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公开(公告)号：US20150345298A1
公开(公告)日：2015-12-03
申请号：US14655058
申请日：2013-05-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dominic J. MONGILLO , Tracy A. PROPHETER-HINCKLEY
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
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公开(公告)号：US20160130950A1
公开(公告)日：2016-05-12
申请号：US14896730
申请日：2014-06-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San QUACH , Tracy A. PROPHETER-HINCKLEY , Matthew A. DEVORE
CPC classification number: F01D5/186 , B22C9/103 , F01D5/187 , F01D9/041 , F01D25/12 , F02C3/04 , F04D29/324 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/125 , F05D2240/30 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil. A first cooling cavity merges into the plenum and a second cooling cavity merges into the plenum. A rib extends from at least one of the first sidewall and the second sidewall at least partially into the plenum to separate the first cooling cavity from the second cooling cavity.
Abstract translation: 根据本公开的示例性方面的部件包括除了别的以外的翼型件，其包括在前缘和后缘处连接在一起并且从基部延伸到尖端的第一侧壁和第二侧壁。 在翼型内定义了一个通风室。 第一个冷却腔并入集气室，第二个冷却腔并入集气室。 肋条从第一侧壁和第二侧壁中的至少一个至少部分地延伸到气室中，以将第一冷却腔与第二冷却腔分开。
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公开(公告)号：US20150330228A1
公开(公告)日：2015-11-19
申请号：US14704022
申请日：2015-05-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San QUACH , Tracy A. PROPHETER-HINCKLEY , Steven Bruce GAUTSCHI
CPC classification number: F01D5/187 , F01D5/147 , F01D5/186 , F01D5/20 , F05D2220/32 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.
Abstract translation: 根据本公开的示例性方面的部件包括除了别的以外的翼型件，其包括在前缘和后缘处在一起相遇的压力侧壁和抽吸侧壁。 翼型件延伸到尖端。 尖端口形成在尖端中并且在后缘之前终止。 传热增强装置形成在尖端口袋中。
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公开(公告)号：US20160290647A1
公开(公告)日：2016-10-06
申请号：US14673622
申请日：2015-03-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. PROPHETER-HINCKLEY , Dominic J. MONGILLO , Mark F. ZELESKY , Joel H. WAGNER , William A. SOWA
CPC classification number: F23R3/002 , F23R3/007 , F23R3/60 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045
Abstract: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.
Abstract translation: 本公开涉及用于燃气涡轮发动机的燃烧器构造，面板和部件。 在一个实施例中，用于燃气涡轮发动机的燃烧器包括支撑结构，该支撑结构包括多个开口和安装到该结构的多个面板。 多个面板限定了燃烧器的燃烧腔。 每个面板包括构造成接收冷却空气的第一壁和被构造成为空腔提供气流的第二壁。 第一和第二壁形成空腔并且包括用于控制每个面板的冷却效果的一个或多个元件。 另一个实施例涉及一种包括用于控制冷却效果的一个或多个元件的燃烧器面板。 另一实施例涉及燃气涡轮发动机的燃烧器的支撑结构。 另一个实施例涉及包括单壁部分或单壁面板的面板的构造。
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Patent Agency Ranking
5.发明申请GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开具有瓦斯工程尺寸结构的气体涡轮发动机部件公开(公告)号：US20150345396A1
公开(公告)日：2015-12-03
申请号：US14655059
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. ZELESKY , Joel H. WAGNER , Tracy A. PROPHETER-HINCKLEY , Michael F. BLAIR , Thomas N. SLAVENS , Dominic J. MONGILLO
CPC classification number: F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/12 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , F23R3/002 , F23R2900/03043 , Y10T29/49318
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
Abstract translation: 根据本公开的示例性方面的部件尤其包括形成在壁内部的壁和血管工程格子结构。 血管工程化晶格结构包括中空血管结构和固体血管结构中的至少一个，其被配置为使流体通过血管工程化晶格结构传播。
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公开(公告)号：US20160279697A1
公开(公告)日：2016-09-29
申请号：US15034612
申请日：2014-10-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dewight R. CASSELLS , Alan C. BARRON , John P. RIZZO , Gordon Miller REED , Tracy A. PROPHETER-HINCKLEY
IPC: B22C9/18 , B22C9/24 , F01D5/12 , G01N19/04 , F04D29/32 , F04D29/54 , G01B11/30 , B22C9/10 , F01D9/02
Abstract: A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.
Abstract translation: 根据本公开的示例性方面的耐火金属芯（RMC）精加工方法包括：在多个RMC样品上执行多个精加工操作，分析多个RMC样品的至少一部分的一个或多个特性 的RMC样品并且选择用于产生具有用于制造没有缺陷的部件的期望性质的RMC的精加工操作的组合。
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公开(公告)号：US20160017717A1
公开(公告)日：2016-01-21
申请号：US14837014
申请日：2015-08-27
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D9/041 , F05D2240/12 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的翼型件尤其包括设置在翼型体内部的翼型体和冷却回路，并且包括前缘腔，第一部分从径向内壁 到所述翼型件本体的径向外壁，以及从所述翼型件主体的前缘内壁延伸到后缘内壁的第二部分。 冷却回路构造成在冷却回路的第二腔体离开前缘空腔之前将冷却气流通过第一部分和第二部分。
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8.发明申请GAS TURBINE ENGINE COMPONENT HAVING TRANSVERSELY ANGLED IMPINGEMENT RIBS 审中-公开气动涡轮发动机组件具有横向旋转轴承RIBS公开(公告)号：US20160003053A1
公开(公告)日：2016-01-07
申请号：US14759271
申请日：2013-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. PROPHETER-HINCKLEY , San QUACH , Matthew A. DEVORE
CPC classification number: F01D5/186 , B22D30/00 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/21 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F23R3/002
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括主体部分，其包括与第二壁间隔开并围绕中心线轴线设置的第一壁。 至少一个肋在第一壁和第二壁之间延伸。 至少一个肋沿着相对于中心线轴线横向成角度的肋轴线延伸。 至少一个冲击孔延伸穿过至少一个肋。
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9.发明申请GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开具有瓦斯工程尺寸结构的气体涡轮发动机部件公开(公告)号：US20150345304A1
公开(公告)日：2015-12-03
申请号：US14654676
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dominic J. MONGILLO , Tracy A. PROPHETER-HINCKLEY , Mark F. ZELESKY , Joel H. WAGNER , Thomas N. SLAVENS
IPC: F01D5/18
CPC classification number: F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/12 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , F23R3/002 , F23R2900/03043 , Y10T29/49318
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.
Abstract translation: 根据本公开的示例性方面的部件尤其包括形成在壁内部的壁和血管工程格子结构。 血管工程格子结构限定了中空血管结构，其构造成使流体通过血管工程化晶格结构。 血管工程格子结构具有至少一个入口孔和至少一个出口孔，其将流体与中空血管结构连通。
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