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公开(公告)号：US20240052783A1
公开(公告)日：2024-02-15
申请号：US18260880
申请日：2021-12-20
IPC分类号： F02C7/266
CPC分类号： F02C7/266 , F05D2220/329 , F05D2260/85
摘要： A method for igniting a continuous combustion engine including an electronic engine control member, a high energy box, a spark plug ignition circuit and a fuel solenoid valve, cooperating with a starter motor, the method being implemented by the electronic engine control member and including precharging the high energy box before an engine starting procedure, activated on an engine starting command, the precharging being controlled by switching on the electronic engine control member, or by putting the engine in idle mode.
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公开(公告)号：US20220212547A1
公开(公告)日：2022-07-07
申请号：US17602096
申请日：2020-04-10
摘要： A hybrid propulsion installation for an aircraft, including an internal combustion engine having at least one combustion chamber; at least one electricity generator; an electrical propulsion system; electromechanical protection mechanism arranged between the or each electricity generator and the electrical propulsion system; wherein the installation also includes: an electronic computer configured to: receive at least one piece of information on a position of the electromechanical protection mechanism; receive at least one piece of information on a speed of rotation of a shaft of the internal combustion engine; and control the flow of fuel supplying the combustion chamber depending on the information received.
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3.发明申请公开(公告)号：US20180187604A1
公开(公告)日：2018-07-05
申请号：US15129240
申请日：2015-03-26
IPC分类号： F02C7/275 , B64C27/12 , B64D35/02 , B64D35/08 , F02C3/107 , F02C3/10 , F02C7/262 , F02C9/42 , F02C7/32 , H02K7/20 , H02K7/18
CPC分类号： F02C7/275 , B64C27/12 , B64D35/02 , B64D35/08 , F02C3/10 , F02C3/107 , F02C7/262 , F02C7/32 , F02C7/36 , F02C9/42 , F05D2220/329 , F05D2220/76 , H02K7/1823 , H02K7/20 , Y02T50/671
摘要： An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.
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公开(公告)号：US20180171874A1
公开(公告)日：2018-06-21
申请号：US15129309
申请日：2015-03-19
CPC分类号： F02C7/268 , B64C27/04 , B64D31/00 , B64D2221/00 , F02C6/206 , F02N11/04 , F02N11/0866 , F02N11/087 , F02N2011/0885 , F02N2300/2002 , F05D2220/323 , F05D2220/76 , F05D2260/42 , F05D2260/85 , F05D2270/304 , H02J7/1423 , H02J7/345 , Y02T50/671
摘要： The system for rapidly reactivating a turbine engine of an aircraft includes an electrical machine that is DC powered from an on-board electrical power supply network. The system also includes a switch interposed between the on-board network and the electrical machine, an additional set including a plurality N electrical energy storage elements, and a control unit for controlling a device for discharging the storage elements and adapted to enable a series circuit including at least some of the N electrical energy storage elements to be connected in parallel with the on-board network so that when the rapid reactivation system is in operation the electrical machine is powered by a voltage level higher than the voltage level of its nominal characteristics.
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公开(公告)号：US20170292491A1
公开(公告)日：2017-10-12
申请号：US15518199
申请日：2015-10-06
发明人： Romain THIRIET , Jean-Michel BAZET , Guillaume COTTIN , Camel SERGHINE , Patrick MARCONI , Bertrand MOINE , Vincent POUMAREDE
CPC分类号： F02P7/028 , F01D19/00 , F02B53/12 , F02C7/232 , F02C7/264 , F02C9/266 , F02C9/56 , F02P5/045 , F05D2260/80 , Y02T50/671
摘要： 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.
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