公开(公告)号：US20140290270A1

公开(公告)日：2014-10-02

申请号：US14356045

申请日：2012-10-24

Applicant: SNECMA

Inventor： Guillaume Bodard ,  Cyprien Henry ,  Norman Jodet ,  Alexandre Alfred, Gaston Vuillemin

IPC: F02C7/20

CPC classification number: F02C7/20 ,  B64C2230/14 ,  B64D29/02 ,  Y02T50/166

Abstract: A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral faces and defined longitudinally between a leading edge and a trailing edge. On each of its lateral faces the pylon includes a series of deflectors that are transversely spaced apart from one another and that define between them convergent and curved channels configured to accelerate air streams flowing within the channels on aircraft takeoff or in flight to deflect the air streams towards a jet of the engine.

Abstract translation: 一种用于附接涡轮发动机的吊架，所述吊架构造成将发动机连接到飞行器的结构元件。 塔架包括由两个相对的侧面限定的流线型轮廓，并且在前缘和后缘之间纵向限定。 在其每个侧面上，塔架包括一系列偏转器，它们彼此横向地间隔开并且在它们之间限定会聚的和弯曲的通道，其被构造成加速飞行器起飞或飞行中在通道内流动的空气流，以使空气流 朝向发动机的喷气式飞机。

公开(公告)号：US08881502B2

公开(公告)日：2014-11-11

申请号：US14035113

申请日：2013-09-24

Applicant: SNECMA

Inventor： Norman Jodet ,  Guillaume Bodard ,  Cyprien Georges Eric Henry ,  Maxime Koenig

IPC: F02K1/38 ,  F02K1/34 ,  F02K1/48

CPC classification number: F02K1/34 ,  F02K1/48 ,  Y02T50/671

Abstract: A mixer for a confluent-flow nozzle of a turbine engine is provided. The mixer includes: an annular cap designed to be centered on a longitudinal axis of the nozzle and having a stationary upstream portion and a downstream portion that is movable in rotation about the longitudinal axis relative to the stationary portion, the movable portion of the cap terminating at its downstream end in inner lobes alternating circumferentially with outer lobes; and a mechanism which imparts reciprocating rotary motion to the movable portion of the cap.

Abstract translation: 提供了一种用于涡轮发动机的汇流流动喷嘴的混合器。 混合器包括：环形帽，设计成以喷嘴的纵向轴线为中心，并且具有固定的上游部分和可相对于固定部分围绕纵向轴线旋转的下游部分，帽子的可移动部分终止 在其下部端部在内部裂片周向交替地具有外部波瓣; 以及向帽的可动部进行往复旋转运动的机构。

公开(公告)号：US09617954B2

公开(公告)日：2017-04-11

申请号：US14346602

申请日：2012-09-24

Applicant: SNECMA

Inventor： Alexandre Alfred Gaston Vuillemin ,  Guillaume Bodard ,  Sebastien Jean-Paul Aeberli

IPC: F02K1/28 ,  F02K1/34 ,  F02K1/30 ,  F02K3/02 ,  F02K3/075 ,  F02K1/46 ,  F02K1/38

CPC classification number: F02K1/34 ,  F02K1/28 ,  F02K1/30 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/025 ,  F02K3/075 ,  Y02T50/671

Abstract: The invention relates to a primary cowl for a turbofan comprising a primary body generating a primary stream to be ejected through a primary nozzle, and a secondary body generating a secondary stream to be ejected through a secondary nozzle, the primary cowl being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbofan, the path followed by the primary stream downstream from the primary nozzle and, on the outside, the path followed by the secondary stream downstream from the secondary nozzle. The primary cowl comprises a coupling to a system for supplying a pressurized gas and at least one perforation for injecting the pressurized gas, through the perforation, into the secondary stream. The primary cowl preferably comprises a ring which has perforations and which is rotated about the axis of rotation of the turbofan.

公开(公告)号：US20140245715A1

公开(公告)日：2014-09-04

申请号：US14346602

申请日：2012-09-24

Applicant: SNECMA

Inventor： Alexandre Alfred Gaston Vuillemin ,  Guillaume Bodard ,  Sebastien Jean-Paul Aeberli

IPC: F02K1/34 ,  F02K3/02 ,  F02K1/38

CPC classification number: F02K1/34 ,  F02K1/28 ,  F02K1/30 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/025 ,  F02K3/075 ,  Y02T50/671

Abstract: The invention relates to a primary cowl for a turbofan comprising a primary body generating a primary stream to be ejected through a primary nozzle, and a secondary body generating a secondary stream to be ejected through a secondary nozzle, the primary cowl being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbofan, the path followed by the primary stream downstream from the primary nozzle and, on the outside, the path followed by the secondary stream downstream from the secondary nozzle. The primary cowl comprises a coupling to a system for supplying a pressurised gas and at least one perforation for injecting the pressurised gas, through the perforation, into the secondary stream. The primary cowl preferably comprises a ring which has perforations and which is rotated about the axis of rotation of the turbofan.

Abstract translation: 本发明涉及一种用于涡轮风扇的主罩，其包括主体，其产生要通过主喷嘴喷射的主流，以及产生要通过次喷嘴喷射的次流的次体，该主罩被成形为 位于主体的下游并且在涡轮风扇的内侧上限定了从主喷嘴下游的初级流的路径，并且在外部将辅助流的下游路径跟随在二次喷嘴的下游。 主罩包括与用于供应加压气体的系统的联接件和用于将加压气体通过穿孔注入次流中的至少一个穿孔。 主罩盖优选地包括具有穿孔并且围绕涡轮风扇的旋转轴线旋转的环。

公开(公告)号：US09938901B2

公开(公告)日：2018-04-10

申请号：US14356045

申请日：2012-10-24

Applicant: SNECMA

Inventor： Guillaume Bodard ,  Cyprien Henry ,  Norman Jodet ,  Alexandre Alfred Gaston Vuillemin

IPC: F02C7/20 ,  B64D29/02

CPC classification number: F02C7/20 ,  B64C2230/14 ,  B64D29/02 ,  Y02T50/166

Abstract: A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral faces and defined longitudinally between a leading edge and a trailing edge. On each of its lateral faces the pylon includes a series of deflectors that are transversely spaced apart from one another and that define between them convergent and curved channels configured to accelerate air streams flowing within the channels on aircraft takeoff or in flight to deflect the air streams towards a jet of the engine.

公开(公告)号：US09249755B2

公开(公告)日：2016-02-02

申请号：US13764125

申请日：2013-02-11

Applicant: SNECMA

Inventor： Julien Szydlowski ,  Guillaume Bodard ,  Matthieu Leyko ,  Jonathan Langridge

IPC: F02K1/48 ,  F02K1/38 ,  F02K1/46 ,  A45D34/00 ,  A45D40/00

CPC classification number: F02K1/48 ,  A45D34/00 ,  A45D40/00 ,  F02K1/386 ,  F02K1/46 ,  F05B2250/611 ,  F05D2240/127 ,  F05D2250/323 ,  F05D2260/96 ,  F05D2270/20 ,  Y10T29/49826

Abstract: According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.

Abstract translation: 根据本发明，用于定义纵向轴线LL的会聚发散喷嘴的形状的方法包括在喉部处连接到其下游自由端的发散部分的收敛部分，该收敛部分包括分隔在其中的减少噪音的人字形的扇贝 圆周方向包括使用发散的第一部分，发散的第二部分和收敛部分事先确定喷嘴的发散部分，将初始值归因于定义人字形和三部分的尺寸参数，计算性能标准并检查 计算的性能标准满足预定义的性能条件。