公开(公告)号：US10118710B2

公开(公告)日：2018-11-06

申请号：US15050637

申请日：2016-02-23

Applicant: SNECMA ,  AIRCELLE

Inventor： Charles-Henri Michel Marie Derrez ,  Adrien Jacques Philippe Fabre ,  Sebastien Marcelino Juste ,  Cyril Roger Yves Le Pecheur ,  Michel Pierre Rognant

IPC: B64D29/06 ,  B64C11/02 ,  B64C11/06 ,  B64C11/48 ,  F04D29/32 ,  B64D27/10 ,  B64D29/08 ,  B64F5/40

Abstract: An unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.

公开(公告)号：US10113506B2

公开(公告)日：2018-10-30

申请号：US14881886

申请日：2015-10-13

Applicant: AIRCELLE

Inventor： Hélène Malot ,  Jean-Pierre Guegou ,  Philippe Bienvenu ,  Philippe Prunin

IPC: F01D25/24 ,  F02K1/28 ,  F02K1/82 ,  F02K3/072 ,  F02C3/067 ,  F02K3/06

Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

公开(公告)号：US10087841B2

公开(公告)日：2018-10-02

申请号：US14846129

申请日：2015-09-04

Applicant: AIRCELLE

Inventor： Pierre Caruel

IPC: F02C7/14 ,  F01D25/24 ,  F01D25/12 ,  B64D33/02

Abstract: The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air.

公开(公告)号：US10016912B2

公开(公告)日：2018-07-10

申请号：US14761792

申请日：2014-01-09

Applicant: SAFRAN ,  AIRCELLE

Inventor： Patrick Dunleavy ,  Bertrand Desjoyeaux

IPC: D03D3/02 ,  B60B11/06 ,  B29B11/16 ,  D03D25/00

CPC classification number: B29B11/16 ,  B60B11/06 ,  B60B2310/241 ,  B60B2360/3444 ,  B60Y2200/51 ,  D03D3/02 ,  D03D25/005 ,  D10B2101/06 ,  D10B2101/08 ,  D10B2505/02 ,  Y10T428/1314 ,  Y10T428/1362

Abstract: A single-piece woven fiber structure for fabricating an axisymmetric part of varying diameter made out of composite material, the fiber structure having a portion of frustoconical shape with a large diameter and a small diameter, the ratio between the large diameter and the small diameter being not less than 2. The fiber structure is formed by winding layers of warp and weft yarns that are woven on a mandrel having a profile that is defined as a function of the profile of the part to be fabricated with warp yarn take-up. For each layer of yarns, the weft yarns are angularly distributed on a single diameter in a zone of the large diameter of the portion of frustoconical shape and on at least two different diameters in a zone of the small diameter of the portion of frustoconical shape in order to form at least two superposed plies of weft yarns.

公开(公告)号：US09938897B2

公开(公告)日：2018-04-10

申请号：US14496518

申请日：2014-09-25

Applicant: Aircelle

Inventor： Jean-Philippe Joret ,  André Baillard

IPC: B64D33/02 ,  F02C7/045 ,  B64D29/06 ,  F02C7/20 ,  B64D29/00

CPC classification number: F02C7/045 ,  B64D29/00 ,  B64D29/06 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/20 ,  F05D2230/64 ,  Y10T137/0536

Abstract: An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.

公开(公告)号：US09835113B2

公开(公告)日：2017-12-05

申请号：US15076907

申请日：2016-03-22

Applicant: AIRCELLE

Inventor： Alexis Loncle

IPC: F02K1/78 ,  F02K1/76 ,  F02K1/72 ,  B64D29/06 ,  E05B63/18 ,  F02K1/80

CPC classification number: F02K1/766 ,  B64D29/06 ,  E05B63/18 ,  E05B63/185 ,  F02K1/72 ,  F02K1/763 ,  F02K1/80 ,  Y02T50/671

Abstract: The present disclosure relates to a thrust reverser for a turbojet engine nacelle, including cowls that move backwards to open the thrust reverser. Each cowl includes a primary axial guide rail that receives most of the loads of the cowl, and secondary rails guiding an outer portion of each cowl. The thrust reverser includes a rear end stop for each cowl is arranged on the primary axial guide rails.

公开(公告)号：US20170298870A1

公开(公告)日：2017-10-19

申请号：US15290115

申请日：2016-10-11

Applicant: AIRCELLE

Inventor： Patrick BOILEAU ,  Olivier KERBLER

IPC: F02K1/60 ,  F02K1/76

CPC classification number: F02K1/766 ,  F02K1/09 ,  F02K1/72 ,  F02K1/763 ,  F02K1/80

Abstract: A thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.

公开(公告)号：US09777598B2

公开(公告)日：2017-10-03

申请号：US14471307

申请日：2014-08-28

Applicant: AIRCELLE

Inventor： Jean-Philippe Joret ,  Xavier Bouteiller ,  Xavier Cazuc ,  Pierre Caruel

IPC: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2250/14

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

公开(公告)号：US09670878B2

公开(公告)日：2017-06-06

申请号：US14322601

申请日：2014-07-02

Applicant: AIRCELLE

Inventor： Xavier Cazuc ,  Jean-Philippe Joret

IPC: F01D25/24 ,  F02K1/82 ,  F01D9/04

CPC classification number: F02K1/827 ,  F01D9/041 ,  F05D2260/96 ,  F05D2260/963 ,  Y02T50/672 ,  Y02T50/673

Abstract: A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure.

公开(公告)号：US09670874B2

公开(公告)日：2017-06-06

申请号：US15093798

申请日：2016-04-08

Applicant: AIRCELLE

Inventor： Fabrice Provost

IPC: F02K1/72 ,  F02K1/80 ,  F16J15/02 ,  F02K1/56 ,  F01D11/00 ,  F16J15/06

CPC classification number: F02K1/566 ,  F01D11/005 ,  F02K1/72 ,  F02K1/805 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2240/55 ,  F05D2250/182 ,  F05D2260/30 ,  F16J15/027 ,  F16J15/061

Abstract: The present disclosure relates to a seal for an aircraft turbojet engine nacelle thrust reverser, the seal having body having a cross section with respect to a longitudinal axis of the seal that is substantially circular, and a base which is intended to be mounted in a seal support. The seal is notable in that the base of said seal has apertures spaced from each other.