公开(公告)号：US20160339504A1

公开(公告)日：2016-11-24

申请号：US15114918

申请日：2015-02-02

Applicant: SNECMA

Inventor： Michel BRETON ,  Samuel SICOT

IPC: B21H1/06

Abstract: Mandrels for rolling a ring include recesses for receiving the ring, which have rounded parts at the connection between the various faces, so as to avoid the formation of sharp angles on the rolled ring and the accidental formation of cracks.

Abstract translation: 用于滚动环的心轴包括用于接收环的凹部，其在各个面之间的连接处具有圆形部分，以避免在滚动环上形成锐角并且意外形成裂纹。

公开(公告)号：US09494051B2

公开(公告)日：2016-11-15

申请号：US14405565

申请日：2013-05-30

Applicant: SNECMA

Inventor： Nicolas Fillaud

IPC: F01D25/24 ,  F01D25/28

CPC classification number: F01D25/243 ,  F01D25/28 ,  F16B2200/506

Abstract: A counter plate for a turbo machine, including: a first external surface and a second external surface, which are substantially parallel; the first external surface of the counter plate creates a continuous ring or continuous ring segment and includes a first series of holes through which fasteners can pass; the second external surface of the counter plate including a plurality of surfaces for supporting heads of the fasteners, the support surfaces including a second series of holes, positioned facing the first series of holes, so that the fasteners can pass through the holes in the counter plate.

Abstract translation: 一种用于涡轮机的计数器板，包括：基本平行的第一外表面和第二外表面; 计数器板的第一外表面形成连续的环形或连续的环形部分，并且包括紧固件可以通过的第一系列孔; 台板的第二外表面包括用于支撑紧固件的头部的多个表面，支撑表面包括面对第一系列孔定位的第二系列孔，使得紧固件可以穿过计数器中的孔 盘子。

公开(公告)号：US09487310B2

公开(公告)日：2016-11-08

申请号：US14405947

申请日：2013-06-03

Applicant: SNECMA

Inventor： Nicolas Soulier ,  Maxime Vicentini ,  Jean-Marie Conrardy

IPC: B64G1/26 ,  B64G1/40 ,  F02K9/76 ,  B64G1/24

CPC classification number: B64G1/242 ,  B64G1/26 ,  B64G1/40 ,  B64G1/401 ,  B64G1/402 ,  F02K9/766

Abstract: A spacecraft including at least one main propellant tank, a main engine fed with propellant by the main tank, and a de-orbiting device. The de-orbiting device includes a detonation engine fed with propellant by the main tank.

Abstract translation: 包括至少一个主推进剂罐，由主油箱供给推进剂的主发动机和离轨装置的航天器。 离轨装置包括由主油箱供给推进剂的爆震发动机。

公开(公告)号：US20160319772A1

公开(公告)日：2016-11-03

申请号：US15107700

申请日：2014-12-30

Applicant: SNECMA

Inventor： Gaëlle LE BOUAR

IPC: F02K9/58 ,  F02K9/48

CPC classification number: F02K9/58 ,  F02K9/48 ,  F02K9/563 ,  F05D2270/304 ,  F05D2270/3061

Abstract: The invention relates to the field of propulsion assemblies, and in particular to rocket engines of the “expander” type, wherein at least one propulsion chamber (40) is fed with at least a first propellant by a first pump (33) coupled to a first turbine (34) that is driven by partial expansion of said first propellant upstream from said propulsion chamber (40) after passing, downstream from the first pump (33), through a heat exchanger (23) heated by said propulsion chamber (40). A method of the invention for controlling such a propulsion assembly (10) comprises the steps of determining whether there exists a risk of instability for the propulsion assembly (10), and in response to determining that said risk of instability exists, using a branch connection (28) situated between the first turbine (34) and the propulsion chamber (40) to shed a portion of said first propellant.

Abstract translation: 本发明涉及推进组件领域，特别涉及“膨胀机”类型的火箭发动机，其中至少一个推进室（40）由第一泵（33）供给至少第一推进剂，第一泵（33） 第一涡轮机（34），其在所述推进室（40）的上游在所述第一泵（33）的下游经过由所述推进室（40）加热的热交换器（23）经过所述第一推进剂的部分膨胀之后被驱动， 。 用于控制这种推进组件（10）的本发明的方法包括以下步骤：确定是否存在用于推进组件（10）的不稳定性的风险，并且响应于确定存在所述不稳定性的风险，使用分支连接 （28）位于所述第一涡轮（34）和所述推进室（40）之间以使所述第一推进剂的一部分脱落。

公开(公告)号：US20160319676A1

公开(公告)日：2016-11-03

申请号：US15105406

申请日：2014-12-12

Applicant: SNECMA

Inventor： Sami BENICHOU ,  Christian BARIAUD ,  Stéphanie DEFLANDRE ,  Sébastien DIGARD BROU DE CUISSART ,  Patrick Emilien Paul Emile HUCHIN

IPC: F01D5/22 ,  F01D9/04 ,  F01D5/30

Abstract: A blade for a turbomachine bladed wheel having N blades.At one end, the blade presents a platform that is formed integrally with an airfoil of the blade.Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil.Each of these segments forms an angle of 90°-180° /N relative to the radial direction on either side of the airfoil.

Abstract translation: 这些段中的每一个相对于翼型两侧的径向方向形成90°-180°/ N的角度。

公开(公告)号：US20160313728A1

公开(公告)日：2016-10-27

申请号：US15102455

申请日：2014-12-03

Applicant: SNECMA

Inventor： Alexandre ANFRIANI ,  Julien Alexis Louis RICORDEAU

IPC: G05B23/02 ,  G06Q10/00

CPC classification number: G05B23/0283 ,  G06Q10/20

Abstract: There is provided a method of and system for forecasting maintenance operations to be applied to an aircraft engine including a plurality of components monitored by damage counters, each damage counter being limited by a corresponding damage ceiling, the method including simulating consumption of the damage counters by iteratively drawing a series of simulation missions from a learning database; for each iteration, determining an accumulated consumption of each of the damage counters, until at least one damage counter related to a current simulation mission reaches a predetermined value limited by the damage ceiling associated with the damage counter; and applying a maintenance strategy on the current simulation mission to determine maintenance indicators representative of maintenance operations to be planned on the aircraft engine.

Abstract translation: 提供了一种用于预测应用于飞机发动机的维护操作的方法和系统，包括由损坏计数器监视的多个部件，每个损伤计数器受相应的损伤上限限制，该方法包括模拟损坏计数器的消耗 从学习数据库中迭代绘制一系列模拟任务; 确定每个损伤计数器的累积消耗，直到与当前模拟任务相关的至少一个损伤计数器达到由与损伤计数器相关联的损伤上限限制的预定值; 并对当前的模拟任务应用维护策略，以确定代表在飞机发动机上计划的维护操作的维护指标。

公开(公告)号：US20160312744A1

公开(公告)日：2016-10-27

申请号：US15029920

申请日：2014-10-10

Applicant: SNECMA

Inventor： Robert GAZAVE

IPC: F02K9/64

CPC classification number: F02K9/64 ,  F05D2230/60 ,  F05D2250/72 ,  F05D2300/603

Abstract: A rocket propulsion chamber and a method of fabricating such a propulsion chamber are provided. The propulsion chamber includes a combustion chamber, a wall of the combustion chamber having a cooling circuit wherein a first propellant flows. A thermostructural composite material shell is placed against the outside of the combustion chamber and including a diverging nozzle extending beyond the bottom end of the combustion chamber, wherein a fraction of the thermostructural composite material shell is covered in a radially strong outer reinforcing shell for containing deformation of the combustion chamber and thermostructural composite material shell, the thermostructural composite material shell and the outer reinforcing shell forming a unitary assembly.

Abstract translation: 提供火箭推进室和制造这种推进室的方法。 推进室包括燃烧室，燃烧室的壁具有第一推进剂流动的冷却回路。 将热结构复合材料壳放置在燃烧室的外部，并且包括延伸超过燃烧室底端的发散喷嘴，其中一部分热结构复合材料壳体被覆盖在径向强的外部增强壳体中，用于容纳变形 的燃烧室和热结构复合材料外壳，热结构复合材料外壳和外加强外壳形成一体式组件。

公开(公告)号：US20160305283A1

公开(公告)日：2016-10-20

申请号：US15099880

申请日：2016-04-15

Applicant: SNECMA

Inventor： Serge Rene MORREALE ,  Dominik IGEL

IPC: F01D25/18 ,  F01D25/16 ,  F16J15/00 ,  F16J15/3252 ,  F16J15/447 ,  F16J15/3268

CPC classification number: F01D25/183 ,  F01D11/02 ,  F01D25/16 ,  F02C7/28 ,  F05D2220/30 ,  F05D2240/55 ,  F05D2260/98 ,  F16J15/002 ,  F16J15/162 ,  F16J15/324 ,  F16J15/3252 ,  F16J15/3268 ,  F16J15/442 ,  F16J15/447

Abstract: A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing (8) rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.

Abstract translation: 一种用于涡轮发动机的密封装置，其具有包括转子轴的油封壳; 固定到发动机壳体上的环形盖，围绕转子轴布置以与其配合，以限定油封，该油封可容纳相对于发动机壳体可旋转地支撑转子轴的轴承; 安装在转子轴上的迷宫式密封件，其面向盖的一端; 安装在所述盖内的环形边缘; 动态环形垫片径向插入在轮​​辋和转子轴之间; 以及夹子，其用于轴向地阻挡所述盖内的轮辋并且包括至少一个通过所述轮辋径向穿过并且径向地容纳在形成在所述盖中的凹槽内的闩锁。

公开(公告)号：US20160290156A1

公开(公告)日：2016-10-06

申请号：US15037549

申请日：2014-11-24

Applicant: SNECMA

Inventor： Jean-Luc LE STRAT ,  Herve POHIER

IPC: F01D25/04 ,  F01D9/02 ,  F02C7/04

Abstract: A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.

Abstract translation: 平衡的涡轮机部件包括一个角扇形部，其布置成形成以环轴为中心的平衡环。 角扇区包括多个紧固件，与平衡环具有互补形状的支承面，轴承面上的角部分。 所述部件还包括多个平衡块，每个平衡块均固定到所述角部分的相应的紧固件上，所述平衡块中的至少一个还用作紧固件，用于将所述角形区域紧固在所述支承面上。

公开(公告)号：US20160290145A1

公开(公告)日：2016-10-06

申请号：US15087195

申请日：2016-03-31

Applicant: HERAKLES ,  SNECMA

Inventor： Clément ROUSSILLE ,  Gael EVAIN ,  Aline PLANCKEEL ,  Claire GROLEAU

IPC: F01D9/04

CPC classification number: F01D9/04 ,  F01D11/08 ,  F01D25/246 ,  F05D2240/11 ,  F05D2300/6033

Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of CMC material and forming a turbine ring, each ring sector including an annular base with respective end portions having edges that are held facing an edge of the end portion of the annular base of a sector that is adjacent in the turbine ring. The assembly includes resilient holder devices for holding the ring sectors in position on the ring support structure, and each resilient holder device includes a spring element present beside the outside face of the ring support structure.

Abstract translation: 涡轮环组件包括环支撑结构和由CMC材料制成并形成涡轮环的多个环形部分，每个环形部分包括环形基部，其中相应的端部具有保持面向边缘的边缘 在涡轮机环中相邻的扇区的环形基座。 组件包括用于将环形部分保持在环形支撑结构上的适当位置的弹性保持器装置，并且每个弹性保持器装置包括存在于环形支撑结构的外表面旁边的弹簧元件。