and at least one cover ring, preferably two cover rings, the nozzle ring to be produced.
    公开号:CH713505A2
    申请号:CH00059/18
    申请日:2018-01-18
    公开日:2018-08-31
    发明作者:Maurer Helmuth
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    Description [0001] The invention relates to a method for producing a toroidal core for the production of a nozzle ring of an axial turbine by casting. Furthermore, the invention relates to a method for the production of a nozzle ring by casting using such a toroidal core.
    From DE 20 2014 002 981 U1 the basic structure of a nozzle ring of an axial turbine is known. A nozzle ring of an axial turbine has an outer cover ring, an inner cover ring as well as extending between the outer cover ring and the inner cover ring extending vanes.
    Typically, the guide vanes of the nozzle ring go into the inner cover ring and the outer cover ring perpendicular without transition radii. In the case of such nozzle rings, it can be seen that cracks develop in the region of the inner ring and the outer ring, which impair the service life of the nozzle ring. In order to increase the service life of nozzle rings, it is desirable to form defined transition radii in the transition region of the guide vanes to the inner cover ring and to the outer cover ring.
    For the production of nozzle rings casting technology methods are used, in which a core is used as part of a mold. Typically, cores designed as ring cores are used, ie one-piece cores. By using such toroidal cores, a nozzle ring can be made relatively inexpensively, but no transition radii can be formed in the transition region of the guide vanes to the cover rings of the nozzle ring.
    In order to provide nozzle rings with transition radii in the transition region between the guide vanes and the cover rings of the nozzle ring, it is necessary to change from the toroidal technology to the segmented core technology, that is, as part of a casting mold for the casting process of the nozzle ring a segmented, multi-part core to use. However, such segment cores are expensive to manufacture, which can increase the cost of producing nozzle rings to more than double. The use of segment rings is therefore not preferred.
    There is a need to use a toroidal core in the casting production of a nozzle ring, with the present invention, in particular a method for producing a toroidal core for the casting production of a nozzle ring is proposed, the formation of transition radii in the transition region between the vanes and the cover rings of the nozzle ring allowed.
    Proceeding from this, the present invention seeks to provide a novel method for producing a toroidal core for the casting technology of a nozzle ring of an axial turbine.
    This object is achieved by a method for producing a toroidal core for the casting production of a nozzle ring of an axial turbine according to claim 1.
    According to the invention are mounted on the elements corresponding to the guide vanes of the nozzle ring to be manufactured before pouring the assembly with the ceramic material pieces that define a defined transition radius between the vanes and at least one cover ring, preferably two cover rings, the nozzle ring to be produced.
    With the inventive method, a toroidal core for the casting manufacturing of a nozzle ring of an axial turbine can be provided, which allows the formation of transition radii between the guide vanes of the nozzle ring and the cover rings thereof. This makes it possible for the first time, inexpensive to manufacture nozzle rings with transition radii in the transition region between the vanes and the cover rings using a toroidal core. Segment cores can be omitted.
    According to a further development, the top pieces of a flexible material, such that the top pieces nestle when casting the assembly with the ceramic material to the support elements. Such attachments are particularly preferred. When the arrangement with the ceramic material is encapsulated, the sections of the respective attachment which face the carrier elements of the arrangement and the elements of the nozzle ring to be produced are conformed to the same. Hereby transition radii can be made highly accurate.
    The inventive method for producing a nozzle ring by casting using such a ring core produced in the above manner is defined in claim 9.
    Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
    1 is a perspective view of a used for producing the ring shape attachment piece.
    Fig. 2 is a perspective view of an element used to make the ring mold, which corresponds to a guide vane of the nozzle ring to be produced, together with two attachment pieces mounted thereon.
    The invention relates to a method for producing a toroidal core for the casting production of a nozzle ring of an axial turbine.
    The basic procedure during the casting production of a nozzle ring of an axial turbine using a toroidal core is familiar to the person skilled in the art. At this point, for the sake of completeness, it should be pointed out that initially a toroidal core is produced, which is subsequently used as part of a casting mold for the casting-technical production of the nozzle ring.
    To produce such a toroidal core for the casting production of a nozzle ring, which has an inner cover ring, an outer cover ring and extending between the inner cover ring and the outer cover ring vanes, the procedure is that on an outer support member which corresponds to the outer capping of a nozzle ring to be produced , and an inner support element, which corresponds to the inner cover ring of the nozzle ring to be produced, elements are mounted, which correspond to the guide vanes of the nozzle ring to be produced. For this purpose, the support elements have a plurality of slot-like recesses, in which the elements corresponding to the guide vanes are inserted in the direction of their longitudinal extent.
    Such an arrangement of the support elements and the elements mounted on the support elements is then encapsulated with a ceramic, liquid material.
    Of the encapsulated arrangement, the support elements and the elements mounted on the support elements, which correspond to the guide vanes of the nozzle ring to be manufactured, removed after partial hardening of the ceramic material, wherein a remaining case of the partially dried ceramic material is hardened to provide the toroidal core, in particular by burning out in an oven.
    In order to assemble and dismantle the guide vanes of the nozzle ring to be produced corresponding elements on the cover rings of the nozzle ring to be produced corresponding support elements, so far according to the prior art no transition radii are formed in the transition region between the vanes and the cover rings of a nozzle ring to be produced.
    With the present invention, it is now proposed that are mounted on the elements of the assembly for the production of the toroidal core, which correspond to the vanes of the nozzle ring to be produced, before molding the assembly with the ceramic workpiece attachment pieces, which have a transition radius between the guide vanes and Define the cover rings of the nozzle ring to be produced. After an element which corresponds to a guide vane of a nozzle ring to be produced has been threaded with one end into a recess of one of the support elements, two attachment pieces are subsequently threaded onto the respective element before it is subsequently inserted into a corresponding recess of the other support element.
    Then, if on each element, which corresponds to a guide vane of a nozzle ring to be produced, two attachment pieces are threaded, serves a first attachment piece providing a defined transition radius between the vane and the inner cover ring and a second attachment piece providing a defined transition radius between the Guide vane and the outer cap ring.
    Then, if on each element, which corresponds to a vane of a nozzle ring to be produced, only one essay pieces is threaded, it serves either to provide a defined transition radius between the guide vane and inner cover ring or the provision of a defined transition radius between the vane and the outer cap ring.
    The threading of two attachment pieces on the elements, which correspond to the guide vanes of a nozzle ring to be produced, is preferred in order to provide the defined transition radii between the guide vane two cover rings.
    After an element which corresponds to a guide vane of a nozzle ring to be produced has been mounted on two support elements, the attachment pieces are subsequently moved in the direction of the respective support element, namely a first attachment piece in the direction of the outer support member and a second attachment piece in the direction the inner support element. Contours of the attachment pieces, which are remote from the support elements, determine the transition radius between the guide vanes and the cover rings of the nozzle ring to be produced.
    Fig. 1 shows such an attachment piece 10 in isolation. The attachment piece 10 comprises a recess 11, via which it can be threaded onto an element which corresponds to a guide vane of a nozzle ring to be produced.
    Fig. 2 shows an element 12, which corresponds to a guide vane of a nozzle ring to be produced, in a perspective view together with two threaded on the element 12 Aufsatzstücken 10th
    权利要求:
    Claims (9)
    [1]
    Each attachment 10 has two circumferential contours 13,14, wherein in Fig. 1 and 2, the contour 13 of the respective attachment piece 10 defines the transition radius between the vanes and the respective cover ring of the nozzle ring to be produced, and wherein the opposite contour 14 at the production of the toroidal core come to rest on the respective support element. The top pieces 10 are made of a flexible material. The material of the attachment pieces 10 is so flexible that the attachment pieces 10 conform to the support elements when the arrangement of the support elements corresponding to the cover rings of the nozzle ring to be produced, the elements corresponding in the rotor blades of the nozzle ring to be produced, and the attachment pieces 10 , The top pieces 10 may consist of a rubber material or a rubber-like material, in particular of a silicone material or other elastic plastic. After the casting of the assembly of the support elements, from the blades of the nozzle ring corresponding elements 12 and from the attachment pieces 10 with the liquid ceramic material not only the support elements and mounted on the support elements, the blades of the nozzle ring to be produced corresponding Elements 12 of the partially dried and cured ceramic material forming a blank removes, but also the top pieces 10 of the flexible material. Subsequently, the blank is dried in particular in an oven by burning and hardened, to be subsequently used as part of a casting mold for the casting production of the nozzle ring. In this case, the ring core produced according to the invention is then surrounded with a metallic material from which the nozzle ring to be produced is made. The support elements which correspond to the cover rings of the nozzle ring, and the elements mounted on the support elements, which correspond to the guide vanes of the nozzle ring to be produced, are preferably made of a metallic material. The attachments are made of a flexible, non-metallic material. With the invention, a nozzle ring having the same transition radii between the vanes and the cover rings thereof, can be produced inexpensively and easily, namely using the toroidal technology. REFERENCE SIGNS LIST 10 attachment piece 11 recess 12 element 13 contour 14 outline patent claims
    1. A method for producing a toroidal core for the casting production of a nozzle ring of an axial turbine, wherein elements are mounted on an outer support element, which corresponds to an outer cover ring of a nozzle ring to be produced, and on an inner support element, which corresponds to an inner cover ring of a nozzle ring to be produced, the guide vanes correspond to the nozzle ring to be produced, the arrangement of the outer support member, the inner support member and the elements mounted on the support elements are encapsulated with a ceramic material, being removed from the encapsulated arrangement, the support members and the elements mounted on the support elements and then a remaining Blank is hardened from the ceramic material to provide the toroidal core, characterized in that on the elements corresponding to the guide vanes of the nozzle ring to be produced, before pouring the arrangement with the ker Amical material attachment pieces are mounted, which define a defined transition radius between the guide vanes and at least one cover ring, preferably two cover rings, the nozzle ring to be produced.
    [2]
    2. The method according to claim 1, characterized in that the attachment pieces consist of a flexible material.
    [3]
    3. The method according to claim 1 or 2, characterized in that the material of the attachment pieces is so flexible that the attachment pieces cling to the encasing the assembly with the ceramic material to the support elements.
    [4]
    4. The method according to any one of claims 1 to 3, characterized in that the attachment pieces consist of a rubber material or rubber-like material.
    [5]
    5. The method according to any one of claims 1 to 3, characterized in that the attachment pieces consist of a silicone material.
    [6]
    6. The method according to any one of claims 1 to 3, characterized in that the attachment pieces consist of a plastic.
    [7]
    7. The method according to any one of claims 1 to 6, characterized in that in addition to the support elements and the elements mounted on the support elements and the attachment pieces are removed before hardening of the blank of the cast-over arrangement.
    [8]
    8. The method according to any one of claims 1 to 6, characterized in that the support elements and the elements mounted on the support elements made of a metallic material.
    [9]
    9. A method for producing a nozzle ring of an axial turbine, producing a toroidal core according to one of claims 1 to 8, using the toroidal core as a casting mold or part of a casting mold when casting the nozzle ring of a metallic material.
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    同族专利:
    公开号 | 公开日
    CN108500213A|2018-09-07|
    JP2018140439A|2018-09-13|
    DE102017104014A1|2018-08-30|
    KR20180099483A|2018-09-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB785291A|1953-10-27|1957-10-23|Power Jets Res & Dev Ltd|An improved process for moulding or casting profiled articles|
    CN1037289A|1987-03-19|1989-11-22|高伟|Simple strengthening method for fast making silastic mould|
    US4878827A|1988-08-22|1989-11-07|Davidson Textron Inc.|Plastic shell for foam moldings|
    US20070201980A1|2005-10-11|2007-08-30|Honeywell International, Inc.|Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages|
    US20080006761A1|2006-06-22|2008-01-10|John Vitale|Round rubber champhering ring|
    CN102125996B|2010-12-30|2013-03-27|吉林大学|Method for forming bionic non-smooth surface of casting|
    US8714927B1|2011-07-12|2014-05-06|United Technologies Corporation|Microcircuit skin core cut back to reduce microcircuit trailing edge stresses|
    CN202963369U|2012-02-01|2013-06-05|大同北方天力增压技术有限公司|Split type wax mold die of integral nozzle ring|
    CN202683928U|2012-07-12|2013-01-23|陈国强|Quick molding wax mould of metal pipeline|
    CN203484603U|2013-09-24|2014-03-19|南京宁铁有色合金科技开发有限公司|Setting ring|
    KR101376674B1|2013-10-04|2014-03-21|권성애|Precision casting method of fauset connector|
    DE202014002981U1|2014-04-08|2014-04-16|Man Diesel & Turbo Se|Axial turbine for an exhaust gas turbocharger|
    法律状态:
    2021-01-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017104014.5A|DE102017104014A1|2017-02-27|2017-02-27|Method for producing a toroidal core for the casting production of a nozzle ring of an axial turbine|
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