-
Patent Agency Ranking
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
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：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
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
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：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
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.
-
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).
-
-
-
-
Search Results
5
records
(took 0.016 seconds)
