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61. 发明申请

US20130330201A1 CASTING METHOD FOR OBTAINING A PART INCLUDING A TAPERING PORTION 有权
标题翻译：用于获取包括切割部分的部件的铸造方法
公开(公告)号：US20130330201A1
公开(公告)日：2013-12-12
申请号：US13913759
申请日：2013-06-10
申请人： SNECMA
发明人： Sebastien DIGARD BROU DE CUISSART , Josserand Bassery , Stephanie Deflandre
IPC分类号： B22D25/02 , F01D5/14 , B22C9/04
CPC分类号： B22D25/02 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/24 , B22D19/0072 , B22D19/04 , F01D5/147 , F05D2230/21 , F05D2240/304
摘要： A casting method for obtaining a part that includes a tapering portion, and also a turbine engine blade obtained by casting and including a tapering trailing edge. According to the invention, the method comprises the following steps: providing an insert element having a tapering portion; making a shell around the insert element; and casting a molten material into said shell including the insert element.
摘要翻译：一种用于获得包括锥形部分的部件的铸造方法，以及通过铸造并包括锥形后缘而获得的涡轮发动机叶片。根据本发明，该方法包括以下步骤：提供具有锥形部分的插入元件; 在插入元件周围形成一个外壳; 并将熔融材料浇铸到包括插入元件的所述外壳中。

62. 发明申请

US20130323078A1 TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES 有权
标题翻译：涡轮叶片带微型冷却通道
公开(公告)号：US20130323078A1
公开(公告)日：2013-12-05
申请号：US13484767
申请日：2012-05-31
申请人： Jeffrey S. Beattie , Jeffrey Michael Jacques , Justin D. Piggush
发明人： Jeffrey S. Beattie , Jeffrey Michael Jacques , Justin D. Piggush
IPC分类号： F01D5/18 , B21D53/78
CPC分类号： F01D5/187 , B22C9/04 , B22C9/103 , F05D2230/211 , F05D2260/204 , Y02T50/676 , Y10T29/49316
摘要： A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
摘要翻译：一种制造翼型的方法包括以下步骤：制造第一芯，其包括限定完成的翼型件的第一多个通道的第一多个肋，并且制造为第二芯，该第二芯包括限定第二多个通路的第二多个肋完成机翼。第二多个肋包括多个支座。所述多个支座在所述第一多个肋与所述第二多个肋之间设置间隔，以限定所述第一多个通道与所述完整翼型的所述第二多个通道之间的间隔。然后将翼型件围绕芯组件成型。一旦完成，移除芯组件以提供具有期望的稳定性和结构完整性的并入多个微电路的完整翼型件。

63. 发明申请

US20130280091A1 GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING 有权
标题翻译：气体涡轮发动机空气流动冷却
公开(公告)号：US20130280091A1
公开(公告)日：2013-10-24
申请号：US13454197
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
IPC分类号： F01D5/18 , B05D1/36
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
摘要翻译：机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘以提供外部翼面表面。前缘壁在前缘提供外部翼型表面。冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。冲击孔横向穿过冲击壁间隔开。一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。

64. 发明申请

US20130276451A1 COMBUSTION SYSTEM INCLUDING A TRANSITION PIECE AND METHOD OF FORMING USING A CAST SUPERALLOY 有权
标题翻译：包括过渡段的燃烧系统和使用煤炭超级合金的成型方法
公开(公告)号：US20130276451A1
公开(公告)日：2013-10-24
申请号：US13454785
申请日：2012-04-24
申请人： Kevin Weston MCMAHAN , Arthur PECK , Nicholas VLESSIS
发明人： Kevin Weston MCMAHAN , Arthur PECK , Nicholas VLESSIS
IPC分类号： F23R3/02 , B23P15/00
CPC分类号： F01D9/023 , B22C9/04 , B22D19/0009 , B22D19/045 , B22D21/025 , B23P2700/13 , F05D2230/21 , F05D2230/211 , F05D2230/53 , F05D2300/175 , Y10T29/49988
摘要： A combustion system including a transition piece and method of forming the transition piece using a cast nickel-based superalloy is provided. The transition piece includes a body defining a flowpath and enclosure, the body having a circular inlet section for receiving combustion product from the combustor and an outlet end for flowing the combustor products into a first stage nozzle of a gas turbine. The transition piece comprises a one-piece single casting construction of the circular inlet section, the body, and the outlet end. The transition piece is formed from a nickel-based superalloy. The transition piece has a thick-to-thin ratio of wall thickness of thick transition to wall thickness of thin transition of about 1.1 to about 2.5.
摘要翻译：提供一种包括过渡件的燃烧系统和使用铸造镍基超级合金形成过渡件的方法。过渡件包括限定流路和外壳的主体，主体具有用于从燃烧器接收燃烧产物的圆形入口部分和用于使燃烧器产物流入燃气轮机的第一级喷嘴的出口端。过渡件包括圆形入口部分，主体和出口端的一体式单一铸造结构。过渡件由镍基超级合金形成。该过渡件具有厚到1mm的过渡到厚度过渡的壁厚的厚至约2.5的厚比。

65. 发明授权

US08500411B2 Turbine airfoil with outer wall thickness indicators 失效
标题翻译：涡轮机翼外墙厚度指示器
公开(公告)号：US08500411B2
公开(公告)日：2013-08-06
申请号：US12794972
申请日：2010-06-07
申请人： John J. Marra , Allister W. James , Gary B. Merrill
发明人： John J. Marra , Allister W. James , Gary B. Merrill
IPC分类号： B64C11/24 , B22C9/00
CPC分类号： B23P15/02 , B22C9/04 , B22C9/10 , F01D5/147 , F01D21/003 , Y10T29/49336
摘要： A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.
摘要翻译：一种可用于涡轮发动机并且包括用于确定外壁叶片厚度的深度指示器的涡轮机翼型。翼型件可以包括在外壁的外表面中具有多个凹槽的外壁。凹槽可以具有表示外壁的期望外表面和壁厚的深度。形成外壁的外表面的材料可以被去除以与每个凹槽中的最内点齐平，从而减小壁厚并提高效率。多个凹槽可以定位在靠近尖端的翼型件的径向外部区域中。

66. 发明申请

US20130174999A1 INVESTMENT CASTING 有权
标题翻译：投资铸造
公开(公告)号：US20130174999A1
公开(公告)日：2013-07-11
申请号：US13544486
申请日：2012-07-09
申请人： Richard Dudley Shaw
发明人： Richard Dudley Shaw
IPC分类号： B22C1/00
CPC分类号： B22C1/00 , B22C1/181 , B22C1/183 , B22C9/04
摘要： The invention provides novel binder, slurry and dry mix compositions for use in the production of investment casting moulds. These compositions comprise water insoluble fibers and significant amounts of uncalcined clay. The compositions display favourable separation characteristics and short drying times. The moulds formed using the compositions have a favourable green strength and conform closely to the wax pattern on which the mould is coated. Also provided are methods of producing the compositions, methods of investment casting mould production utilising the compositions and investment casting coating shells produced using the compositions of the invention.
摘要翻译：本发明提供用于生产熔模铸造模具的新型粘合剂，浆料和干混组合物。这些组合物包含水不溶性纤维和大量未煅烧粘土。该组合物显示出有利的分离特性和较短的干燥时间。使用该组合物形成的模具具有良好的生坯强度并且与涂覆有模具的蜡图案紧密地吻合。还提供了生产组合物的方法，使用组合物的熔模铸造模具生产方法和使用本发明的组合物生产的熔模铸造涂层壳。

67. 发明授权

US08449254B2 Branched airfoil core cooling arrangement 有权
标题翻译：分支翼型芯冷却装置
公开(公告)号：US08449254B2
公开(公告)日：2013-05-28
申请号：US12748501
申请日：2010-03-29
申请人： Matthew A. Devore , Eleanor D. Kaufman
发明人： Matthew A. Devore , Eleanor D. Kaufman
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , B22C9/04 , B22C9/10 , F05D2250/185 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2260/2214 , Y02T50/676
摘要： An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.
摘要翻译：示例性翼型件冷却装置包括具有第一面和与第一面相对的第二面的翼型件壁。翼型壁建立了一个通道，该通道被配置成在入口孔和出口孔之间连通流体。该通道包括从主要部分分支的次级部分。示例性翼型件冷却方法包括从翼型芯腔接收流体流并将流体流通过在翼型的壁内的通道。通道具有从主要部分分支的次级部分。

68. 发明申请

US20130092340A1 Process and Refractory Metal Core for Creating Varying Thickness Microcircuits for Turbine Engine Components 有权
$Process and Refractory Metal Core for Creating Varying Thickness Microcircuits for Turbine Engine Components$
标题翻译：用于为涡轮发动机部件创建不同厚度的微电路的工艺和耐火金属芯
公开(公告)号：US20130092340A1
公开(公告)日：2013-04-18
申请号：US13708036
申请日：2012-12-07
申请人： United Technologies Corporation
发明人： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
IPC分类号： B22C9/10 , B22D29/00
CPC分类号： B22C9/10 , B22C9/04 , B22C9/108 , B22D29/001 , F01D5/187 , F05D2230/00 , F05D2230/21 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/185 , F05D2300/13
摘要： The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.
摘要翻译：本公开涉及用于在涡轮发动机部件中形成变化的厚度微电路的难熔金属芯，用于形成耐火金属芯的方法以及用于形成涡轮发动机部件的工艺。耐火金属芯用于涡轮发动机部件的铸造。芯由具有与前缘部一体形成的弯曲后缘部的耐火金属材料片形成。

69. 发明申请

US20130068415A1 MOLD FOR CASTING A WORKPIECE THAT INCLUDES ONE OR MORE CASTING PINS 有权
标题翻译：用于铸造包括一个或多个铸造销钉的工具的模具
公开(公告)号：US20130068415A1
公开(公告)日：2013-03-21
申请号：US13234966
申请日：2011-09-16
申请人： Paul M. Lutjen , Christopher W. Strock
发明人： Paul M. Lutjen , Christopher W. Strock
IPC分类号： B22C9/00 , B22C9/10
CPC分类号： B22C9/04 , B22C9/108 , B22C9/24
摘要： A mold for casting a workpiece that includes a casting shell, a casting core and casting pin that supports the core within the shell. The casting shell includes an interior shell surface. The casting core is located within the shell, and includes a sidewall extending between a first core surface and a second core surface. The casting pin includes an intermediate segment connected between a first support segment and a second support segment. The intermediate segment contacts the sidewall. The first support segment extends from the first core surface to a first side of the interior shell surface. The second support segment extends from the second core surface to a second side of the interior shell surface that is opposite the first side.
摘要翻译：一种用于铸造工件的模具，其包括铸造壳体，铸造芯和铸造销，所述铸造支撑件在壳体内支撑芯部。铸造壳体包括内壳表面。铸造芯位于壳体内，并且包括在第一芯表面和第二芯表面之间延伸的侧壁。铸造销包括连接在第一支撑段和第二支撑段之间的中间段。中间部分接触侧壁。第一支撑段从第一芯表面延伸到内壳表面的第一侧。第二支撑段从第二芯表面延伸到内壳表面的与第一侧相对的第二侧。

70. 发明授权

US08393381B2 Method of forming a cast metal article 有权
标题翻译：铸造金属制品的成型方法
公开(公告)号：US08393381B2
公开(公告)日：2013-03-12
申请号：US13110362
申请日：2011-05-18
申请人： Lawrence D. Graham , James Barrett , Don Deptowicz
发明人： Lawrence D. Graham , James Barrett , Don Deptowicz
IPC分类号： B22D29/00
CPC分类号： B22D29/002 , B22C9/04 , B22C9/10 , B22D15/02 , B33Y80/00
摘要： A cast metal article is formed with an internal cavity. The internal cavity is formed by a ceramic core which is removed from the cast metal article to leave the cavity. The ceramic core is formed with a cavity to facilitate removal of the core from the cast metal article. To remove the core from the cast metal article, the cavity in the core is filled with a leaching liquid.
摘要翻译：铸造金属制品形成有内部空腔。内腔由陶瓷芯形成，陶瓷芯从铸造金属制品上移除以离开空腔。陶瓷芯形成有空腔以便于将铸件从铸造金属制品中取出。为了从铸造金属制品中除去芯体，芯体中的空腔填充有浸出液体。

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