公开(公告)号：US09695703B2

公开(公告)日：2017-07-04

申请号：US14404975

申请日：2013-06-24

Applicant: SNECMA

Inventor： Francois Gallet

IPC: F04D29/34 ,  F01D9/04 ,  F01D7/00 ,  F04D29/32 ,  F01D17/12

CPC classification number: F01D9/041 ,  F01D7/00 ,  F01D17/12 ,  F04D29/323 ,  F05D2220/36 ,  F05D2260/74 ,  F05D2260/79 ,  Y02T50/671 ,  Y02T50/673

Abstract: A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile.

公开(公告)号：US09567090B2

公开(公告)日：2017-02-14

申请号：US14427189

申请日：2013-09-12

Applicant: SNECMA

Inventor： Francois Gallet ,  Patrick Joyez

IPC: B64D27/26 ,  B64D27/12 ,  B64C11/48 ,  B64D27/00

CPC classification number: B64D27/26 ,  B64C11/48 ,  B64D27/12 ,  B64D2027/005 ,  B64D2027/264 ,  Y02T50/66

Abstract: A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, is provided. The system includes a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism. The connection mechanism allows movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.

Abstract translation: 提供了一种用于将发动机安装在飞行器的结构或飞机的机翼上的塔架附接系统。 该系统包括可固定到塔架的第一连接机构和可固定到飞行器结构的第二连接机构。 连接机构连接第一和第二附接机构。 连接机构允许第一连接机构相对于第二连接机构在第一和第二位置之间移动。

公开(公告)号：US09482104B2

公开(公告)日：2016-11-01

申请号：US14059968

申请日：2013-10-22

Applicant: SNECMA

Inventor： Francois Gallet

IPC: F01D5/30 ,  F01D5/28 ,  B29D99/00

CPC classification number: F01D5/284 ,  B29D99/0028 ,  F01D5/3053 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A turbine blade for a turbojet engine, made of a ceramic matrix composite material and including a vane that extends above a platform and a root that extends below the platform is provided. The pressure face and the suction face of the vane is formed by sheets of a composite material, the sheets meeting at the leading edge and trailing edge of the vane. The pressure face and suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge.

Abstract translation: 提供了一种用于涡轮喷气发动机的涡轮叶片，其由陶瓷基体复合材料制成并且包括在平台上方延伸的叶片和在平台下方延伸的根部。 叶片的压力面和吸力面由复合材料片形成，片材在叶片的前缘和后缘处相交。 压力面和吸力面由在前缘或后缘沿着径向自身弯曲的同一片形成。

公开(公告)号：US09217391B2

公开(公告)日：2015-12-22

申请号：US13654796

申请日：2012-10-18

Applicant: SNECMA

Inventor： Francois Gallet ,  Audrey Grede

IPC: F02K3/062 ,  F02K3/072

CPC classification number: F02K3/072 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/325 ,  Y02T50/672

Abstract: An open rotor type aircraft turbine engine including a contrarotating propeller receiver and a dual-body gas generator having a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, in which the gas generator is arranged upstream from the receiver is provided. The turbine engine includes a structural casing for supporting the receiver, surrounding the gas generator and having a downstream end attached to the receiver and an upstream end attached to the intermediate housing; and a connection device between the structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing.

Abstract translation: 提供一种开式转子式飞机涡轮发动机，其包括对转螺旋桨接收器和具有低压压缩机和由其中气体发生器布置在接收器上游的中间壳体分隔的高压压缩机的双体气体发生器 。 涡轮发动机包括用于支撑接收器的结构壳体，围绕气体发生器并且具有附接到接收器的下游端和附接到中间壳体的上游端; 以及布置在壳体的上游和下游端之间的结构支撑壳体和气体发生器之间的连接装置。

公开(公告)号：US20150167482A1

公开(公告)日：2015-06-18

申请号：US14404975

申请日：2013-06-24

Applicant: SNECMA

Inventor： Francois Gallet

IPC: F01D9/04 ,  F01D17/12

CPC classification number: F01D9/041 ,  F01D7/00 ,  F01D17/12 ,  F04D29/323 ,  F05D2220/36 ,  F05D2260/74 ,  F05D2260/79 ,  Y02T50/671 ,  Y02T50/673

Abstract: A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile.

Abstract translation: 一种用于涡轮机的压缩机转子，包括轴和安装在轴上的至少两个盘，用于保持围绕轴的旋转轴线可旋转移动的单组叶片，至少一个第一盘以可移动的方式安装在 轴能够相对于第二盘产生角度间隙并且触发叶片绕其径向轴的旋转，两个盘中的至少一个被成形为容纳至少一个用于附接叶片的机构， 盘和附接机构之间的连接使得连接机构能够围绕径向轴线旋转，并且连接是切向和轴向移动的球接头连接。

公开(公告)号：US20130277454A1

公开(公告)日：2013-10-24

申请号：US13856038

申请日：2013-04-03

Applicant: AIRCELLE ,  Snecma

Inventor： Herve Hurlin ,  Nicolas Dezeustre ,  Wouter Balk ,  Francois Gallet

IPC: F02K1/56

CPC classification number: F02K1/566 ,  F01D5/005 ,  F02K1/605 ,  F02K1/625 ,  F02K1/72 ,  F02K1/766 ,  F05D2230/80 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

Abstract: The disclosure relates to an aircraft propulsion assembly including a nacelle having an intermediate housing and a front frame that is to be mounted downstream of an outer envelope of the intermediate housing. The front frame includes a deviation edge and an element forming a direct or indirect support for at least one flow deviation vanes, in particular, the deviation edge and the support-forming element are built into the outer envelope of the intermediate housing.

Abstract translation: 本发明涉及一种飞机推进组件，其包括具有中间壳体和将被安装在中间壳体的外壳的下游的前框架的机舱。 前框架包括偏离边缘和形成用于至少一个流动偏离叶片的直接或间接支撑的元件，特别地，偏转边缘和支撑形成元件被内置在中间壳体的外包层中。

公开(公告)号：US20130225353A1

公开(公告)日：2013-08-29

申请号：US13773811

申请日：2013-02-22

Applicant: SNECMA

Inventor： Francois Gallet ,  Boris Briantais ,  Jean-Pierre Serey ,  Alexandre Tan-Kim

IPC: F16H57/04

CPC classification number: F16H57/042 ,  F01D25/18 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/0423 ,  F16H57/0456 ,  F16H57/0479 ,  F16H57/0486 ,  Y02T50/671

Abstract: A reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field.

Abstract translation: 减速齿轮包括太阳小齿轮和由太阳小齿轮驱动并在固定齿圈上滚动的行星小齿轮。 该装置包括一个油箱，一个供油管道和油路导管。 该装置还包括在固定供应管道的端部处的油喷射装置，其取向包括远离公共旋转轴线的径向部件，以及用于回收可围绕共同的旋转运动的油的圆柱形装置 旋转轴。 油喷射装置通过至少一个管道连接到用于通过至少一个行星小齿轮的齿与相邻小齿轮的配合而形成的齿轮的润滑装置。 该装置借助于离心场的作用将供给油的管道供给到待润滑的部件。