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：US20150047369A1

公开(公告)日：2015-02-19

申请号：US14164827

申请日：2014-01-27

Applicant: SNECMA

Inventor： Nadege HUGON ,  Gilles Alain CHARIER

IPC: F02C6/20 ,  B64D27/10

CPC classification number: F01D9/065 ,  F01D25/16 ,  F01D25/18 ,  F01D25/28 ,  F02C3/067 ,  F02C7/32 ,  F02K3/072 ,  F05D2220/323 ,  F05D2230/64 ,  F05D2240/50 ,  F05D2240/61 ,  F05D2250/70 ,  F05D2260/30 ,  F05D2260/40 ,  F05D2260/96 ,  Y02T50/671 ,  Y10T29/49826

Abstract: The invention relates to a fixed turbine engine receiver part comprising a fixed hollow shaft for carrying ancillary systems of a turbine engine, centered on the turbine engine axis, turbine engine ancillary systems, an assembly for holding ancillary systems in position situated inside the fixed hollow shaft. The assembly for holding ancillary systems in position comprises at least one first ancillary system support ring, having an axis substantially parallel with the turbine engine axis, a first distance sleeve for holding the first ancillary system support ring in position, having an axis substantially parallel with the turbine engine axis, the first distance sleeve bearing against the first support ring, such that the first support ring comprises a plurality of mutually separated through holes, each through hole defining a passage for at least one ancillary system, each through hole being traversed by at least one of the ancillary systems of the turbine engine.

Abstract translation: 本发明涉及一种固定涡轮发动机接收器部件，其包括用于承载以涡轮发动机轴线为中心的涡轮发动机的辅助系统的固定空心轴，涡轮发动机辅助系统，用于将辅助系统保持在位于固定空心轴内部的位置 。 用于将辅助系统保持在适当位置的组件包括至少一个具有基本上与涡轮发动机轴线平行的轴线的第一辅助系统支撑环，用于将第一辅助系统支撑环保持在适当位置的第一距离套筒， 所述涡轮发动机轴线，所述第一距离套筒轴承抵靠所述第一支撑环，使得所述第一支撑环包括多个相互分离的通孔，每个通孔限定用于至少一个辅助系统的通道，每个通孔横穿所述通孔 涡轮发动机的辅助系统中的至少一个。