公开(公告)号：US20220213842A1

公开(公告)日：2022-07-07

申请号：US17608685

申请日：2020-07-03

Applicant: SAFRAN HELICOPTER ENGINES ,  SAFRAN POWER UNITS

Inventor： Fabien MERCIER-CALVAIRAC ,  Patrick MARCONI ,  Denis Antoine Julien REAL

IPC: F02C9/28 ,  B64D27/24 ,  B64F5/60 ,  B64D31/06 ,  F02C6/00

Abstract: A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.

公开(公告)号：US20170122221A1

公开(公告)日：2017-05-04

申请号：US15128060

申请日：2015-03-20

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Patrick MARCONI ,  Romain THIRIET ,  Olivier BEDRINE

IPC: F02C9/16 ,  F02C7/268 ,  F02C3/04 ,  B64D27/14 ,  B64C27/04

CPC classification number: F02C9/16 ,  B64C27/04 ,  B64D27/14 ,  F02C3/04 ,  F02C3/10 ,  F02C3/113 ,  F02C7/268 ,  F05D2220/329 ,  F05D2270/023 ,  F05D2270/304 ,  Y02T50/671

Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterised in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.

公开(公告)号：US20170292491A1

公开(公告)日：2017-10-12

申请号：US15518199

申请日：2015-10-06

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Romain THIRIET ,  Jean-Michel BAZET ,  Guillaume COTTIN ,  Camel SERGHINE ,  Patrick MARCONI ,  Bertrand MOINE ,  Vincent POUMAREDE

IPC: F02P7/02 ,  F02C9/26 ,  F02P5/04

CPC classification number: F02P7/028 ,  F01D19/00 ,  F02B53/12 ,  F02C7/232 ,  F02C7/264 ,  F02C9/266 ,  F02C9/56 ,  F02P5/045 ,  F05D2260/80 ,  Y02T50/671

Abstract: A system for igniting a combustion chamber of a turboshaft engine, comprising: a plurality of start-up injectors which are suitable for injecting fuel into said chamber during a combustion-initiating phase; a circuit for supplying fuel to said start-up injectors, comprising a first sub-circuit, referred to as the primary start-up circuit, designed to supply fuel to some of said plurality of start-up injectors; a second sub-circuit, referred to as the secondary start-up circuit, designed to supply fuel to the other start-up injectors of said plurality.

公开(公告)号：US20170241347A1

公开(公告)日：2017-08-24

申请号：US15519804

申请日：2015-10-14

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Patrick MARCONI ,  Romain THIRIET ,  Camel SERGHINE ,  Caroline SEVE ,  Pierre DARFEUIL

IPC: F02C7/277 ,  B64C27/14 ,  B64D27/10 ,  F02C7/36

CPC classification number: F02C7/277 ,  B64C27/14 ,  B64D27/10 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/329 ,  F05D2220/50 ,  Y02T50/671

Abstract: The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine (6) being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.

公开(公告)号：US20210108578A1

公开(公告)日：2021-04-15

申请号：US16500285

申请日：2018-03-30

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Pierre DARFEUIL ,  Patrick MARCONI ,  Caroline SEVE

IPC: F02C9/42 ,  B64D27/10 ,  B64D31/02 ,  F02C6/20

Abstract: A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.

公开(公告)号：US20170101936A1

公开(公告)日：2017-04-13

申请号：US15128375

申请日：2015-03-20

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Patrick MARCONI ,  Romain THIRIET ,  Camel SERGHINE

IPC: F02C7/36 ,  F02C3/04 ,  B64D27/10

Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterised in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.