公开(公告)号：US20170044986A1

公开(公告)日：2017-02-16

申请号：US15304212

申请日：2015-04-14

Applicant: SNECMA

Inventor： Philippe VERTENOEUIL ,  Bellal WAISSI

IPC: F02C7/236 ,  F04C11/00 ,  F04C15/00 ,  F04C2/18

CPC classification number: F02C7/236 ,  F01D25/186 ,  F04C2/18 ,  F04C11/001 ,  F04C11/005 ,  F04C15/0038 ,  F04C2210/1044 ,  F04C2240/30 ,  F04D1/00 ,  F04D13/12 ,  F04D29/0473 ,  F05D2220/323 ,  F05D2240/53 ,  Y02T50/671

Abstract: A geared fuel pump (4′) operates to supply a determined flow but at low or zero pressure rise. It is planned to add gland packing (46) between support bearings (19) of the pinions (11), or between some of them, to provide hydrodynamic lift for these bearings, by delimiting a closed cavity (47) to provide lift by a fluid with better viscosity properties instead of using the fluid itself that is pumped. Possible application to fuel pumps for aircraft engines, in which the pump (4′) is a high pressure pump associated with a low pressure pump.

Abstract translation: 齿轮燃料泵（4'）用于提供确定的流量，但是在低或零压力升高。 计划在小齿轮（11）的支撑轴承（19）之间或其中一些支撑轴承（19）之间增加压盖（46），以便为这些轴承提供流体动力提升，通过限定一个闭合腔（47），以提供一个 流体具有更好的粘度特性，而不是使用被泵送的流体本身。 可能应用于用于飞机发动机的燃料泵，其中泵（4'）是与低压泵相关联的高压泵。

公开(公告)号：US20170037733A1

公开(公告)日：2017-02-09

申请号：US15305605

申请日：2015-04-23

Applicant: SNECMA

Inventor： Charlotte Marie DUJOL ,  Patrice ENEAU ,  Sebastien DIGARD BROU DE CUISSART ,  Matthieu Jean-Luc VOLLEBREGT

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/323 ,  F05D2240/301 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

Abstract: The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.

Abstract translation: 由于在每个压力侧和吸入侧壁上的这种冷却的不均匀性，飞机涡轮机中的涡轮机的叶片的内部冷却受到限制。 为了解决这个问题，提出了一种叶片，其包括用于冷却其翼型部分的电路，其中串联连接的空腔的电路使得空气流沿压力侧的压力侧壁径向流向外部 并且通过翼型部的内壁与吸入侧腔分离的吸入侧空腔中的吸入侧壁径向向内侧径向移动。 以这种方式，科里奥利效应的力将空气流偏向压力侧和吸力侧壁，从而限制了不均匀性。

公开(公告)号：US20170028489A1

公开(公告)日：2017-02-02

申请号：US15303124

申请日：2015-04-08

Applicant: SNECMA

Inventor： Claude DEJAUNE ,  Cyril DOUADY

IPC: B23D77/00 ,  F16F15/023 ,  F16F15/02 ,  B23B41/02

CPC classification number: B23D77/003 ,  B23B27/002 ,  B23B29/022 ,  B23B41/02 ,  B23B49/02 ,  B23B2250/12 ,  B23B2250/16 ,  B23D77/006 ,  B23D2277/10 ,  B23D2277/60 ,  F16F15/022 ,  F16F15/023 ,  F16F15/0237 ,  F16F15/08

Abstract: An anti-vibration device for the machining of a shaft includes a first fixed ring intended to be kept inside a shaft by a shoulder, the anti-vibration device including: at least one first external groove and at least one first external seal for forming at least one contact with the internal surface of the shaft; at least one first internal circumferential groove and at least one first internal seal for forming at least one contact with the external surface of the bar; an internal circumferential cavity that is able to cause the circulation of a fluid arriving through a first duct and leaving through a second duct, the first duct and second duct passing through the radial thickness of the anti-vibration device, the internal circumferential cavity making it possible to realize a vibration-damping function when a fluid passes through it.

Abstract translation: 一种用于加工轴的防振装置包括：用于通过肩部保持在轴内的第一固定环，所述防振装置包括：至少一个第一外槽和至少一个第一外密封件，用于在 与轴的内表面的至少一个接触; 至少一个第一内部周向槽和至少一个第一内部密封件，用于与所述杆的外部表面形成至少一个接触; 能够引起通过第一管道到达的流体的循环并且通过第二管道离开的内部圆周腔，第一管道和第二管道穿过防振装置的径向厚度，使得内周空腔使其 可以在流体通过时实现减振功能。

公开(公告)号：US20170021654A1

公开(公告)日：2017-01-26

申请号：US15301191

申请日：2015-03-26

Applicant: SNECMA

Inventor： Pascal Fabrice BILHE ,  Geoffrey BEGUE-DUTHU

IPC: B41M5/24 ,  G03H1/04 ,  B23K26/0622

CPC classification number: B41M5/24 ,  B23K26/0622 ,  B23K26/066 ,  B23K26/361 ,  B41M5/26 ,  B41M5/262 ,  B41M5/267 ,  G03H1/04

Abstract: A method of marking the surface of a mechanical part with a predefined graphic having a holographic type effect, the method including using a laser source to apply a succession of laser pulses to the outside surface of a part for marking, with different masks being interposed between the laser source and the outside surface of the part, each mask having a particular pattern, each laser pulse having a power density of at least 20 MW/cm2 and a duration that is less than or equal to 100 ns.

Abstract translation: 一种利用具有全息型效果的预定图形来标记机械部件的表面的方法，该方法包括使用激光源将一系列激光脉冲施加到用于标记的部件的外表面，其中不同的掩模介于 激光源和部件的外表面，每个掩模具有特定的图案，每个激光脉冲具有至少20MW / cm 2的功率密度和小于或等于100ns的持续时间。

公开(公告)号：US09545762B2

公开(公告)日：2017-01-17

申请号：US13850169

申请日：2013-03-25

Applicant: SNECMA

Inventor： Francois Marie Paul Marlin ,  Philippe Verseux

IPC: B29C70/32 ,  B29C70/54 ,  B29C70/34 ,  F16L47/14 ,  B29C70/08 ,  B29K707/04 ,  B29K709/08 ,  B29L31/24 ,  B29C70/00

CPC classification number: B29C70/545 ,  B29C70/00 ,  B29C70/08 ,  B29C70/32 ,  B29C70/34 ,  B29C70/342 ,  B29C70/345 ,  B29C2793/009 ,  B29K2277/10 ,  B29K2707/04 ,  B29K2709/08 ,  B29L2031/24 ,  F16L47/14

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract translation: 公开了一种由包括由纤维结构增强的聚合物基体的复合材料制成的联接器。 联接器包括由主纤维结构增强的结构部分和由与主纤维结构不同的第一纤维结构增强的第一加工部分。 结构部分和第一加工部分的矩阵是相同的。 第一加工部分位于结构部分的主面的至少一部分上，并且在第一加工表面中加工。 第一加工面与主纤维结构的纤维之间没有交叉。

公开(公告)号：US20170009781A1

公开(公告)日：2017-01-12

申请号：US15105359

申请日：2014-12-18

Applicant: SNECMA

Inventor： Vianney Christophe Marie MANIERE ,  Matthieu Jean Luc VOLLEBREGT ,  Gaetan Jean Marie LOUPY ,  Paul Henri Joseph MAUCLAIR

IPC: F04D29/66 ,  F04D29/68 ,  F04D29/54 ,  F04D29/32

Abstract: The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2), between the pressure face of the first blade (3I) and the suction face of the second blade (3E) has a non-axisymmetric surface (S) defining a plurality of fins (4) of substantially triangular section extending downstream of a leading edge (BA) of each of the blades (3I, 3E), each fin (4) being associated with a leading position and a trailing position on the surface (S), between which positions the fin (4) extends, such that: the leading position is situated at between 5% and 35% length relative to a chord of the blade (3I, 3E) extending from a leading edge (BA) to a trailing edge (BF) of the blade (3I, 3E);—the further a fin (4) is from the suction face of the second blade (3E), the further the leading position of said fin (4) is axially from the leading edge (BA) of the blades (3I, 3E).

Abstract translation: 本发明涉及涡轮机组件（1）或包括至少第一和第二叶片（3I，3E）和平台（2）的组件的集合，叶片（3I，3E）从该平台延伸，其特征在于， 平台（2）在第一叶片（3I）的压力表面和第二叶片（3E）的吸力面之间具有非轴对称表面（S），该​​非轴对称表面限定了在下游延伸的大致三角形截面的多个翅片（4） 每个叶片（3I，3E）的前缘（BA）中的每个翅片（4）与表面（S）上的前导位置和后方位置相关联，翅片（4）延伸的位置， 使得：引导位置相对于从叶片（3I，3E）的前缘（BA）延伸到叶片（3I，3E）的后缘（BF）的叶片（3I，3E）的弦线位于5％和35％之间 ）; - 另外一个翅片（4）来自第二叶片（3E）的吸力面，所述翅片（4）的引导位置进一步从轴向 叶片（3I，3E）的前缘（BA）。

公开(公告)号：US20170002689A1

公开(公告)日：2017-01-05

申请号：US15100225

申请日：2014-12-02

Applicant: SNECMA

Inventor： Alexandre Leon ,  Gilles Brun

IPC: F01D25/32 ,  B64C1/14 ,  B64D29/00 ,  F02K3/06 ,  F01D25/24

CPC classification number: F01D25/32 ,  B64C1/1453 ,  B64D29/00 ,  F01D25/24 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/75 ,  F05D2260/602

Abstract: A device for retaining drained fluids for a propulsive assembly includes a cavity for storing the drained fluids and two walls mounted at the opening of said cavity. The cavity has a fluid storage volume V1 when the device is in a substantially vertical position, and each wall is configured such as to define a fluid storage volume (V2 and V3 respectively) in the cavity when the device is in a substantially horizontal position, each of the volumes V2 and V3 being at least equal to the volume V1.

Abstract translation: 用于保持用于推进组件的排出的流体的装置包括用于存储排出的流体的空腔和安装在所述腔的开口处的两个壁。 当装置处于基本上垂直的位置时，空腔具有流体存储容积V1，并且当装置处于基本上水平的位置时，每个壁被构造成限定空腔中的流体存储容积（V2和V3） 体积V2和V3中的每一个至少等于体积V1。

公开(公告)号：US20170001366A1

公开(公告)日：2017-01-05

申请号：US15101754

申请日：2014-11-28

Applicant: SNECMA

Inventor： Thierry GODON ,  Julien SCHNEIDER ,  Franck VARIN

IPC: B29C65/48 ,  F01D5/28 ,  F16B11/00 ,  B29C65/00

CPC classification number: B29C65/48 ,  B29C65/02 ,  B29C65/026 ,  B29C65/18 ,  B29C65/26 ,  B29C65/4815 ,  B29C65/4835 ,  B29C65/70 ,  B29C66/1122 ,  B29C66/301 ,  B29C66/532 ,  B29C66/721 ,  B29C66/742 ,  B29C66/81459 ,  B29C70/72 ,  B29C70/84 ,  B29L2031/08 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/23 ,  F05D2300/603 ,  F16B11/006 ,  Y10T156/1002 ,  Y10T156/103 ,  Y10T156/1031

Abstract: A method is provided of bonding together at least two parts. The method includes assembling together at least two parts and at least one adhesive layer, the adhesive being configured so that its adhesive power increases on heating as a result of it polymerizing, at least one of the parts being made of composite material or of metal, the adhesive layer being present, after assembly, between the parts, the assembled together parts and the adhesive being present in a chamber defined by a wall, the wall having an inside face situated facing a first part present between the adhesive layer and the wall, the first part being intended to be bonded to a second part and only a fraction of the second part being present inside the chamber; and applying a liquid against the wall on its side opposite from the chamber.

Abstract translation: 提供了将至少两个部分结合在一起的方法。 所述方法包括将至少两个部分和至少一个粘合剂层组装在一起，所述粘合剂构造成使得其粘合力由于其聚合而在加热时增加，所述部分中的至少一个由复合材料或金属制成， 粘合剂层在组装之后存在于部件之间，组装在一起的部件和粘合剂存在于由壁限定的室中，壁具有面向位于粘合剂层和壁之间的第一部分的内表面， 第一部分旨在结合到第二部分，并且仅第二部分的一部分存在于腔室内; 以及在与所述腔室相对的一侧在所述壁上施加液体。

公开(公告)号：US20160376016A1

公开(公告)日：2016-12-29

申请号：US15110670

申请日：2015-01-07

Applicant: SNECMA

Inventor： Mathieu Ange POISSON ,  Francois Robert BELLABAL ,  Nicolas FLORENT

IPC: B64D27/26 ,  B64D33/02

CPC classification number: B64D27/26 ,  B64D33/02 ,  B64D2027/005 ,  B64D2027/262 ,  F02C6/206 ,  F05D2220/325 ,  F05D2240/14 ,  Y02T50/44 ,  Y02T50/66 ,  Y02T50/671

Abstract: A suspension structure for suspending a turboprop including two unducted propellers from a structural element of an aircraft, the structure including a suspension frame for fastening to a structural element of the aircraft and including a main beam extending parallel to a longitudinal axis of the turboprop, the suspension frame being fastened to an air intake structure of the turboprop by an attachment frame.

Abstract translation: 一种悬挂结构，用于悬挂涡轮螺旋桨飞机，其包括来自飞行器的结构元件的两个未被引导的螺旋桨，该结构包括用于紧固到飞行器的结构元件的悬架，并且包括平行于涡轮螺旋桨发生器的纵向轴线延伸的主梁 悬挂框架通过附接框架紧固到涡桨螺旋桨的进气结构。

公开(公告)号：US20160375610A1

公开(公告)日：2016-12-29

申请号：US15195088

申请日：2016-06-28

Applicant: SNECMA

Inventor： Matthieu Jean Luc VOLLEBREGT ,  Patrick Emilien Paul Emile HUCHIN

IPC: B29C33/76 ,  F01D5/18

CPC classification number: B29C33/76 ,  B22C9/103 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/21 ,  F05D2260/607 ,  Y02T50/671 ,  Y02T50/676

Abstract: A core for the moulding of a turbine engine blade, this blade including a vane extending along a spanwise direction and ending in a top, this core including a first core element to delimit a first internal cavity and a second core element of which at least one portion delimits a second internal cavity. The second cavity is situated between the first cavity and the top of the blade along the spanwise direction, and the portion of the second core element delimiting the second cavity includes a through hole, which emerges in line with an end face of the first core element to constitute a de-dusting conduit of the first cavity, this conduit traversing the second cavity from end to end while emerging in the top of the blade.

Abstract translation: 一种用于模制涡轮发动机叶片的芯，该叶片包括沿翼展方向延伸并终止于顶部的叶片，该芯包括限定第一内腔的第一芯元件和至少一个 部分界定第二内腔。 第二腔沿翼展方向位于第一腔和刀片的顶部之间，并且限定第二腔的第二芯体的部分包括通孔，其与第一芯体元件的端面对齐 以构成第一腔的除尘导管，该导管在出现在叶片顶部的同时从一端到另一端横过第二腔。