公开(公告)号：US20180065730A1

公开(公告)日：2018-03-08

申请号：US15573163

申请日：2016-04-29

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Tewfik BOUDEBIZA ,  Olivier BELMONTE ,  Gilles CHARIER ,  Emmanuel Pierre Dimitri PATSOURIS ,  Pierre-Alain REIGNER

IPC: B64C11/30

CPC classification number: B64C11/308 ,  B64D2027/005 ,  Y02T50/66

Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

公开(公告)号：US20190010957A1

公开(公告)日：2019-01-10

申请号：US16067981

申请日：2017-01-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Olivier BELMONTE ,  Christophe Paul JACQUEMARD ,  Clementine Charlotte Marie MOUTON ,  Emmanuel Pierre Dimitri PATSOURIS

IPC: F04D29/36 ,  F04D29/056 ,  F16C19/54 ,  F16C19/56 ,  B64C11/32

Abstract: A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.

公开(公告)号：US20180347460A1

公开(公告)日：2018-12-06

申请号：US15994265

申请日：2018-05-31

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Julien NGUYEN VAN ,  Olivier BELMONTE ,  Jeremy Phorla LAO ,  Clementine Charlotte Marie MOUTON ,  Emmanuel Pierre Dimitri PATSOURIS ,  Didier Jean-Louis YVON

IPC: F02C6/20 ,  B64D27/14 ,  B64D27/26

CPC classification number: F02K3/065 ,  F02K3/072 ,  F05D2260/40311

Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet comprising a gas generator (3-8), a first unducted propeller (21) connected to a shaft (81) of the gas generator (3-8) via first reduction gearing (23), and a second unducted propeller (91) connected to a shaft (81) of the gas generator (3-8) via second reduction gearing (93), wherein the first propeller (21) and the first reduction gearing (23) are mounted at the front of the gas generator (3-8), and wherein the second propeller (91) and the second reduction gearing (93) are mounted at the rear of the gas generator (3-8).

公开(公告)号：US20190093508A1

公开(公告)日：2019-03-28

申请号：US16142034

申请日：2018-09-26

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Emmanuel Pierre Dimitri PATSOURIS ,  Arnaud Nicolas Negri

IPC: F01D25/16 ,  F01D25/18

Abstract: An assembly for a turbomachine including a shaft of a rotor of a turbomachine, and at least two bearings allowing at least one portion of the shaft to be supported, including a bearing support configured to be connected to a casing of the turbomachine which extends between the internal rings of the bearings while being mounted thereon, as well as a bearing connector which is connected to the shaft of the rotor and which is mounted on the external rings of the bearings while extending between them, the bearing support and the bearing connector being common to the two bearings and delimiting together at least partially an oil circulation housing common to the two bearings.

公开(公告)号：US20220154815A1

公开(公告)日：2022-05-19

申请号：US17430172

申请日：2020-02-05

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Arnaud Nicolas NEGRI ,  Julien Fabien Patrick BECOULET ,  Romain Guillaume CUVILLIER ,  Emmanuel Pierre Dimitri PATSOURIS

IPC: F16H57/08 ,  F16H1/28 ,  F01D15/12

Abstract: The invention relates to a reducing assembly (26) comprising a planet carrier (27) that is flexible and fixed, borne by a casing (32) which surrounds it by means of two distinct connections with this casing (32), with means (44) for applying a torsional prestress to the planet carrier (27) between these two connections.
Prestressing the flexible planet carrier (27) makes it possible to limit its level of mechanical stress when it is in service, in order to simplify its design and dimensioning.

公开(公告)号：US20200095876A1

公开(公告)日：2020-03-26

申请号：US16068029

申请日：2017-01-05

Applicant: Safran Aircraft Engines

Inventor： Romain Guillaume CUVILLIER ,  Nils Edouard Romain BORDONI ,  Michel Gilbert Roland BRAULT ,  Guillaume Patrice KUBIAK ,  Arnaud Nicolas NEGRI ,  Nathalie NOWAKOWSKI ,  Emmanuel Pierre Dimitri PATSOURIS ,  Sebastien Emile Philippe TAJAN

IPC: F01D7/00 ,  F02K3/06 ,  F04D29/36

Abstract: A fan of a turbine engine includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20°.

公开(公告)号：US20190195170A1

公开(公告)日：2019-06-27

申请号：US16227237

申请日：2018-12-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Emmanuel Pierre Dimitri PATSOURIS ,  Quentin Matthias Emmanuel Granaud ,  Antoine Elie Hellegouarch ,  Martial Alexandre Monseu ,  Clementine Charlotte Marie Mouton

IPC: F02K1/76 ,  F16H25/22 ,  G05G5/06

CPC classification number: F02K1/763 ,  F02K1/72 ,  F02K1/766 ,  F05D2260/57 ,  F16H25/2056 ,  F16H25/2204 ,  G05G5/06

Abstract: The turbojet comprises, linking two of its parts (1, 2) as a main nacelle portion and a rear nacelle portion, a device (4) which moves them relative to one another, for example in order to open a reverse gas thrust slot (3). The device (4) comprises a sleeve (5) and two rods (6, 7) which are coaxial connected together by two screw links (8, 9) and two locking means (10, 11) which may be engaged independently, such that the deployment of one of the rods (6) results in the opening of the slot (3) and the movement of the other rod (7), controlled by the same device (12), only occurs under specific turbojet maintenance circumstances.

公开(公告)号：US20190009887A1

公开(公告)日：2019-01-10

申请号：US16067973

申请日：2017-01-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Didier Jean-Louis YVON ,  Clementine Charlotte Marie MOUTON ,  Emmanuel Pierre Dimitri PATSOURIS

IPC: B64C11/38 ,  B64D27/16 ,  F01D7/00

Abstract: A system for controlling the pitch of fan blades of a turbine engine propeller, the system including an actuator secured to a casing of the turbine engine, having a movable portion that is movable in translation relative to the casing, the movable portion being mechanically coupled to a load transfer bearing having an outer ring that is coupled to fan blade pivots so that a movement in translation of the movable portion of the actuator leads to a change in the pitch angle of the fan blades, and at least one locking peg secured to the casing of the turbine engine and suitable, in the event of the actuator malfunctioning, for mechanically locking the load transfer bearing in a position wherein the fan blades are feathered.