Welding Additive Material, Welding Methods And Component
    2.
    发明申请
    Welding Additive Material, Welding Methods And Component 审中-公开
    焊接添加剂材料,焊接方法和部件

    公开(公告)号:US20090285715A1

    公开(公告)日:2009-11-19

    申请号:US12225088

    申请日:2007-02-16

    Abstract: The invention relates to a welding additive material, a use of a welding additive material, welding methods and a component which significantly improves the weldability of some nickel-based superalloys by means of a welding additive material and comprises the following constituents (in wt %): 18.0%-20.0% of chromium, 9.0%-11.0% of cobalt, 7.0%-10.0% of molybdenum, 2.0%-2.5% of titanium, 1.0%-1.7% of aluminum, 0.04%-0.08% of carbon, balance nickel.

    Abstract translation: 本发明涉及焊接添加剂材料,焊接添加剂材料的使用,焊接方法和组分,其通过焊接添加剂材料显着地改善了一些镍基超级合金的焊接性,并且包括以下成分(以重量%计) :铬的18.0〜20.0%,钴的9.0〜11.0%,钼的7.0〜10.0%,钛的2.0〜2.5%,铝的1.0〜1.70%,碳的0.04〜-08% 镍。

    Casting mold
    3.
    发明申请
    Casting mold 失效
    铸造模具

    公开(公告)号:US20060032604A1

    公开(公告)日:2006-02-16

    申请号:US10977736

    申请日:2004-10-28

    CPC classification number: B22C9/24 B22C9/00 B22C9/04 B22C9/10

    Abstract: According to the prior art, through-holes in components are often introduced after the production (casting) of the component. This entails additional outlay in terms of time and equipment. The time required can be considerably shortened if a casting mold is designed in such a way that the through-hole is at least in part formed by corresponding projections being formed on the inner wall and/or the outer wall of the casting mold.

    Abstract translation: 根据现有技术,在部件的生产(铸造)之后经常引入部件中的通孔。 这需要在时间和设备方面的额外费用。 如果铸模被设计成使得通孔至少部分地由形成在铸模的内壁和/或外壁上的相应突起形成的方式来缩短所需的时间。

    GAS TURBINE COMPONENT, METHOD FOR ITS PRODUCTION AND CASTING MOLD FOR USE OF THIS METHOD
    4.
    发明申请
    GAS TURBINE COMPONENT, METHOD FOR ITS PRODUCTION AND CASTING MOLD FOR USE OF THIS METHOD 审中-公开
    气体涡轮机组件,用于生产和铸造模具的方法,用于本方法

    公开(公告)号:US20140099209A1

    公开(公告)日:2014-04-10

    申请号:US14033589

    申请日:2013-09-23

    Abstract: A method is provided for casting a gas turbine component having at least a first section and a second section. As per the method, a liquid metal is cast into a casting mold and solidification of the metal is induced by means of controlled cooling. The cooling of the liquid metal in the first section is controlled in such a way that the metal solidifies in a directionally solidified crystal structure or a single-crystal structure. In the second section the cooling is carried out in such a way that it solidifies in a multidirectional crystal structure.

    Abstract translation: 提供一种用于铸造具有至少第一部分和第二部分的燃气涡轮机部件的方法。 按照该方法,将液态金属浇铸到铸模中,并通过受控制的冷却来诱导金属的凝固。 控制第一部分中的液态金属的冷却,使得金属以定向凝固的晶体结构或单晶结构固化。 在第二部分中,以使其以多向晶体结构固化的方式进行冷却。

    Method for producing a pattern for the precision-cast preparation of a component comprising at least one cavity
    5.
    发明授权
    Method for producing a pattern for the precision-cast preparation of a component comprising at least one cavity 失效
    用于制造用于精密铸造制备包含至少一个腔的部件的图案的方法

    公开(公告)号:US08074701B2

    公开(公告)日:2011-12-13

    申请号:US12517889

    申请日:2007-09-21

    Applicant: Uwe Paul

    Inventor: Uwe Paul

    CPC classification number: B22C7/026 B22C9/04 B22C9/10 B33Y80/00

    Abstract: A method for producing a pattern for the precision-cast representation of a component having a cavity is provided. In the method wherein the component is a turbine component having a cavity, the finished pattern comprises a core and an outer contour pattern, the outer contour pattern at least partially surrounds the core and at least partially defines the outer contour of the turbine component. The core is produced from a curable core material, which cures during the course of the method, and the outer contour pattern is produced from a material which can be burned or melted out. In this case, first the outer contour pattern is produced with a cavity corresponding to the cavity of the turbine component and subsequently the curable core material is filled into the cavity and cured to produce the core.

    Abstract translation: 提供了一种用于制造具有空腔的部件的精密铸造表面的图案的方法。 在其中所述部件是具有空腔的涡轮机部件的方法中,所述精加工图案包括芯部和外部轮廓图案,所述外部轮廓图案至少部分地围绕所述芯部并且至少部分地限定所述涡轮机部件的外部轮廓。 芯由可固化的芯材制成,其在该方法的过程中固化,并且外轮廓图案由可燃烧或熔化的材料制成。 在这种情况下,首先利用对应于涡轮机部件的空腔的空腔来制造外部轮廓图案,随后将可固化的芯材料填充到腔体中并固化以产生芯部。

    Heat treatment method for monocrystalline or directionally solidified structural components
    6.
    发明授权
    Heat treatment method for monocrystalline or directionally solidified structural components 失效
    单晶或定向凝固结构组分的热处理方法

    公开(公告)号:US07892370B2

    公开(公告)日:2011-02-22

    申请号:US11587897

    申请日:2005-04-28

    CPC classification number: C22F1/10 C21D9/00 C30B11/003 C30B29/52 C30B33/00

    Abstract: The invention relates to a heat treatment method for monocrystalline or directionally solidified structural components. Said method comprises a heat treatment which results in dissolving at least one crystalline phase of the material of the structural component, referred to in the following as component material. The inventive method is characterized by carrying out the heat treatment by heating the structural component to a dissolution temperature required for dissolving the crystalline phase only in at least one first component area in which the stresses within the component material do not exceed a predetermined value. In at least one second component area in which the stresses within the component material exceed the predetermined value the material is only heated to a temperature below the dissolution temperature.

    Abstract translation: 本发明涉及单晶或定向凝固结构组分的热处理方法。 所述方法包括热处理,其导致以下结构组分的材料的至少一个结晶相溶解作为组分材料。 本发明的方法的特征在于,通过将结构组分加热到仅将结晶相溶解在组分材料中的应力不超过预定值的至少一个第一组分区域中所需的溶解温度来进行热处理。 在其中部件材料内的应力超过预定值的至少一个第二部件区域中,材料仅被加热到低于溶解温度的温度。

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