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公开(公告)号：US11370551B2
公开(公告)日：2022-06-28
申请号：US17051587
申请日：2019-04-04
Inventor： Mathieu Jean Jacques Santin , Guillaume Julien Beck , Aldric Renaud Gabriel Marie Moreau De Lizoreux , Boris Pierre Marcel Morelli , Jean-Michel Bernard Paul Chastagnier , Thomas Turchi
Abstract: A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.
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公开(公告)号：US10301035B2
公开(公告)日：2019-05-28
申请号：US14410671
申请日：2013-06-12
Applicant: SAFRAN HELICOPTER ENGINES , SAFRAN POWER UNITS , SAFRAN ELECTRICAL & POWER
Inventor： Olivier Bedrine , Christian Sarrat , Fabien Silet , Sebastien Vieillard
Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.
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公开(公告)号：US20170226933A1
公开(公告)日：2017-08-10
申请号：US15502017
申请日：2015-07-31
Inventor： Thomas KLONOWSKI , Michel NOLLET , Frederic PAILHOUX
IPC: F02C7/268 , F01D15/10 , F02C3/10 , F02C6/14 , H01G11/14 , H01M10/04 , H01M10/625 , H01G11/78 , H01G11/08 , F02C7/32 , H01M10/42
CPC classification number: F02C7/268 , F01D15/10 , F02C3/10 , F02C6/14 , F02C7/26 , F02C7/32 , F02C9/42 , F02K9/38 , F02K9/95 , F05D2220/32 , F05D2270/09 , H01G11/08 , H01G11/14 , H01G11/78 , H01M10/04 , H01M10/425 , H01M10/625 , H01M2010/4271 , H01M2220/20
Abstract: The rapid assistance device applies to a free turbine engine of an aircraft having at least a first free turbine engine provided with a gas generator and associated with an electrical machine capable of operating both as a starter and as a generator, the first engine being capable of being put into a standby mode or into an unwanted shut-down mode, the electrical machine being powered from on on-board electrical energy power supply network. The device further includes at least one electrical energy storage member adapted to be electrically connected to the electrical machine associated with the first engine in order to provide a burst of assistance to the gas generator of that engine. The electrical energy storage member constitutes a non-rechargeable “primary” energy storage member that can be used once only. The device includes a system for activating the electrical energy storage member and a device for coupling the electrical energy storage member with an electrical power supply system of the electrical machine.
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公开(公告)号：US20230368683A1
公开(公告)日：2023-11-16
申请号：US18247011
申请日：2021-09-14
Inventor： Hakim MAALIOUNE , Laurent MIRALLES , Christophe BASTIDE , Jérémy Edmond FERT , Vincent HUPIN
CPC classification number: G08G5/065 , G08G5/0013 , G08G5/0065 , G08G5/0091
Abstract: A system for real-time control of the trajectory of an aircraft on a runway, includes at least one steering system configured to steer the aircraft on the ground, each steering system being associated with at least one use parameter; a computer configured for determining, from aircraft data and external data including runway condition data and ground meteorological data, each steering system intended to steer the aircraft according to a predetermined trajectory and each corresponding use parameter; and a control system configured to control each steering system determined according to each corresponding determined use parameter.
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公开(公告)号：US20220411082A1
公开(公告)日：2022-12-29
申请号：US17756132
申请日：2020-11-12
Applicant: SAFRAN , SAFRAN AIRCRAFT ENGINES , SAFRAN ELECTRICAL & POWER
Inventor： Philippe DELBOSC , Clement DUPAYS , Anne LIENHARDT , Benoit MICHAUD , Cyrille GAUTIER , Anthony GIMENO
Abstract: The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.
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Patent Agency Ranking
16.发明授权公开(公告)号：US10858112B2
公开(公告)日：2020-12-08
申请号：US15115137
申请日：2015-01-29
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN , SAFRAN POWER UNITS
Inventor： Nicolas Claude Parmentier , Pierre Froment , Jean-François Rideau , Bruno Thoraval
IPC: B64D13/06 , F02C6/20 , B64D13/00 , B64D13/02 , B64D13/08 , B64D27/10 , F04D29/32 , F04D29/52 , F04D29/56 , F04D29/58 , F02C7/27 , F02C9/18
Abstract: An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the means for supplying air has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.
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17.发明授权公开(公告)号：US10703487B2
公开(公告)日：2020-07-07
申请号：US15115116
申请日：2015-01-29
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN , SAFRAN POWER UNITS
Inventor： Nicolas Claude Parmentier , Pierre Froment , Jean-François Rideau , Bruno Thoraval
IPC: B64D13/06 , F02C6/20 , B64D13/00 , B64D13/02 , B64D13/08 , B64D27/10 , F04D29/32 , F04D29/52 , F04D29/56 , F04D29/58 , F02C7/27 , F02C9/18
Abstract: An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.
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公开(公告)号：US20240003261A1
公开(公告)日：2024-01-04
申请号：US18265021
申请日：2021-12-01
Applicant: SAFRAN , SAFRAN HELICOPTER ENGINES , SAFRAN POWER UNITS
CPC classification number: F01D15/10 , F01D21/00 , F05D2220/323 , F05D2220/76 , F05D2270/02
Abstract: This method for stopping at least one aircraft turbogenerator (1) comprises: —controlling the stopping (E1) of the turbogenerator (1); —passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); —controlling the extinction of the combustion chamber (6) of the gas turbine (2); —maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, —controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).
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公开(公告)号：US11855549B2
公开(公告)日：2023-12-26
申请号：US17594288
申请日：2020-03-20
Applicant: SAFRAN , SAFRAN ELECTRICAL & POWER , SAFRAN HELICOPTER ENGINES
Inventor： Garance Vinson , Florent Rougier , Stéphane Meyer Beddok
CPC classification number: H02M5/4585 , B60L50/15 , B64D27/24 , H02J3/36 , B60L2200/10 , B64D2027/026 , B64D2221/00 , H02J2310/44
Abstract: Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (VHVDC), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.
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公开(公告)号：US11235627B2
公开(公告)日：2022-02-01
申请号：US16759553
申请日：2018-10-16
Applicant: COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN , SAFRAN , SAFRAN LANDING SYSTEMS , SAFRAN ELECTRONICS & DEFFENSE
Inventor： Lionel Fagot-Revurat , Julien Destraves
Abstract: A system for measuring parameters of a mounted assembly comprises an electronic device for measuring parameters of the mounted assembly and a bonding interface made of elastomeric material surrounding the electronic device. The measuring electronic device comprises: a UHF radiofrequency antenna; and an electronic board with an electronic chip coupled to the UHF radiofrequency antenna, a sensor for measuring parameters of the mounted assembly, a microcontroller and an electrical circuit. The measuring system comprises a ground plane connected to the electronic board. The electronic board comprises an energy manager and a capacitive element. The coupling between the electronic chip and the UHF radiofrequency antenna is of an electrical nature. The electronic chip, the microcontroller and the measuring sensor are components of low energy consumption.
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