公开(公告)号：US20150308280A1

公开(公告)日：2015-10-29

申请号：US14474463

申请日：2014-09-02

Applicant: Snecma

Inventor： Jean-Christophe DUFFET ,  Benoit Guillaume Farvacque

IPC: F01D11/08 ,  F16J15/00 ,  F16J15/32 ,  F01D5/02

CPC classification number: F01D11/08 ,  F01D5/02 ,  F01D11/001 ,  F01D11/127 ,  F05D2220/30 ,  F05D2240/56 ,  F16J15/002 ,  F16J15/3204 ,  F16J15/3288 ,  F16J15/4472

Abstract: The main object of the invention is an assembly forming a seal (1) for a turbomachine (10), used to provide a seal between two elements of the turbomachine (10) rotating relative to one another, and being rotationally symmetrical around an axis (X) of the assembly forming a seal (1), characterised in that it includes a brush seal (2), which is annular around the axis (X) of the assembly forming a seal (1), having multiple elastic sealing bristles (5, 5a, 5b) intended to be attached to one of the two elements of the turbomachine (10) rotating relative to one another, and at least one lip (3, 3a, 3b, 3c), which is annular around the axis (X) of the assembly forming a seal (1), extending radially in the direction of the brush seal (2), intended to be attached to the other of the two elements of the turbomachine (10) rotating relative to one another, where the said at least one lip (3, 3a, 3b, 3c) penetrates at least partially into the brush seal (2).

Abstract translation: 本发明的主要目的是形成用于涡轮机（10）的密封件（1）的组件，用于在相对于彼此旋转的涡轮机（10）的两个元件之间提供密封，并围绕轴线旋转对称 （1）的组件，其特征在于，其包括刷密封件（2），所述刷密封件围绕形成密封件（1）的组件的轴线（X）环绕，具有多个弹性密封刷毛（5） ，5a，5b），其被安装在相对于彼此旋转的所述涡轮机（10）的两个元件中的一个上，以及至少一个围绕所述轴线的环（3,3a，3b，3c） ）形成密封件（1），其沿刷子密封件（2）的方向径向延伸，用于附接到相对于彼此旋转的涡轮机（10）的两个元件中的另一个，其中所述 至少一个唇缘（3,3a，3b，3c）至少部分地穿透到刷子密封件（2）中。

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）。