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1.发明申请GAS TURBINE ENGINE COMPONENT MANUFACTURING METHOD AND CORE FOR MAKING SAME 审中-公开气体涡轮发动机组件制造方法和制造方法的核心公开(公告)号：US20160001354A1
公开(公告)日：2016-01-07
申请号：US14767612
申请日：2014-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hector M. Pinero , Richard H. Page
CPC classification number: B22C9/24 , B22C9/04 , B22C9/10 , B22C9/108 , B22C9/12 , B22C21/14 , B22D21/025 , B22D25/02 , F01D5/18 , F01D5/187 , F01D9/041 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2300/177 , F05D2300/20 , Y02T50/676
Abstract: A method of manufacturing a gas turbine engine component includes providing a core having a brittle feature, supporting the feature with a first meltable material, arranging the core with the first meltable material in a first mold, and surrounding the core and the first meltable material with a second meltable material to provide a component shape. The method also includes coating the second meltable material with a refractory material to produce a second mold, removing the first and second meltable material, and casting a component in the second mold.
Abstract translation: 一种制造燃气涡轮发动机部件的方法包括提供具有脆性特征的芯部，用第一可熔融材料支撑该特征，将芯体与第一可熔材料一起设置在第一模具中，并且围绕芯部和第一可熔融材料， 第二可熔融材料，以提供部件形状。 该方法还包括用耐火材料涂覆第二可熔材料以产生第二模具，去除第一和第二可熔融材料，以及将组件浇铸在第二模具中。
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2.发明申请Process and Refractory Metal Core for Creating Varying Thickness Microcircuits for Turbine Engine Components 有权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
Applicant: United Technologies Corporation
Inventor： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
CPC classification number: 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
Abstract: 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.
Abstract translation: 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。
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3.发明授权Process and refractory metal core for creating varying thickness microcircuits for turbine engine components 有权用于为涡轮发动机部件创建不同厚度的微电路的工艺和难熔金属芯公开(公告)号：US09038700B2
公开(公告)日：2015-05-26
申请号：US13708036
申请日：2012-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
CPC classification number: 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
Abstract: 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.
Abstract translation: 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。
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