公开(公告)号：US20160201791A1

公开(公告)日：2016-07-14

申请号：US14907791

申请日：2014-08-06

Applicant: SNECMA

Inventor： Augustin Curlier ,  Tewfik BOUDEBIZA ,  Gilles Alain Charier

IPC: F16H57/04 ,  F16H57/08 ,  F02C7/36 ,  F16H1/28

CPC classification number: F16H57/0486 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0427 ,  F16H57/043 ,  F16H57/0471 ,  F16H57/0482 ,  F16H57/082

Abstract: The epicyclic reduction gear comprises a planetary input shaft, planet gears meshing around said shaft and supported by a planet carrier, and two transverse sides. According to the invention, the reduction gear comprises at least one fluid transfer pipe suitable for being connected to a fluid supply source and passing through the planet carrier, being linked in rotation to same, from a first of said transverse sides of the reduction gear to a second of said transverse sides of the latter in order to open on the outside of the reduction gear and dispense the fluid.

Abstract translation: 行星减速齿轮包括行星输入轴，围绕所述轴啮合并由行星架支撑的行星齿轮和两个横向侧面。 根据本发明，减速齿轮包括至少一个流体输送管，该流体输送管适于连接到流体供应源，并且通过行星架从第一减速齿轮的横向侧转动到与行星架相同的旋转方向， 后者的所述横向侧面中的第二个，以便在减速齿轮的外部打开并分配流体。

公开(公告)号：US20150361830A1

公开(公告)日：2015-12-17

申请号：US14763385

申请日：2014-01-21

Applicant: SNECMA

Inventor： Tewfik BOUDEBIZA ,  Michel Henri ZIEGLER ,  Guillaume MARCILLAUD

IPC: F01D25/28 ,  H02G3/32 ,  B65D63/10 ,  F16B1/00 ,  H01B7/00 ,  B65D63/04

CPC classification number: F01D25/28 ,  B65D63/04 ,  B65D63/10 ,  F01D25/00 ,  F02C7/00 ,  F05D2220/30 ,  F05D2260/30 ,  F16B1/00 ,  F16B2001/0028 ,  H01B7/0045 ,  H02G3/32 ,  Y10T24/14 ,  Y10T24/1457

Abstract: The device for securing and retaining at least one electrical harness in a turbomachine includes: at least one hollow profiled element that extends in one direction and has at least two slots of approximately the same dimension and; and a clamping element intended to retain the at least one harness in position in a manner parallel to the hollow profiled element. The clamping element includes: a touch-and-close tape designed to cooperate with the width of the slots so as to allow it to pass on both sides of the profiled element and; an end stop secured to the tape, the end stop preventing the tape from passing through one of the slots in the profiled element.

Abstract translation: 用于固定和保持涡轮机中的至少一个电气线束的装置包括：至少一个中空型材元件，其在一个方向上延伸并且具有至少两个大致相同尺寸的槽; 以及用于将所述至少一个线束以平行于所述中空型材元件的方式保持就位的夹紧元件。 夹紧元件包括：设计成与狭槽的宽度配合的接触和关闭带，以允许其在异型元件的两侧通过; 固定在胶带上的端部止挡件，防止胶带穿过异形元件中的一个狭槽的端部止挡件。

公开(公告)号：US20160326964A1

公开(公告)日：2016-11-10

申请号：US15110001

申请日：2014-12-24

Applicant: SNECMA

Inventor： Augustin CURLIER ,  Julien AUSTRUY ,  Tewfik BOUDEBIZA ,  Gilles Alain CHARIER

IPC: F02C7/36 ,  F16H1/28 ,  F16D3/223 ,  F02K3/072

CPC classification number: F02C7/36 ,  F02K3/072 ,  F05D2260/40311 ,  F16D3/223 ,  F16H1/28 ,  Y02T50/671

Abstract: An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Abstract translation: 一种用于驱动涡轮发动机的第一叶片组的旋转的行星齿轮装置，该装置包括：以涡轮发动机的纵向轴线为中心并连接到发动机的转子的阳光，以便旋转驱动; 至少有一个行星与太阳轮啮合; 行星架可旋转地承载行星并连接到第一叶片组以驱动其旋转; 和与地球啮合的环; 太阳轮通过第一等速球传动接头连接到转子。

公开(公告)号：US20160290236A1

公开(公告)日：2016-10-06

申请号：US15088525

申请日：2016-04-01

Applicant: SNECMA

Inventor： Tewfik BOUDEBIZA ,  Gilles Alain CHARIER ,  Augustin Marc Michel CURLIER ,  Jean-Christophe DUFFET

IPC: F02C7/18 ,  F01D25/24 ,  F02K3/072 ,  F02C3/10 ,  F02C3/067

CPC classification number: F02C7/18 ,  F01D9/065 ,  F01D25/24 ,  F02C3/067 ,  F02C3/10 ,  F02K3/072 ,  F05D2220/32 ,  F05D2220/324 ,  F05D2260/20 ,  F05D2260/40311 ,  Y02T50/675

Abstract: The invention relates to a non-faired propeller turbo-engine comprising a gas generator (12) and a propulsion unit (14) which is separated from the gas generator (12) by an intermediate housing (40), the turbo-engine (10) including a housing (100) and a radially internal ferrule (44) which are coaxial, which are connected by hollow radial arms (50), said housing (100) also defining in part a gas flow duct (48) of a secondary gas flow, 1wherein each radial arm (50) is hollow and is traversed by at least one service (54) of the turbo-engine, characterised in that at least one arm (50) is traversed by a ventilation gas circulation duct (56) from the secondary gas flow and which leads to at least one component from among in particular a power turbine and a mechanical transmission of said propulsion unit.

公开(公告)号：US20150217854A1

公开(公告)日：2015-08-06

申请号：US14612661

申请日：2015-02-03

Applicant: SNECMA

Inventor： Jean-Christophe DUFFET ,  Tewfik BOUDEBIZA ,  Augustin CURLIER

IPC: B64C11/30

CPC classification number: B64C11/306 ,  B64C11/308 ,  B64D2027/005 ,  F02C3/067 ,  F02C6/206 ,  Y02T50/66 ,  Y02T50/672

Abstract: The turbine engine includes respective systems for changing the pitch of the propeller blades, the system (22) for the upstream propeller including a linear actuator (23) and a transmission mechanism (24) connecting the actuator to the blades in order to transform the sliding of the actuator into a rotation of the blades, said upstream propeller (2) including a rotatable housing (19) rigidly connected to a rotatable shaft (17) supported in a static housing (27) of the turbine engine by a bearing (29) upstream of the system, and by a bearing (30) downstream of the system. Advantageously:the rotatable housing (19) of the upstream propeller includes a support (36) rigidly connected to said rotatable housing and surrounding the static housing (27),the actuator (23) is annular and fixed to the support (36) of the rotatable housing, outside the support, and the transfer mechanism comprises connecting rods (33) and rotatable radial arms (34) traversing the gaseous flow path in order to control the pitch of the blades, andthe downstream bearing (30) is provided between the static housing (27) and the support (36), inside said support (36).

Abstract translation: 涡轮发动机包括用于改变螺旋桨叶片间距的相应系统，用于上游螺旋桨的系统（22）包括线性致动器（23）和将致动器连接到叶片的传动机构（24），以便将滑动 所述上游螺旋桨（2）包括通过轴承（29）刚性地连接到支撑在所述涡轮发动机的静态壳体（27）中的可旋转轴（17）的可旋转壳体（19） 在系统的上游，以及系统下游的轴承（30）。 有利地：上游螺旋桨的可旋转壳体（19）包括刚性地连接到所述可旋转壳体并围绕静态壳体（27）的支撑件（36），致动器（23）是环形的并且固定到支撑件（36） 可旋转壳体，支撑件外部，并且传送机构包括连接杆（33）和横穿气体流动路径的可旋转的径向臂（34），以便控制叶片的间距，并且下游轴承（30）设置在 静止壳体（27）和支撑件（36）。