公开(公告)号：US20220145805A1

公开(公告)日：2022-05-12

申请号：US17431896

申请日：2020-02-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Arnaud Nicolas NEGRI ,  Julien Fabien Patrick BECOULET ,  Michel Gilbert Roland BRAULT ,  Romain Guillaume CUVILLIER

IPC: F02C7/36 ,  F16D9/08 ,  F16C3/02

Abstract: A drive shaft of an aircraft turbine engine includes a first portion and a second portion, and connecting means connecting the first and second portions and being configured to transmit a torque from the second portion to the first portion. The connecting means has at least one bellows with a first section having a diameter greater than the diameters of the first and second portions and second sections flanking the first section. The first section includes at least one fusible section with at least one through-hole and being configured to break when the value of a torque applied to the first portion exceeds a predetermined threshold value.

公开(公告)号：US20210164350A1

公开(公告)日：2021-06-03

申请号：US16954143

申请日：2018-12-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Arnaud Nicolas NEGRI ,  Julien Fabien Patrick BECOULET ,  Michel Gilbert Roland BRAULT ,  Guillaume Patrice KUBIAK

IPC: F01D5/02 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F16D1/10

Abstract: A shaft assembly (22, 32) for an aircraft turbine engine (1), comprising a first outer shaft (32) and a second inner shaft (22), the first outer shaft being intended to be engaged axially on the second shaft and comprising inner longitudinal splines (34) for coupling with outer longitudinal splines (24) of the second shaft, characterised in that, when the first and second shafts are in the coupling position, the inner and outer splines are engaged in one another and cooperate with each other in an axial coupling area (Z), the inner and outer teeth being situated outside this coupling area.

公开(公告)号：US20170191495A1

公开(公告)日：2017-07-06

申请号：US15398133

申请日：2017-01-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nils Edouard Romain BORDONI ,  Michel Gilbert Roland BRAULT ,  Romain Guillaume CUVILLIER ,  Guillaume Patrice KUBIAK ,  Arnaud Nicolas NEGRI ,  Nathalie NOWAKOWSKI

IPC: F04D29/36 ,  F04D19/00 ,  F02K3/06

CPC classification number: F04D29/36 ,  B64C11/00 ,  B64C11/30 ,  B64C11/325 ,  F01D7/02 ,  F02K3/06 ,  F04D19/002 ,  F04D29/323 ,  F04D29/366 ,  F05D2220/36 ,  F05D2250/311 ,  F05D2260/40311 ,  F05D2260/71 ,  F05D2260/79 ,  Y02T50/671 ,  Y02T50/673

Abstract: A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.

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：US20210087947A1

公开(公告)日：2021-03-25

申请号：US16956407

申请日：2018-12-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel Gilbert Roland BRAULT ,  Romain Guillaume CUVILLIER ,  Julien Fabien Patrick BECOULET ,  Arnaud Nicolas NEGRI

IPC: F01D25/18 ,  F16J15/16

Abstract: Dynamic sealing device for an aircraft turbomachine, comprising two rotors (3, 8) which are configured to rotate about the one same axis (A) and different speeds, the said rotors extending at least in part around one another and dynamic sealing means (14) being mounted between the said rotors, characterized in that:—the said sealing means comprise annular rings (38) extending about the said axis, these rings being mounted with the ability to slide on a first (3) of the said rotors, in a radial direction with respect to the said axis, and being able to bear radially via their external periphery against a second (8) of the said rotors which at least partially surrounds the said first rotor, and in that it further comprises:—oil discharge means comprising an annular cavity (44) formed in the said second rotor, the said annular cavity opening radially towards the inside in the vicinity of the said sealing means and being in fluidic communication with oil passage ports (45) formed in the bottom of the cavity and passing through the said second rotor.

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：US20200018181A1

公开(公告)日：2020-01-16

申请号：US16471489

申请日：2017-12-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel Gilbert Roland BRAULT ,  Julien Fabien Patrick BECOULET ,  Arnaud Nicolas NEGRI ,  Didier Jean-Louis YVON

IPC: F01D21/04

Abstract: A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (20) and the fan shaft (18), which decoupling means are able to decouple the reduction device (20) and the fan shaft (18), characterized in that the reduction device (20) is coupled to the fan shaft via the intermediary of a coupling (17) having trapezoidal teeth of the curvic type which comprises said decoupling means (28), said decoupling means (28) being configured to decouple the reduction device (20) and the fan shaft (18) in response to a predetermined resistive torque (CD), referred to as the decoupling torque, being exceeded, which torque acts between the fan shaft (18) and the reduction device (20).

公开(公告)号：US20190153958A1

公开(公告)日：2019-05-23

申请号：US16076294

申请日：2017-02-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume Patrice KUBIAK ,  Nils Edouard Romain BORDONI ,  Michel Gilbert Roland BRAULT ,  Romain Guillaume CUVILLIER ,  Benoit Jean Henri GOMANNE ,  Arnaud Nicolas NEGRI ,  Nicolas Xavier TRAPPIER

IPC: F02C7/36 ,  F02K3/04 ,  F01D5/30 ,  F16H1/28 ,  F16H57/08 ,  F16C1/02

Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis Ω, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.

公开(公告)号：US20190101081A1

公开(公告)日：2019-04-04

申请号：US16085394

申请日：2017-03-15

Applicant: Safran Aircraft Engines

Inventor： Romain Guillaume CUVILLIER ,  Nils Edouard Romain BORDONI ,  Michel Gilbert Roland BRAULT ,  Sebastien Christophe CHALAUD ,  Guillaume Patrice KUBBIAK ,  Arnaud Nicolas NEGRI ,  Nathalie NOWAKOWSKI

IPC: F02K3/06 ,  F02C7/36 ,  F01D25/20 ,  F02C7/06

Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.

公开(公告)号：US20190085724A1

公开(公告)日：2019-03-21

申请号：US16085366

申请日：2017-03-15

Applicant: Safran Aircraft Engines

Inventor： Romain Guillaume CUVILLIER ,  Nils Edouard Romain BORDONI ,  Michel Gilbert Roland BRAULT ,  Jeremy DIEVART ,  Guillaume Patrice KUBIAK ,  Arnaud Nicolas NEGRI ,  Nathalie NOWAKOWSKI

IPC: F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F01D25/20

Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.