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公开(公告)号：US09863273B2
公开(公告)日：2018-01-09
申请号：US14914349
申请日：2014-08-21
Applicant: SNECMA
Inventor： Francois Robert Bellabal , Francois Gallet , Mathieu Ange Poisson
CPC classification number: F01D25/16 , B64D27/16 , B64D27/26 , B64D2027/266 , F02C7/20 , F02K1/04 , F02K3/06 , F05D2220/323 , Y02T50/672
Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
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公开(公告)号：US09404420B2
公开(公告)日：2016-08-02
申请号：US14379840
申请日：2013-02-22
Applicant: SNECMA
Inventor： Francois Gallet , Boris Briantais , Jean-Pierre Serey , Alexandre Tan-Kim
CPC classification number: F02C7/06 , F01D25/18 , F02C7/36 , F05D2260/40311 , F16H57/0409 , F16H57/0421 , F16H57/0423 , F16H57/0427 , F16H57/0456 , F16H57/0479 , F16H57/0486 , Y02T50/671
Abstract: An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.
Abstract translation: 一个行星减速齿轮，包括可围绕旋转轴线旋转的行星齿轮，行星齿轮由行星齿轮驱动并且可围绕由行星架承载的行星齿轮的轴线旋转，行星齿轮在固定齿圈上滚动， 行星架相对于齿圈轴向地位于横向，由行星齿轮和齿圈形成的齿轮形成为在使用后轴向地排出其润滑油。 行星架包括径向延伸部，该径向延伸部定位成面向齿轮并且形成用于将油引导到其径向端部的机构，以通过离心从其中喷出。
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公开(公告)号：US20150275680A1
公开(公告)日：2015-10-01
申请号：US14431294
申请日：2013-09-26
Applicant: SNECMA
Inventor： Francois Gallet
IPC: F01D5/30
CPC classification number: F01D5/3007 , F01D5/26 , F01D5/3084 , Y02T50/672
Abstract: The invention relates to a turbine blade having an airfoil (31) extending above a platform (32) and a root (33) extending below said platform, the root of said blade having the form of a radially extending arm (34), being produced from composite material and having at least one cylindrical face (34), the direction of the generatrices of which is oriented in the direction of said platform so as to allow a clamping piece (5) to slide towards the latter on said cylindrical face under the action of centrifugal force, characterized in that said arm has, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1), and in that the root (33) is located entirely on the side of said protuberance with respect to said face.
Abstract translation: 本发明涉及一种具有在平台（32）上方延伸的翼型件（31）和在所述平台下方延伸的根部（33）的涡轮机叶片，所述叶片的根部具有径向延伸的臂（34）的形式， 从复合材料制成并具有至少一个圆柱面（34），其母线的方向在所述平台的方向上定向，从而允许夹紧件（5）在所述圆柱形表面 离心力的作用，其特征在于，所述臂在其下端具有形成径向支承点的突起（35），用于与用于将叶片保持在涡轮盘（1）上的元件接合，并且其中根 33）完全位于所述凸起相对于所述面的一侧。
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4.发明申请TURBINE ENGINE COMPRISING A CONTRAROTATING PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL CASING ATTACHED TO THE INTERMEDIATE HOUSING 有权包含连接在中间房的结构框架支撑的对比螺旋桨接收器的涡轮发动机公开(公告)号：US20130098066A1
公开(公告)日：2013-04-25
申请号：US13654796
申请日：2012-10-18
Applicant: SNECMA
Inventor： Francois Gallet , Audrey Grede
IPC: F02C7/20
CPC classification number: F02K3/072 , F02K3/062 , F05D2220/324 , F05D2220/325 , Y02T50/672
Abstract: The present invention relates to an open rotor type aircraft turbine engine (1), comprising a contrarotating propeller receiver (30) and a dual-body gas generator (14) comprising a low-pressure compressor (16) and a high-pressure compressor (18) separated by an intermediate housing (27), said gas generator being arranged upstream from said receiver.According to the invention, the turbine engine further comprises a structural casing (50) for supporting the receiver (30), surrounding the gas generator (14) and having a downstream end (50a) attached to said receiver and an upstream end (50b) attached to said intermediate housing (27). Furthermore, it comprises additional connection means (60) between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends (50b, 50a) of the casing.
Abstract translation: 本发明涉及一种开式转子式飞机涡轮发动机（1），包括对转螺旋桨式接收器（30）和双体气体发生器（14），该双体气体发生器包括低压压缩机（16）和高压压缩机 18），由中间壳体（27）分开，所述气体发生器布置在所述接收器的上游。 根据本发明，涡轮发动机还包括用于支撑接收器（30）的结构壳体（50），围绕气体发生器（14）并且具有附接到所述接收器的下游端（50a）和上游端（50b） 附接到所述中间壳体（27）。 此外，它包括设置在壳体的上游端和下游端（50b，50a）之间的在所述结构支撑壳体和气体发生器之间的附加连接装置（60）。
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公开(公告)号：US10227881B2
公开(公告)日：2019-03-12
申请号：US14431294
申请日：2013-09-26
Applicant: SNECMA
Inventor： Francois Gallet
Abstract: A turbine blade including an airfoil (31) extending above a platform (32) and a root (33) extending below the platform, the root of the blade having the form of a radially extending arm (34), being produced from composite material and including at least one cylindrical face (34). The direction of the generatrices which are oriented in the direction of the platform to allow a clamping piece (5) to slide towards the latter on the cylindrical face under the action of centrifugal force. The arm includes, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1). The root (33) is located entirely on the side of the protuberance with respect to the face.
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Patent Agency Ranking
公开(公告)号：US20160200443A1
公开(公告)日：2016-07-14
申请号：US14914349
申请日：2014-08-21
Applicant: SNECMA
Inventor： Francois Robert Bellabal , Francois Gallet , Mathieu Ange Poisson
CPC classification number: F01D25/16 , B64D27/16 , B64D27/26 , B64D2027/266 , F02C7/20 , F02K1/04 , F02K3/06 , F05D2220/323 , Y02T50/672
Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
Abstract translation: 本发明涉及一种旁通涡轮喷气发动机，其包括具有中心轮毂（13）和连接装置（11）的排气壳体，该连接装置可将由涡轮喷气发生的力传递到其所推进的飞行器的结构，所述连接装置是两个臂 径向地从中心轮毂排出以便穿过所述涡轮喷气发动机的冷流，并且其特征在于它们固定到所述中心轮毂并相对于彼此以直径相对的方式定位。 另外的连接装置（14）在轮毂（13）和区域（9）之间延伸，用于将排气罩固定到飞行器的结构（12），以便传递异常尺寸的载荷，所述连接装置在 正常使用，在所述轮毂和所述区域之间没有任何的力传递。
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公开(公告)号：US20150239569A1
公开(公告)日：2015-08-27
申请号：US14427189
申请日：2013-09-12
Applicant: SNECMA
Inventor： Francois Gallet , Patrick Joyez
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, including 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 configured to allow movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.
Abstract translation: 一种用于将发动机安装在飞行器的结构上或飞机的机翼上的塔架连接系统，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附接机构 。 连接机构连接第一和第二附接机构，连接机构构造成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。
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8.发明授权Reduction gear with epicyclic gear train having roller-bearing-mounted planet spindles 有权具有行星齿轮系的减速齿轮具有滚子轴承安装的行星主轴公开(公告)号：US08986146B2
公开(公告)日：2015-03-24
申请号：US13904483
申请日：2013-05-29
Applicant: SNECMA
Inventor： Francois Gallet
CPC classification number: F02C7/36 , F02C3/107 , F02K3/06 , F05D2260/4031 , F16H3/44 , F16H57/082 , F16H2057/085 , Y02T50/671
Abstract: A reduction gear with epicyclic gear train including an annulus gear, and at least one planet gear rolling on the annulus gear and able to rotate about a planet spindle borne by a planet carrier is provided. The planet spindle is mounted such that it can itself rotate about its axis relative to the planet carrier. The reduction gear is suitable for mounting in a high bypass ratio jet engine for driving the fan thereof.
Abstract translation: 一种具有行星齿轮系的减速齿轮，包括环形齿轮，以及至少一个在环形齿轮上滚动并能够围绕由行星架承载的行星轴线旋转的行星齿轮。 行星主轴安装成使得其本身可绕其轴线相对于行星架转动。 减速装置适用于安装在用于驱动其风扇的高旁通比喷气发动机中。
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公开(公告)号：US08876647B2
公开(公告)日：2014-11-04
申请号：US13773811
申请日：2013-02-22
Applicant: SNECMA
Inventor： Francois Gallet , Boris Briantais , Jean-Pierre Serey , Alexandre Tan-Kim
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。
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10.发明授权公开(公告)号：US09738392B2
公开(公告)日：2017-08-22
申请号：US14762281
申请日：2014-01-15
Applicant: SNECMA
Inventor： Antoine Hellegouarch , Mathieu Ange Poisson , Francois Gallet
CPC classification number: B64D27/26 , B64D27/10 , B64D27/12 , B64D27/14 , F02C7/20 , F02C7/36 , F05D2260/4031
Abstract: A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.
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