公开(公告)号：US20180281978A1

公开(公告)日：2018-10-04

申请号：US15765469

申请日：2016-09-29

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Albert BEUTIN ,  Nicolas Maurice Herve AUSSEDAT ,  Nicolas Alain BADER ,  Philippe Gerard CHANEZ ,  Gilles Alain CHARIER ,  Mathieu LALLIA ,  Lionel Jean Leon LEFRANC ,  Kevin Morgane LEMARCHAND ,  Herve Jean Albert MOUTON ,  Nicolas Joseph SIRVIN ,  Ludovic Michael Laurent TOUPET ,  Christian Sylvain VESSOT ,  Nathalie NOWAKOWSKI

IPC: B64D27/12 ,  B64D33/02 ,  B64D27/26 ,  B64C3/32 ,  B64C3/18 ,  F02C7/20 ,  F02C7/04 ,  F02K3/077 ,  B64D33/04 ,  F02K1/52

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (α) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.

公开(公告)号：US20170137135A1

公开(公告)日：2017-05-18

申请号：US15346612

申请日：2016-11-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Philippe Gerard CHANEZ ,  Mathieu Patrick Jean-Louis LALLIA ,  Christian Sylvain VESSOT

IPC: B64D27/18 ,  B64D33/02 ,  F02C7/05

CPC classification number: B64D27/18 ,  B64D27/12 ,  B64D33/02 ,  B64D2033/0286 ,  F02C7/05 ,  F02K1/52 ,  F02K3/06 ,  F02K3/077 ,  F05D2240/40 ,  F05D2250/312

Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane.According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17′) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.

公开(公告)号：US20210207494A1

公开(公告)日：2021-07-08

申请号：US17058433

申请日：2019-05-24

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Romain Jean-Claude FERRIER ,  Sebastien Christophe CHALAUD ,  Philippe Gerard CHANEZ ,  Lauren DAVIS ,  Bastien Pierre VERDIER ,  Christian Sylvain VESSOT

IPC: F01D25/12

Abstract: The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.

公开(公告)号：US20180135557A1

公开(公告)日：2018-05-17

申请号：US15785953

申请日：2017-10-17

Applicant: Safran Aircraft Engines

Inventor： Guillaume Rodolphe Jacques Gerard POUYAU ,  Gabriela PHILIPPART ,  Christian Sylvain VESSOT ,  Marc Patrick TESNIERE

IPC: F02K3/06 ,  F02C7/042 ,  F04D29/36 ,  F01D9/06 ,  F02K1/66 ,  B64D33/02

CPC classification number: F02K3/06 ,  B64D27/16 ,  B64D33/02 ,  B64D2033/0286 ,  F01D9/065 ,  F02C7/042 ,  F02K1/66 ,  F02K3/075 ,  F04D29/362 ,  F05D2220/323 ,  F05D2260/50

Abstract: Propulsion assembly comprising: an inner casing (13); an outer casing (3); an inter-duct casing (15) delimiting a primary duct (12) between the inner casing (13) and an outer wall (14), and a secondary duct (16) between the outer casing (3) and an outer wall (17); a fan capable of generating an air flow (24) circulating from downstream to upstream in the secondary duct (16); the assembly further comprising: at least one duct (27) for bleeding air from said flow (24), this bleed duct (27) comprising an inlet port (28) in the outer wall (17) and an outlet port (29) in the inner wall (14); an outer flap (30) movable between an open position and a closed position of the inlet port (28); an inner flap (31) movable between an open position and a closed position of the outlet port (29).