公开(公告)号：US09885315B2

公开(公告)日：2018-02-06

申请号：US14326160

申请日：2014-07-08

Applicant: SNECMA ,  Centre National De La Recherche Scientifique (CNRS) ,  UNIVERSITE DE POITIERS ,  ENSMA

Inventor： Alexandre Alfred Gaston Vuillemin ,  Maxime Koenig ,  Peter Jordan ,  Pierre Comte ,  Yves Gervais

IPC: F02K1/34 ,  F02K1/46

CPC classification number: F02K1/34 ,  F02K1/46 ,  F02K3/06 ,  F05D2250/411 ,  F05D2260/962 ,  Y02T50/671

Abstract: The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.

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.