公开(公告)号：US20240282986A1

公开(公告)日：2024-08-22

申请号：US18565055

申请日：2022-05-31

申请人： SAFRAN POWER UNITS

发明人： Kilian Frank, Claude BERNARD ,  Robin Jacques, Marie VIALET ,  Olivier Rafaël, René CRASSOUS ,  Rémi André, Armand STEPHAN

IPC分类号： H01M8/04089 ,  H01M8/0444 ,  H01M8/04746

CPC分类号： H01M8/04104 ,  H01M8/04455 ,  H01M8/04753 ,  H01M8/04776 ,  H01M2250/20

摘要： Disclosed is a method for controlling a pressure regulating valve (6) for regulating the internal pressure (Pint) of a fluid circuit (3) in an electrochemical device (2), said fluid circuit (3) being fed by a compressor (4) drawing air at an external pressure (Pext) and compressing same at the internal pressure (Pint) according to a compression ratio (A); said method comprises a step of measuring the external pressure (Pext), determining an internal pressure set point (Pint*) on the basis of the external pressure (Pext) measured and the compression range (B), so as to promote overall efficiency (R1) of the electrochemical device (2) and the compressor (4) according to the internal pressure (Pint) and the compression ratio (A), and a step of controlling the pressure regulating valve (6) so as to reach the internal pressure set point (Pint*).

公开(公告)号：US12040519B2

公开(公告)日：2024-07-16

申请号：US17299134

申请日：2019-12-04

申请人： SAFRAN POWER UNITS

发明人： Romain Quinton ,  Jean-Baptiste Jollys ,  Théophile Horde

IPC分类号： H01M8/248 ,  H01M8/2483

CPC分类号： H01M8/248 ,  H01M8/2483

摘要： A fuel cell comprising a stack which comprises a plurality of cells, each cell comprising a plurality of fluid flow openings aligned in parallel to form a plurality of fluid flow lines in the stack, two end plates placed at the ends of the stack and at least one traction member connecting the end plates to each other in order to compress the stack, the traction member being mounted in a fluid flow line of the stack.

公开(公告)号：US20240200493A1

公开(公告)日：2024-06-20

申请号：US18565281

申请日：2022-06-30

申请人： SAFRAN POWER UNITS

发明人： Laurent Stéphane Tardy ,  Jaime Georges Paul Culla

IPC分类号： F02C7/045 ,  B64D33/02 ,  B64D41/00 ,  F02C3/08

CPC分类号： F02C7/045 ,  B64D33/02 ,  B64D41/00 ,  F02C3/08 ,  B64D2033/0206 ,  B64D2033/0213 ,  F05D2220/50 ,  F05D2260/96

摘要： The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.

公开(公告)号：US20240003261A1

公开(公告)日：2024-01-04

申请号：US18265021

申请日：2021-12-01

申请人： SAFRAN ,  SAFRAN HELICOPTER ENGINES ,  SAFRAN POWER UNITS

发明人： Fabien Mercier-Calvairac ,  Nicolas Claude Parmentier ,  Denis Antoine Julien Real

IPC分类号： F01D15/10 ,  F01D21/00

CPC分类号： F01D15/10 ,  F01D21/00 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2270/02

摘要： 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).

公开(公告)号：US10766629B2

公开(公告)日：2020-09-08

申请号：US15127747

申请日：2015-03-20

申请人： SAFRAN HELICOPTER ENGINES ,  SAFRAN POWER UNITS

发明人： Fabien Mercier-Calvairac ,  Stéphane Beddok ,  Stéphane Chevalier ,  Sophie Humbert

IPC分类号： F02C7/262 ,  B64D35/08 ,  B64C27/14 ,  F02C9/42 ,  F02C7/275 ,  B64D27/26 ,  F02C3/04 ,  F02C7/268 ,  B64D27/02

摘要： An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.

公开(公告)号：US10677165B2

公开(公告)日：2020-06-09

申请号：US15117904

申请日：2015-02-10

申请人： Safran Power Units

发明人： Amandine Roche

IPC分类号： F02C7/18 ,  F02C7/047 ,  F02C7/04 ,  F02C7/055

摘要： A heat exchange system in a turbomachine that comprises a plurality of members and equipment to be cooled and/or lubricated, the heat exchange system includes a fluid circuit for cooling and/or lubricating the equipment, the heat exchange system being configured to bring the fluid circuit in thermal contact with a fluid, wherein the heat exchange system further includes an open work structure which is in thermal contact with at least one hot section of the fluid circuit and through which the fluid passes.

公开(公告)号：US10450965B2

公开(公告)日：2019-10-22

申请号：US15691066

申请日：2017-08-30

申请人： Safran Power Units

发明人： Guylain Ozzello ,  Pascal Rolland

IPC分类号： F02C9/26 ,  F02C7/228 ,  F02C7/232 ,  F02C9/32

摘要： The invention relates to a fuel metering and distribution unit (10) which comprises in particular a slide valve (20) and a set of slots (41) configured with geometries, dimensions and positions such that: in a first range of displacement of the slide valve, the flow area (31) which feeds the outlet port of the start-up ramp is progressively opened with the displacement of the slide valve (20), while the area (41) of the set of slots which feeds the outlet port of the main ramp is closed, then, in a second range of displacement of the slide valve (20), the area (41) of the set of slots which feeds the outlet port (42) of the main ramp is progressively opened with the displacement of the slide valve, while the flow area (31) which feeds the outlet port of the start-up ramp is kept open, the outlet port (42) of the main ramp thus being able to receive a portion of the total metered flow rate at the flow area (31) feeding the outlet port of the start-up ramp.

公开(公告)号：US10266277B2

公开(公告)日：2019-04-23

申请号：US15039026

申请日：2014-11-25

申请人： MICROTURBO

发明人： Jean-Francoise Rideau ,  Stephane Vaillant

IPC分类号： B64D41/00 ,  B64D33/04 ,  H01M8/04014 ,  B64D33/02 ,  B64D13/02

摘要： The invention relates to a system (2) for generating non-propulsive energy in an aircraft, including: an auxiliary power unit (20) including a gas turbine (21) and a fuel cell (22); a pathway (23) for the intake of outside air into the aircraft; an exhaust pipe (24) of the gas turbine, the system being characterized in that the air intake pathway (23) includes a pipe (230) for cooling the fuel pipe, in that the pipe is in fluid communication with the exhaust pipe (24) of the gas turbine such that the ejection of the gas from the gas turbine into the exhaust pipe causes a suction of the air outside the aircraft into the cooling pipe (230) by Venturi effect. The invention also relates to a method for generating non-propulsive energy.

公开(公告)号：US20190044166A1

公开(公告)日：2019-02-07

申请号：US16072628

申请日：2017-01-26

申请人： SAFRAN POWER UNITS

发明人： Serge Daniel LE GONIDEC

IPC分类号： H01M8/04746 ,  H01M8/0438 ,  G05D16/20

摘要： A pressure regulator system (100) for regulating a pressure in a fluid line (16A) in such a manner that the pressure complies with a predetermined regulation criterion. The system comprises a valve (20A) that is controllable in on/off mode arranged at a downstream end of the line (16A) and suitable for oscillating between an open position and a closed position; a pressure sensor (40A) connected to the line (16A) and serving to measure the pressure in the line upstream from the valve (20A); and a regulator unit (50) configured to transmit to the valve (20A) open/close commands that are determined as a function of the measured pressure. A constant frequency imposes open periods (Oi) on the valve. The durations of the open periods are modulated in such a manner that the pressure in the line complies with said predetermined criterion.

公开(公告)号：US20180170564A1

公开(公告)日：2018-06-21

申请号：US15843573

申请日：2017-12-15

申请人： SAFRAN POWER UNITS ,  INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE

发明人： Stephane Richard Dominique Vaillant ,  Mickael Faucher ,  Christophe Turpin

IPC分类号： B64D27/24 ,  F02C7/08 ,  B64C27/22 ,  B64D13/06 ,  F02C7/32

CPC分类号： B64D27/24 ,  B64C27/22 ,  B64D13/06 ,  B64D2027/026 ,  B64D2041/002 ,  F01D15/10 ,  F02C3/00 ,  F02C3/04 ,  F02C7/08 ,  F02C7/32 ,  F05D2220/50 ,  F05D2220/76 ,  F05D2270/03

摘要： A unit (1′, 10′, 100′) for generating non-propulsive electrical power for use on board an aircraft, the unit (1′, 10′, 100′) comprising an electricity production device (3, 30) comprising a gas turbine (31) and an electricity generator (32) mechanically connected to an outlet shaft (33) of the gas turbine (31), said electricity generator (32) including output electrical connections (320) for being electrically connected to an electrical power supply network (2, 20, 200) on board an aircraft.The unit (1′, 10′, 100′) includes energy storage means (5) and regulator means (6) configured to control the speed of rotation of the gas turbine (31) as a function of the electrical power required by the on-board electrical power supply network (2, 20, 200).