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：US20190337611A1

公开(公告)日：2019-11-07

申请号：US16480260

申请日：2018-02-14

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Romain THIRIET ,  Jean Michel BAZET ,  Jean-Luc Charles Gilbert FREALLE ,  Pierre DARFEUIL

IPC: B64C27/00 ,  B64C27/06 ,  B64C27/57 ,  B64C13/24

Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.

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.