公开(公告)号：US20200369369A1

公开(公告)日：2020-11-26

申请号：US16068088

申请日：2016-12-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Serge Rene MORREALE ,  Yanis BENSLAMA ,  Jeremy DIEVART ,  Dominik IGEL

IPC: B64C11/32 ,  F01D7/00

Abstract: The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor (2) carrying blades (3), a stationary housing (7), a mechanism (11, 12, 13, 14, 20) for regulating the pitch of the blades (3), which is connected to the rotor, and a control means (16, 17) mounted on the stationary housing (7) and comprising a control part (18) that can be moved in translation according to an axis (X) of rotation of the rotor (2), and a bearing (19) for load transfer between the control part (18) and said mechanism, characterised in that it also comprises a stationary track (23) supporting the elastic restoring means (26, 27) which are arranged so as to exert an axial restoring force on the control part (18) towards a determined position, preferably corresponding to the blade (3) feathering.

公开(公告)号：US20220025822A1

公开(公告)日：2022-01-27

申请号：US17297076

申请日：2019-11-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alexandre Jean-Marie TAN-KIM ,  Yanis BENSLAMA ,  Jérémy DIEVART ,  Julien Fabien Patrick BECOULET

IPC: F02C7/36 ,  F02C7/06

Abstract: A turbojet engine including a central shaft surrounded by a coaxial and independent high-pressure body, the turbojet engine including, from upstream to downstream: —a fan driven by the central shaft; a high-pressure compressor and a high-pressure turbine supported by the high-pressure body; an inter-turbine housing; a low-pressure turbine; and an exhaust housing. The turbojet engine also includes: a low-pressure rotor which extends downstream of the central shaft and supports the low-pressure turbine; a rotor bearing supported by the exhaust housing; a reduction gear by which the low-pressure rotor drives the central shaft, the reduction gear being located upstream of the rotor bearing; and a downstream shaft bearing which is located upstream of the reduction gear.

公开(公告)号：US20220025821A1

公开(公告)日：2022-01-27

申请号：US17294543

申请日：2019-11-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alexandre Jean-Marie TAN-KIM ,  Yanis BENSLAMA ,  Jérémy DIEVART ,  Julien Fabien Patrick BECOULET

IPC: F02C7/36 ,  F02C7/06

Abstract: A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.

公开(公告)号：US20190153978A1

公开(公告)日：2019-05-23

申请号：US16085086

申请日：2017-03-15

Applicant: Safran Aircraft Engines

Inventor： Jeremy DIEVART ,  Yanis BENSLAMA ,  Nathalie NOWAKOWSKI

IPC: F02K3/06 ,  F02C7/06

Abstract: A turbofan engine including: a turbine shaft; a fan shaft; and a reduction mechanism coupling the turbine shaft and the fan shaft, is provided. The turbofan engine has a bypass ratio greater than or equal to 10, and the turbine shaft is supported by four bearings such that the flexural deformation modes of the turbine shaft are positioned in transient phase or outside the operating range of the turbofan engine.

公开(公告)号：US20190085790A1

公开(公告)日：2019-03-21

申请号：US16085441

申请日：2017-03-15

Applicant: Safran Aircraft Engines

Inventor： Jeremy DIEVART ,  Yanis BENSLAMA ,  Nathalie NOWAKOWSKI

IPC: F02K3/04 ,  F01D11/20 ,  F01D21/04 ,  F02C7/36

Abstract: A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

公开(公告)号：US20190003484A1

公开(公告)日：2019-01-03

申请号：US16068102

申请日：2016-12-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Serge Rene MORREALE ,  Yanis BENSLAMA ,  Jeremy DIEVART ,  Dominik IGEL

IPC: F04D29/36 ,  F04D29/32 ,  F02K3/00 ,  F04D29/056 ,  F01D7/00

Abstract: The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).