公开(公告)号：US09540109B2

公开(公告)日：2017-01-10

申请号：US14446552

申请日：2014-07-30

Applicant: SNECMA

Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Julien Szydlowski

IPC: B64D27/00 ,  B64D13/00 ,  B64D29/00 ,  F02K1/82 ,  F02C7/20 ,  B64D33/08 ,  B64C7/02 ,  B64D27/12 ,  B64D27/26 ,  B64D33/04

CPC classification number: B64D13/006 ,  B64C7/02 ,  B64D27/12 ,  B64D27/26 ,  B64D29/00 ,  B64D33/04 ,  B64D33/08 ,  F02C7/20 ,  F02K1/822 ,  F05D2260/20 ,  F05D2260/231 ,  Y02T50/675

Abstract: A turbomachine including a nozzle extending along an axial direction and configured to convey a hot gas stream; and a mounting pylon for mounting the turbomachme, in which the pylon extends radially from a base arranged in the vicinity of the nozzle, is provided. The turbomachine includes a pylon cooler device having at least one auxiliary gas duct having a gas inlet configured to take cold gas from the outside of the nozzle, and a gas outlet opening out in the vicinity of the base of the pylon.

Abstract translation: 一种涡轮机，包括沿着轴向延伸并构造成传送热气流的喷嘴; 以及用于安装涡轮机的安装塔，其中塔架从布置在喷嘴附近的基座径向延伸。 涡轮机包括具有至少一个辅助气体管道的塔架冷却器装置，该辅助气体管道具有构造成从喷嘴外部取出冷气体的气体入口和在塔架的基部附近开口的气体出口。

公开(公告)号：US09683516B2

公开(公告)日：2017-06-20

申请号：US14363508

申请日：2012-12-04

Applicant: SNECMA

Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Mathieu Gaillot

IPC: F02K1/00 ,  F02K1/82 ,  F02K3/06

CPC classification number: F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2250/71

Abstract: A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.

公开(公告)号：US09726111B2

公开(公告)日：2017-08-08

申请号：US13950608

申请日：2013-07-25

Applicant: SNECMA

Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Arthur Droit

IPC: F02K1/78 ,  B64D33/04 ,  F02K1/52 ,  F02K3/06 ,  F02C7/12

Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

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。

公开(公告)号：US10036318B2

公开(公告)日：2018-07-31

申请号：US14978799

申请日：2015-12-22

Applicant: SNECMA

Inventor： Christian Vessot ,  Matthieu Leyko

IPC: F02C6/08 ,  F02C7/12 ,  F02C7/18

CPC classification number: F02C6/08 ,  F02C7/125 ,  F02C7/18 ,  F05D2250/41 ,  F05D2250/51 ,  F05D2250/90 ,  F05D2260/56 ,  Y02T50/675

Abstract: A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts, each duct being arranged between one of the side walls of the central part and one of the peripheral walls, each peripheral wall including an upstream end portion delimiting with one of the side walls an inlet orifice of one of the ducts and a downstream end portion delimiting with one of the side walls an outlet orifice of one of the ducts, at least one member mobile in translation relative to the peripheral walls, the at least one mobile member being formed in the central part and arranged so that its displacement varies a section of each of the inlet orifices and a section of at least one of the outlet orifices.

公开(公告)号：US20150033747A1

公开(公告)日：2015-02-05

申请号：US14363508

申请日：2012-12-04

Applicant: SNECMA

Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Mathieu Gaillot

IPC: F02K1/00

CPC classification number: F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2250/71

Abstract: A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.

Abstract translation: 涡轮发动机会聚发散喷嘴，包括环形中心元件和环形盖，该环形中心元件和环形盖同轴地布置在中心元件周围，以与中心元件配合以限定用于来自发动机的气流的环形流动通道。 在喉部和喷嘴的喷射部分之间，中心元件和帽在纵向截面中呈现相应的内部轮廓，该曲线由具有相同绝对值相同的曲率半径的曲线建模。

公开(公告)号：US09915227B2

公开(公告)日：2018-03-13

申请号：US13950608

申请日：2013-07-25

Applicant: SNECMA

Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Arthur Droit

IPC: F02K1/78 ,  B64D33/04 ,  F02K1/52 ,  F02K3/06 ,  F02C7/12

CPC classification number: F02K1/78 ,  B64D33/04 ,  F02C7/12 ,  F02K1/52 ,  F02K3/06 ,  Y02T50/675 ,  Y10T29/49346

Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.