-
公开(公告)号：WO2015142395A2
公开(公告)日：2015-09-24
申请号：PCT/US2014/070278
申请日：2014-12-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ALARCON, Andrew, G. , TATTON, Royce, E. , FORD, Barry, M. , LI, Linda, S. , TURNER, Matthew, A.
CPC classification number: F01D25/005 , B29C70/12 , B29D99/0025 , B29K2105/12 , F01D11/008 , F02K3/06 , F04D29/325 , F05D2220/36 , F05D2240/30 , F05D2240/80 , F05D2300/123 , F05D2300/2102 , F05D2300/224 , F05D2300/434 , F05D2300/436 , F05D2300/603 , Y02T50/672
Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.
Abstract translation: 本公开一般涉及用于燃气涡轮发动机的风扇叶片平台的领域。 更具体地，本公开涉及用于燃气涡轮发动机的压缩短切纤维风扇叶片平台。
-
公开(公告)号：WO2014143268A1
公开(公告)日：2014-09-18
申请号：PCT/US2013/075442
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ALARCON, Andrew, G. , QUINN, Christopher, M. , GLASPEY, James , TURNER, Matthew, A.
CPC classification number: F01D5/02 , F01D5/025 , F01D5/30 , F01D5/3053 , F01D11/008 , F05D2220/10 , F05D2220/36 , F05D2230/60 , F05D2240/80 , F05D2260/30 , Y02T50/671 , Y10T29/49334
Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.
Abstract translation: 提供了用于燃气涡轮发动机的风扇部分中的平台的防旋转突出部。 防旋转翼片与旋转器的后缘接合，从而防止平台旋转和扭转。
-
3.发明申请
公开(公告)号：WO2014052797A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/062253
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SALAMON, Keith, T. , TURNER, Matthew, A. , TIRONE, John, P.
CPC classification number: F02C7/20 , F01D9/02 , F02K3/06 , F05D2260/941
Abstract: A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that extends axially into the respective mounting bracket. Each of the wall brackets includes a tongue and a base. The tongue extends axially from the base into the groove of a respective one of the mounting brackets. The base is connected to the wall.
Abstract translation: 壁组件包括沿着中心线轴向延伸并沿周向至少部分围绕中心线延伸的壁。 壁组件还包括围绕中心线周向布置的多个安装支架和多个壁支架。 每个安装支架包括一个轴向延伸到相应的安装支架上的槽。 每个墙壁支架都包括舌头和底座。 舌部从基部轴向延伸到相应的一个安装支架的凹槽中。 基座连接到墙壁。
-
公开(公告)号：WO2014051799A2
公开(公告)日：2014-04-03
申请号：PCT/US2013/048172
申请日：2013-06-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： TURNER, Matthew, A. , BROWN, Charles, W. , BUGAJ, Shari, L. , QUINN, Christopher, M. , HYLAND, Dave, J. , ALARCON, Andrew, G.
CPC classification number: F01D11/008 , F01D5/3007 , F05D2220/36 , Y02T50/672
Abstract: A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.
Abstract translation: 整流罩组件包括外壁，第一侧壁，第二侧壁和鞍座。 第一侧壁和第二侧壁从外壁的相对侧面延伸。 第一侧壁，第二侧壁和外壁一起在整流罩组件内形成空腔。 鞍座位于空腔内并且在第一侧壁和第二侧壁之间延伸。 鞍座具有适于连接到第一侧壁的第一肋条和适于连接到第二侧壁的第二肋条。 第一肋和第二肋在中心毂连接在一起。
-
公开(公告)号：WO2014051673A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/029052
申请日：2013-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： TURNER, Matthew, A. , SALAMON, Keith, T. , FORD, Barry, M.
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F01D17/105 , F02C7/18 , F02K3/075 , F05D2240/12 , F05D2250/52 , F05D2260/606 , Y10T137/0536
Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.
Abstract translation: 所公开的燃气涡轮发动机包括：风扇，包括可围绕发动机轴线旋转的多个风扇叶片和设置在用于驱动风扇的核心机舱内的核心发动机。 在核心机舱和外部或风扇机舱之间限定旁路通道。 安装在核心机舱内的管道限定了用于将排气从核心发动机引导到旁路通道中的排气流动路径。 排气管道包括以限定的弦角设置的多个翼型件，用于将排气流引导到旁路通道中以最小化对旁路气流的破坏。
-
Patent Agency Ranking
公开(公告)号：WO2015130382A3
公开(公告)日：2015-09-03
申请号：PCT/US2014/069774
申请日：2014-12-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： TURNER, Matthew, A. , ALARCON, Andrew, G. , BUGAJ, Shari, L.
Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.
Abstract translation: 公开了一种用于燃气涡轮发动机的风扇组件。 风扇组件可以包括转子，从转子径向延伸的多个翼型件以及围绕转子并包括限定多个翼型件之间的流动路径的表面的平台。 该平台可以构造成在燃气涡轮发动机的使用寿命期间是一次性的。
-
公开(公告)号：WO2015017095A2
公开(公告)日：2015-02-05
申请号：PCT/US2014/045985
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROACH, James, T. , KLING, Colin, J. , COOK, Grant, O., III , MCPHAIL, James, J. , BUGAJ, Shari, L. , O'BRIEN, James, F. , DEHLAVI, Majidullah , SMITH, Scott, A. , RADER, Matthew, R. , TURNER, Matthew, A. , XU, JinQuan
CPC classification number: B64D29/00 , B29D22/00 , F01D5/02 , F01D25/28 , F02K3/04 , F05D2220/32 , F05D2230/30 , F05D2230/90 , F05D2300/10 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
Abstract translation: 公开了用于制造轻质电镀聚合物燃气涡轮发动机部件的电镀聚合物燃气涡轮发动机部件和方法。 这些部件包括镀有一个或多个金属层的聚合物基材。 聚合物基材的聚合材料可以用可以包括碳，金属或玻璃的材料在结构上加强。 聚合物基底还可以包括多个层以形成复合铺层结构。
-
公开(公告)号：WO2015006433A3
公开(公告)日：2015-01-15
申请号：PCT/US2014/045928
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROACH, James, T. , BARNETT, Barry , COOK III, Grant, O. , WATSON, Charles, R. , BUGAJ, Shari, L. , LEVASSEUR, Glenn , TWELVES, Wendell, V., Jr. , HERTEL, Christopher, J. , KLING, Colin, J. , TURNER, Matthew, A. , XU, JinQuan , CLARKSON, Steven , CAULFIELD, Michael
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
-
公开(公告)号：WO2014028056A1
公开(公告)日：2014-02-20
申请号：PCT/US2013/032189
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： TURNER, Matthew, A. , ALARCON, Andrew, G. , GLASPEY, James , GREEN, Brian , FORD, Barry, M. , JUREK, Renee, J.
CPC classification number: F01D5/30 , F01D5/02 , F01D5/143 , F01D5/145 , F01D11/008 , F05D2220/32 , F05D2240/55 , Y02T50/673
Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.
Abstract translation: 用于燃气涡轮发动机的转子组件的间隔件组件包括具有非轴对称流路表面的端壁段，第一凹陷和第二凹陷。 流路表面的周边包括前边缘，后边缘，吸力侧边缘和压力侧边缘。 第一凹部沿着与吸入侧边缘相邻的流路面形成，第二凹部沿着与压力侧边缘相邻的流路面形成。
-
公开(公告)号：EP2900959A1
公开(公告)日：2015-08-05
申请号：EP13842614.3
申请日：2013-03-05
Applicant: United Technologies Corporation
Inventor： TURNER, Matthew, A. , SALAMON, Keith, T. , FORD, Barry, M.
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F01D17/105 , F02C7/18 , F02K3/075 , F05D2240/12 , F05D2250/52 , F05D2260/606 , Y10T137/0536
Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.
-
-
-
-
-
-
-
-
-
Search Results
16
records
(took 0.022 seconds)
