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公开(公告)号：WO2015142395A3
公开(公告)日：2015-11-19
申请号：PCT/US2014070278
申请日：2014-12-15
Applicant: UNITED TECHNOLOGIES CORP
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: 本公开总体上涉及用于燃气涡轮发动机的风扇叶片平台领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩的短切纤维风扇叶片平台。
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公开(公告)号：WO2015053848A3
公开(公告)日：2015-07-30
申请号：PCT/US2014049847
申请日：2014-08-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALARCON ANDREW G
CPC classification number: F01D11/008 , F01D5/02 , F01D5/3007 , F02K3/06 , F05D2220/32 , F05D2240/80 , Y02T50/672 , Y02T50/673
Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的平台具有外表面和内表面。 内表面设置有用于将平台安装到转子的安装位置。 平台从前缘延伸到后缘，并在吸力壁和压力壁之间延伸。 在吸入壁和压力壁之间限定圆周方向。 一个突出部从平台向周向外伸出一个吸力壁和压力壁。 当安装平台时，突片具有周向最外部的部分，该部分将邻接相邻平台的内表面。 还公开了风扇部分和燃气涡轮发动机。
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公开(公告)号：CA2917935A1
公开(公告)日：2015-01-15
申请号：CA2917935
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROACH JAMES T , BARNETT BERRY , COOK GRANT O III , WATSON CHARLES R , BUGAJ SHARI L , LEVASSEUR GLENN , WALL SARAH M , HERTEL CHRISTOPHER J , ZIMMITTI JONATHAN F , BETTAGERE LAKSHMINARAYAN , DEHLAVI MAJIDULLAH , WALTER BRIAN D , ALARCON ANDREW G , MARTIN OCTAVIO , ROBERTSON THOMAS J JR , BEAUDRY AARON , SCALIA JEFFREY J , OTT JOE , WASSEL JOSEPH J
IPC: F02C7/30 , C23C18/16 , C23C26/00 , C25D1/00 , C25D7/00 , F01D5/28 , F01D9/00 , F01D25/00 , F01D25/24
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.
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公开(公告)号：WO2015130382A2
公开(公告)日：2015-09-03
申请号：PCT/US2014069774
申请日：2014-12-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TURNER MATTHEW A , ALARCON ANDREW G , BUGAJ SHARI L
CPC classification number: F01D11/008 , B29C70/00 , F05D2220/36 , F05D2230/80 , F05D2240/80 , F05D2300/434 , F05D2300/436 , F05D2300/603 , Y02T50/672 , Y02T50/673
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和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。 该平台可构造成在燃气涡轮发动机的使用寿命期间是一次性的。
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公开(公告)号：WO2014051799A3
公开(公告)日：2014-06-26
申请号：PCT/US2013048172
申请日：2013-06-27
Applicant: UNITED TECHNOLOGIES CORP
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: 整流装置包括外壁，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延伸。 第一侧壁，第二侧壁和外壁一起在整流装置内形成空腔。 鞍座位于空腔内并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和适于连接到第二侧壁的第二肋。 第一肋和第二肋在中心轮毂处连接在一起。
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Patent Agency Ranking
公开(公告)号：SG11201407843UA
公开(公告)日：2015-03-30
申请号：SG11201407843U
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TURNER MATTHEW A , ALARCON ANDREW G , GLASPEY JAMES , GREEN BRIAN , FORD BARRY M , JUREK RENEE J
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.
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公开(公告)号：EP3080418A4
公开(公告)日：2017-08-09
申请号：EP14869623
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALARCON ANDREW G , BOGUE WILLIAM
CPC classification number: F04D29/083 , F01D11/001 , F01D11/008 , F04D19/002 , F04D29/322 , F04D29/329 , F04D29/34 , F04D29/38 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2240/80 , F05D2250/121 , F05D2260/98 , F05D2300/43
Abstract: An edge seal for preventing airflow through a space between a fan platform and an adjacent airfoil in a gas turbine engine may include a bonding segment being bondable to the fan platform. A sealing flap converges with the bonding segment so that the sealing flap is operatively contactable with the adjacent airfoil. A bumper rib protrudes from the bonding segment so that the bumper rib is bondable to the fan platform.
Abstract translation: 用于防止气流通过燃气涡轮发动机中的风扇平台和相邻翼型件之间的空间的边缘密封件可以包括可结合到风扇平台的结合区段。 密封襟翼与接合部分会聚，使得密封襟翼可操作地与相邻翼型接触。 保险杠肋从结合部分突出，使得保险杠肋可结合到风扇平台。
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公开(公告)号：EP3047109A4
公开(公告)日：2016-10-05
申请号：EP14852016
申请日：2014-08-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALARCON ANDREW G
CPC classification number: F01D11/008 , F01D5/02 , F01D5/3007 , F02K3/06 , F05D2220/32 , F05D2240/80 , Y02T50/672 , Y02T50/673
Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的平台具有外表面和内表面。 内表面设置有用于将平台安装到转子的安装位置。 平台从前缘延伸到后缘，并在吸力壁和压力壁之间延伸。 在吸力壁和压力壁之间限定圆周方向。 从平台向外周向向外延伸一个吸力壁和压力壁。 当安装平台时，突片具有周向最外部的部分，该部分将邻接相邻平台的内表面。 还公开了风扇部分和燃气涡轮发动机。
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公开(公告)号：EP2932047A4
公开(公告)日：2015-12-09
申请号：EP13862661
申请日：2013-11-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALARCON ANDREW G , TATTON ROYCE E
IPC: F01D11/08
CPC classification number: F01D11/008 , F01D5/3007 , F05D2220/36 , F05D2250/75 , F05D2300/437 , Y02T50/673
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公开(公告)号：EP2867503A4
公开(公告)日：2015-08-19
申请号：EP13841410
申请日：2013-06-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TURNER MATTHEW A , BROWN CHARLES W , BUGAJ SHARI L , QUINN CHRISTOPHER M , HYLAND DAVID J , ALARCON ANDREW G
CPC classification number: F01D11/008 , F01D5/3007 , F05D2220/36 , Y02T50/672
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