公开(公告)号：WO2014092925A1

公开(公告)日：2014-06-19

申请号：PCT/US2013/070096

申请日：2013-11-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： ALARCON, Andrew G. ,  TATTON, Royce E.

IPC: F01D5/20 ,  F01D11/08 ,  F02C7/28

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F05D2220/36 ,  F05D2250/75 ,  F05D2300/437 ,  Y02T50/673

Abstract: A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

Abstract translation: 用于燃气涡轮发动机的风扇部分包括具有具有外表面的翼型的风扇叶片。 平台密封件粘附在翼型件上。 用于燃气涡轮发动机的风扇部分包括具有槽的风扇毂。 风扇叶片包括从根部延伸到尖端的翼型件。 根被收到在插槽中。 平台被固定到风扇轮毂并且布置在相邻的风扇叶片之间。 密封件具有固定到风扇叶片的相对侧的基部和与基部一体并且从基部延伸并且朝向根部倾斜并与平台接合以提供密封的内部流动路径的翼片。

公开(公告)号：EP3170983B1

公开(公告)日：2020-05-06

申请号：EP16200324.8

申请日：2016-11-23

Applicant: United Technologies Corporation

Inventor： TATTON, Royce E.

IPC: F01D11/00 ,  F01D5/30

公开(公告)号：EP3102791A2

公开(公告)日：2016-12-14

申请号：EP14886052.1

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.

IPC: F01D5/02 ,  F02K3/06

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.

公开(公告)号：EP3170983A1

公开(公告)日：2017-05-24

申请号：EP16200324.8

申请日：2016-11-23

Applicant: United Technologies Corporation

Inventor： TATTON, Royce E.

IPC: F01D5/30

Abstract: A platform (410) for an airfoil in a gas turbine engine is provided. The platform includes a top wall (411) configured to connect to an airfoil of the gas turbine engine, a connector (422) configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall (434) extending from the top wall to the connector, the sidewall having a first arm (434a) and a second arm (434b), wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

Abstract translation: 提供了用于燃气涡轮发动机中的翼型件的平台（410）。 该平台包括构造成连接到燃气涡轮发动机的翼型件的顶壁（411），构造成接收销并将平台固定到燃气涡轮发动机的转子的连接器（422），以及侧壁（434） 从所述顶壁延伸到所述连接器，所述侧壁具有第一臂（434a）和第二臂（434b），其中所述第一臂和所述第二臂弯曲成在弯曲的侧壁处从所述顶壁延伸到所述连接器。

公开(公告)号：EP3078813A1

公开(公告)日：2016-10-12

申请号：EP16164429.9

申请日：2016-04-08

Applicant: United Technologies Corporation

Inventor： TATTON, Royce E.

IPC: F01D11/00 ,  F02K3/06

CPC classification number: F01D11/008 ,  F01D5/3023 ,  F02K3/06 ,  F05D2220/36 ,  F05D2300/431 ,  F05D2300/437

Abstract: A fan section (100) for a gas turbine engine (20) is provided. The fan section includes a fan hub including a slot and a fan blade (210) including an airfoil (211) extending from a root (143) to a tip. The airfoil has an airfoil leading edge (212) and the root is received in the slot. A first platform (134) is secured to the fan hub and arranged between adjacent fan blades. A first platform seal (300A) including a platform seal leading edge (309) and a base (306) is secured to a side of the first platform. A first winglet (304A) extends from the platform seal leading edge and contacts the airfoil leading edge. A corresponding gas turbine engine is also provided.

Abstract translation: 提供一种用于燃气涡轮发动机（20）的风扇部分（100）。 风扇部分包括一个包括槽的风扇轮毂和一个包括从根部（143）延伸到顶端的翼型件（211）的风扇叶片（210）。 机翼具有翼型前缘（212），并且根部被容纳在槽中。 第一平台（134）被固定到风扇轮毂并且布置在相邻的风扇叶片之间。 包括平台密封前缘（309）和基座（306）的第一平台密封件（300A）固定到第一平台的一侧。 第一小翼（304A）从平台密封件前缘延伸并接触翼型件前缘。 还提供了相应的燃气涡轮发动机。

公开(公告)号：EP2932047A1

公开(公告)日：2015-10-21

申请号：EP13862661.9

申请日：2013-11-14

Applicant: United Technologies Corporation

Inventor： ALARCON, Andrew G. ,  TATTON, Royce E.

IPC: F01D5/20 ,  F01D11/08 ,  F02C7/28

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F05D2220/36 ,  F05D2250/75 ,  F05D2300/437 ,  Y02T50/673

Abstract: A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

Abstract translation: 用于燃气涡轮发动机的风扇部分包括具有带外表面的翼型的风扇叶片。 平台密封粘附在翼型上。 用于燃气涡轮发动机的风扇部分包括具有槽的风扇轮毂。 风扇叶片包括从根部延伸到尖端的翼型。 根在槽中被接收。 平台固定在风扇轮毂上并布置在相邻的风扇叶片之间。 密封件具有固定到风扇叶片的相对侧的基部以及与基部一体并从基部延伸并且朝向根部倾斜并接合平台以提供密封的内部流动路径的翼片。

公开(公告)号：EP3121386B1

公开(公告)日：2019-10-09

申请号：EP16180615.3

申请日：2016-07-21

Applicant: United Technologies Corporation

Inventor： TURNER, Matthew A. ,  TATTON, Royce E. ,  WOOD, Kristin ,  SATTERWHITE, Matthew

IPC: F01D11/00

公开(公告)号：EP3170984A1

公开(公告)日：2017-05-24

申请号：EP16200339.6

申请日：2016-11-23

Applicant: United Technologies Corporation

Inventor： TATTON, Royce E.

IPC: F01D5/30

CPC classification number: F01D5/326 ,  F01D5/02 ,  F01D5/12 ,  F01D5/3007 ,  F01D5/3053 ,  F01D11/008 ,  F04D29/322 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2300/6012

Abstract: A platform (410) for an airfoil in a gas turbine engine is provided. The platform includes a top wall (411) configured to connect to an airfoil of the gas turbine engine, two sidewalls (432) extending downward from the top wall, a connector (422) attached to and connecting the two sidewalls, wherein the top wall, the sidewalls, and the connector define an interior volume of the platform, and a single stiffener (436) extending from the connector to the top wall within the interior volume between the two sidewalls. The connector defines two parallel apertures (426a; 426b) passing through the connector.

Abstract translation: 提供了用于燃气涡轮发动机中的翼型件的平台（410）。 该平台包括构造成连接到燃气涡轮发动机的翼型的顶壁（411），从顶壁向下延伸的两个侧壁（432），连接到并连接两个侧壁的连接器（422），其中顶壁 ，侧壁和连接件限定了平台的内部容积，并且单个加强件（436）从连接件延伸到两个侧壁之间的内部容积内的顶壁。 连接器限定穿过连接器的两个平行孔（426a; 426b）。

公开(公告)号：EP3121386A1

公开(公告)日：2017-01-25

申请号：EP16180615.3

申请日：2016-07-21

Applicant: United Technologies Corporation

Inventor： TURNER, Matthew A. ,  TATTON, Royce E. ,  WOOD, Kristin ,  SATTERWHITE, Matthew

IPC: F01D11/00

CPC classification number: F01D5/225 ,  B29C70/682 ,  B29C70/70 ,  B29C70/84 ,  B29C70/865 ,  B29K2309/08 ,  B29K2619/00 ,  B29K2627/12 ,  B29K2707/04 ,  B29L2031/082 ,  F01D5/02 ,  F01D11/008 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2300/431 ,  F05D2300/432 ,  F05D2300/603 ,  Y02T50/672

Abstract: A fan blade platform (150) is provided. The fan blade platform (150) may include a flowpath (106), a first sidewall (110; 152) extending from the flowpath (106) to a circular member (164), and a second sidewall (112; 154) extending from the flowpath (106) to the circular member (164). A stiffening member (158) may also extend from the circular member (164) to the flowpath (106) and be formed integrally with the first sidewall (110; 152), the second sidewall (112; 154), and the flowpath (106).

Abstract translation: 提供了一种风扇叶片平台（150）。 风扇叶片平台（150）可以包括流动路径（106），从流动路径（106）延伸到圆形构件（164）的第一侧壁（110; 152）以及从第二侧壁 流动路径（106）到圆形构件（164）。 加强构件（158）也可以从圆形构件（164）延伸到流动路径（106）并且与第一侧壁（110; 152），第二侧壁（112; 154）和流动路径（106）整体形成 ）。