公开(公告)号：US20230145551A1

公开(公告)日：2023-05-11

申请号：US17767576

申请日：2020-10-12

Applicant: SAFRAN ,  SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE ,  Ye-Bonne Karina MALDONADO

IPC: B64D29/00 ,  F01D25/00 ,  F01D5/02 ,  F02K1/00

CPC classification number: B64D29/00 ,  F01D5/02 ,  F01D25/005 ,  F02K1/002 ,  F05D2220/90 ,  F05D2240/20 ,  F05D2300/505

Abstract: A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

公开(公告)号：US20230348088A1

公开(公告)日：2023-11-02

申请号：US18001668

申请日：2021-06-10

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE ,  Camel SERGHINE

IPC: B64D35/00 ,  B64D27/24 ,  B64C27/50 ,  B64C27/54

CPC classification number: B64D35/00 ,  B64D27/24 ,  B64C27/50 ,  B64C27/54 ,  B64D2027/026

Abstract: A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

公开(公告)号：US20240084761A1

公开(公告)日：2024-03-14

申请号：US17754758

申请日：2020-10-12

Applicant: SAFRAN ,  SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE ,  Ye-Bonne Karina MALDONADO

IPC: F02K1/00 ,  B64D29/00

CPC classification number: F02K1/002 ,  B64D29/00 ,  F05D2270/64 ,  F05D2270/65 ,  F05D2300/505

Abstract: The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.

公开(公告)号：US20230249812A1

公开(公告)日：2023-08-10

申请号：US18001617

申请日：2021-06-14

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE ,  Camel SERGHINE

IPC: B64C27/50 ,  B64D29/00

CPC classification number: B64C27/50 ,  B64D29/00 ,  B64C29/0008

Abstract: A propulsion unit with a propeller includes a nacelle; a propeller rotatably mounted in the nacelle by means of a hub. The propeller has blades mounted in a blade cuff that is pivotable about a pitch axis relative to the hub. Each blade is pivotable relative to the cuff about a folding axis. A folding device includes an actuator for folding the blades. The folding device includes a control member rotationally affixed to the blade cuff and driven by the actuator. A connecting rod is pivotably mounted, on the one hand, on a root of the associated blade and, on the other hand, on the movable control member.

公开(公告)号：US20170015411A1

公开(公告)日：2017-01-19

申请号：US15300739

申请日：2015-03-30

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE

IPC: B64C27/14 ,  F01D13/00 ,  F02C7/272 ,  B64C27/00

CPC classification number: B64C27/14 ,  B64C27/006 ,  B64C27/06 ,  F01D13/003 ,  F02C7/272 ,  F05D2220/329 ,  Y02T50/671

Abstract: The invention relates to a drive chain for driving the rotor(s) (21, 22) of a helicopter, comprising a main transmission gearbox (24) capable of driving the rotor(s) (21, 22) when said gearbox is moving, a main engine (23) for providing the power for the flight, and at least one assistance drive module (31), the main engine (23) and the assistance drive module (31) being mechanically connected to said main transmission gearbox (24) so as to induce the movement of said gearbox. The drive chain is characterised in that the assistance drive module comprises a pyrotechnic device for generating a torque on a power transmission shaft that is mechanically connected to the main transmission gearbox (24). The invention also relates to a helicopter comprising said drive chain.

Abstract translation: 本发明涉及一种用于驱动直升机的转子（21,22）的驱动链，包括当所述变速箱运动时能够驱动转子（21,22）的主传动齿轮箱（24） 用于提供用于飞行的动力的主发动机（23）和至少一个辅助驱动模块（31），主发动机（23）和辅助驱动模块（31）机械连接到所述主变速箱（24） 以便引起所述变速箱的运动。 驱动链的特征在于辅助驱动模块包括用于在与主变速箱（24）机械连接的动力传动轴上产生扭矩的烟火装置。 本发明还涉及一种包括所述驱动链的直升机。

公开(公告)号：US20230234696A1

公开(公告)日：2023-07-27

申请号：US18001688

申请日：2021-06-14

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE ,  Camel SERGHINE

IPC: B64C11/28 ,  B64C11/06 ,  B64C27/28 ,  B64C29/02

CPC classification number: B64C11/28 ,  B64C11/06 ,  B64C27/28 ,  B64C29/02

Abstract: A propulsion unit with a propeller is provided, having a nacelle and a propeller rotatably mounted in the nacelle by a hub. The propeller includes blades mounted in a blade cuff pivotable about a pitch axis relative to the hub, each blade being pivotable relative to the cuff about a folding axis. The propulsion unit can further include a folding device that comprises an actuator for folding the blades. The folding device can include a control member rotationally affixed to the blade cuff and driven by the actuator, and a connecting rod pivotably mounted, on the one hand, on a root of the associated blade and, on the other hand, on the movable control member.

公开(公告)号：US20170175643A1

公开(公告)日：2017-06-22

申请号：US15116169

申请日：2015-02-06

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy BESSE

IPC: F02C7/262 ,  F01D19/00 ,  F42B3/04 ,  F02C7/272

CPC classification number: F02C7/262 ,  F01D19/00 ,  F02C3/165 ,  F02C7/272 ,  F05D2260/85 ,  F42B3/04 ,  F42B10/54

Abstract: The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum (2) rigidly connected to a rotary shaft (3), the axes of symmetry (LL) of the drum (2) and of the shaft being coincident, the flyer further comprising at least one exhaust nozzle (4) for ejecting gas, which is positioned on the periphery of the drum (2) and oriented substantially tangentially to the rotation about said axis (LL), and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle (4), said emergency start system further comprising a support in which the shaft of the flyer rotates, and a volute for recovering the gases, which radially surrounds the flyer and is rigidly connected to said support.