公开(公告)号：US20140061331A1

公开(公告)日：2014-03-06

申请号：US13950608

申请日：2013-07-25

Applicant: SNECMA

Inventor： Matthieu LEYKO ,  Jean Bertucchi ,  Arthur Droit

IPC: F02K1/78

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.

Abstract translation: 公开了一种用于飞机的分离的双流涡轮喷气发动机的排出系统，其由悬架杆支撑。 该系统包括由环形整流罩限定的主喷嘴，其具有限定整流罩的上游和下游部分的环形形状的狭槽，并且由悬架桅杆穿过。 主喷嘴的整流罩的下游部分包括在整流罩的上游部分的下游延伸到主喷嘴的后缘的第一部分，沿着两个预定义的角度部分在悬架的两侧; 以及第二部分，其由所述狭槽的内部轮廓形成，并具有直径小于与所述整流罩的所述下游部分的所述第一部分相关联的所述后缘的直径的后缘。 连接壁横向连接下游部分的第一和第二部分。

公开(公告)号：US20170175554A1

公开(公告)日：2017-06-22

申请号：US14978799

申请日：2015-12-22

Applicant: SNECMA

Inventor： Christian VESSOT ,  Matthieu LEYKO

IPC: F01D9/04 ,  F01D25/12 ,  F01D17/12

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：US20150284098A1

公开(公告)日：2015-10-08

申请号：US14446552

申请日：2014-07-30

Applicant: SNECMA

Inventor： Matthieu LEYKO ,  Jean BERTUCCHI ,  Julien SZYDLOWSKI

IPC: B64D13/00 ,  B64D33/04 ,  B64D27/12 ,  B64D27/26

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 (10) comprising a nozzle (14) extending along an axial direction (A), said nozzle (14) being configured to convey a hot gas stream (GC), and a mounting pylon (12) for mounting the turbomachine, said pylon (12) extending radially from a base (12a) arranged in the vicinity of the nozzle (14). The turbomachine (10) includes a pylon cooler device (18) having at least one auxiliary gas duct (20) having a gas inlet (20a) configured to take cold gas (GF) from the outside of the nozzle (14), and a gas outlet (20b) opening out in the vicinity of the base (12a) of the pylon (12).

Abstract translation: 一种涡轮机（10），包括沿着轴向方向（A）延伸的喷嘴（14），所述喷嘴（14）构造成输送热气流（GC）和用于安装涡轮机的安装塔（12），所述安装塔 塔架（12）从布置在喷嘴（14）附近的基部（12a）径向延伸。 涡轮机（10）包括具有至少一个辅助气体管道（20）的塔架冷却器装置（18），该辅助气体管道具有从喷嘴（14）的外部取得冷气体（GF）的气体入口（20a） 气体出口（20b）在塔架（12）的底座（12a）附近开口。

公开(公告)号：US20130206865A1

公开(公告)日：2013-08-15

申请号：US13764125

申请日：2013-02-11

Applicant: SNECMA

Inventor： Julien SZYDLOWSKI ,  Guillaume BODARD ,  Matthieu LEYKO ,  Jonathan LANGRIDGE

IPC: F02K1/48

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。