Patents by Inventor Francois Danguy

Francois Danguy has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11359545
    Abstract: A pyrotechnic device comprising a main pyrotechnic charge, a firing device for firing the main pyrotechnic charge, a discharge passage for discharging the gas generated by firing the main pyrotechnic charge, and an injector device configured to inject a cooling fluid into said gas discharge passage, so as to deliver gas, specifically for driving turbines, at temperatures that are relatively low, and a method of cooling gas generated by firing the main pyrotechnic charge by injecting the cooling fluid.
    Type: Grant
    Filed: November 17, 2017
    Date of Patent: June 14, 2022
    Assignee: Safran Helicopter Engines
    Inventors: François Danguy, Laurent Paul Lattanzio Fabbri, Romain Maurice Henri Yannick Gauthier, Didier Paul Saucereau
  • Publication number: 20190285001
    Abstract: A pyrotechnic device comprising a main pyrotechnic charge, a firing device for firing the main pyrotechnic charge, a discharge passage for discharging the gas generated by firing the main pyrotechnic charge, and an injector device configured to inject a cooling fluid into said gas discharge passage, so as to deliver gas, specifically for driving turbines, at temperatures that are relatively low, and a method of cooling gas generated by firing the main pyrotechnic charge by injecting the cooling fluid.
    Type: Application
    Filed: November 17, 2017
    Publication date: September 19, 2019
    Applicant: Safran Helicopter Engines
    Inventors: François DANGUY, Laurent Paul Lattanzio FABBRI, Romain Maurice Henri Yannick GAUTHIER, Didier Paul SAUCEREAU
  • Patent number: 10167874
    Abstract: The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a).
    Type: Grant
    Filed: July 11, 2014
    Date of Patent: January 1, 2019
    Assignee: Arianegroup SAS
    Inventors: François Danguy, Jean-Michel Nguyen Duc, Laurent Fabbri, Cëdric Sene
  • Patent number: 9951694
    Abstract: An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: April 24, 2018
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Patrick Marconi, Camel Serghine, Antoine Marie Georges Caratge, Francois Danguy, Laurent Fabbri, Pierre Yvart, Laurent Soulie, Philippe Barrat
  • Publication number: 20170114723
    Abstract: The invention relates to a device for assisting a propulsion system of a single-engine helicopter, comprising an engine connected to a power transmission gearbox (15) suitable for rotating a rotor (88) of the helicopter, characterised in that it comprises: a turbine (18) for driving in rotation an output shaft (34) that is mechanically connected to said power transmission gearbox (15); and controlled means (16) for supplying said drive turbine (18) with pressurised fluid in order to allow said turbine (18) to transform the power from said pressurised fluid into mechanical power for rotating said output shaft (34).
    Type: Application
    Filed: April 3, 2015
    Publication date: April 27, 2017
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine, Francois Danguy, Philippe Barrat, Jean-Louis Besse, Pascal Guillemet, Guillaume Demezon, Jean-Michel Sannino, Nicolas Marucheau De Chanaud
  • Publication number: 20160281641
    Abstract: The invention relates to the field of rocket engines, and more particularly to a propulsion assembly (10) comprising a first tank (11) for a first liquid propellant, a second tank (12) for a second liquid propellant, a pressurizer device (60) configured to maintain a substantially higher pressure in the second tank (12) than in the first tank (11), and a single-shaft turbopump (30) comprising a turbine (33), a first pump (31), and a second pump (32). The turbine (33) is actuated by expansion of the first propellant after it has passed through a regenerative heat exchanger (44), and in turn it acts via the single rotary shaft (34) of the turbopump (30) to drive said first and second pumps (31, 32) respectively pumping said first and second propellants in order to feed a propulsion chamber (40).
    Type: Application
    Filed: November 5, 2014
    Publication date: September 29, 2016
    Applicant: SNECMA
    Inventors: François DANGUY, David HAYOUN, Jean Michel SANNINO
  • Patent number: 9435347
    Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: September 6, 2016
    Assignee: SNECMA
    Inventors: Francois Danguy, Laurent Fabbri, Sebastien Guingo
  • Publication number: 20160230672
    Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.
    Type: Application
    Filed: September 12, 2014
    Publication date: August 11, 2016
    Inventors: Romain Thiriet, Patrick Marconi, Camel Serghine, Antoine Marie Georges Caratge, Francois Danguy, Laurent Fabbri, Pierre Yvart, Laurent Soulie, Philippe Barrat
  • Publication number: 20160195039
    Abstract: A device (10A, 10B) for feeding a rocket engine with propellant, the device comprising at least one propellant tank (10, 11), a combustion chamber (18), and a feed pipe (12, 13) extending from the tank (10, 11) to the combustion chamber (18) to feed propellant to the combustion chamber. A valve (14, 15) and a main pump (16, 17) are arranged in succession along the feed pipe. The rocket engine device further comprises at least one branch pump (20, 21, 120, 220) making a branch connection to the tank upstream from the valve in order to feed an auxiliary pipe (22, 23, 122, 222) that serves an auxiliary function of the rocket engine.
    Type: Application
    Filed: August 4, 2014
    Publication date: July 7, 2016
    Applicant: SNECMA
    Inventors: François DANGUY, Alban LEMAITRE, Laurent FABBRI, Vincent PENDARIES
  • Publication number: 20160177963
    Abstract: The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a).
    Type: Application
    Filed: July 11, 2014
    Publication date: June 23, 2016
    Applicant: SNECMA
    Inventors: François DANGUY, Jean-Michel NGUYEN DUC, Laurent FABBRI, Cédric SENE
  • Patent number: 9341315
    Abstract: A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.
    Type: Grant
    Filed: December 7, 2012
    Date of Patent: May 17, 2016
    Assignee: SNECMA
    Inventors: David Hayoun, Francois Danguy, Jean Michel Sannino, Pascal Marcel Jean Noir
  • Publication number: 20150000755
    Abstract: A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.
    Type: Application
    Filed: December 7, 2012
    Publication date: January 1, 2015
    Applicant: SNECMA
    Inventors: David Hayoun, Francois Danguy, Jean Michel Sannino, Pascal Marcel, Jean Noir
  • Publication number: 20130227931
    Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.
    Type: Application
    Filed: August 31, 2011
    Publication date: September 5, 2013
    Applicant: Snecma
    Inventors: Francois Danguy, Laurent Fabbri, Sebastien Guingo
  • Patent number: 8333548
    Abstract: A turbomachine arranged with a rotor and a stator, including a radial positioning device ensuring that the rotor is radially positioned; and a contactless axial balancing device arranged on at least one bladed wheel for axially balancing the rotor at high speed. The turbomachine includes a thrust bearing distinct from the radial positioning device serving to balance the rotor axially at low speed, and without contact at high speed. In addition, the radial positioning device is constituted by hydrostatic bearings, the turbomachine including hydrostatic bearing feed circuits suitable for connecting the bearings to a source of fluid under pressure. As a result, it is possible to obtain operation at high speeds with a very long lifetime.
    Type: Grant
    Filed: June 16, 2009
    Date of Patent: December 18, 2012
    Assignee: Snecma
    Inventors: Valérie Begin, Frédéric Boudehen, François Danguy, Manuel Frocot
  • Publication number: 20120051885
    Abstract: The invention relates to a centrifugal pump.
    Type: Application
    Filed: May 7, 2010
    Publication date: March 1, 2012
    Inventors: Francois Danguy, Emmanuel Edeline, Laurent Fabbri
  • Patent number: 7686572
    Abstract: A pump for the drawing-in of a fluid, including at least one centrifugal wheel having a fluid inlet edge and a fluid outlet edge, the pump further including an axial balancing system with a high-pressure flow space defined between the housing and an upstream face of the centrifugal wheel. The axial balancing system further includes a device for substantially increasing the hydrostatic pressure of the fluid circulating in the high-pressure flow space during operation of the pump.
    Type: Grant
    Filed: October 13, 2006
    Date of Patent: March 30, 2010
    Assignee: SNECMA
    Inventors: Fabien Wahl, Francois Danguy, Stephane Laffite, Philippe Bourdin
  • Publication number: 20090311089
    Abstract: A turbomachine arranged with a rotor and a stator, including radial positioning means ensuring that the rotor is radially position; and a contactless axial balancing device arranged on at least one bladed wheel for axially balancing the rotor at high speed. The turbomachine includes a thrust bearing distinct from the radial positioning means serving to balance the rotor axially at low speed, and without contact at high speed. In addition, the radial positioning means are hydrostatic bearings, the turbomachine including hydrostatic bearing feed circuits suitable for connecting said bearings to a source of fluid under pressure. As a result, it is possible to obtain operation at high speeds with a very long lifetime.
    Type: Application
    Filed: June 16, 2009
    Publication date: December 17, 2009
    Applicant: SNECMA
    Inventors: Valerie Begin, Frederic Boudehen, Francois Danguy, Manuel Frocot
  • Publication number: 20080267763
    Abstract: The invention relates to a rotary machine for passing a main liquid stream, the machine comprising: a shaft mounted to rotate relative to a casing of the rotary machine; and an active axial balancing system suitable for exerting a first axial take-up force on the shaft. The invention further comprising a circuit for a secondary liquid stream taken from the main liquid stream, and a passive axial balancing system suitable for exerting a second axial take-up force on the shaft, said passive axial balancing system being fed by the circuit for the secondary liquid stream.
    Type: Application
    Filed: June 11, 2007
    Publication date: October 30, 2008
    Inventors: Fabien Wahl, Laurent Fabbri, Francois Danguy
  • Patent number: 7406830
    Abstract: The compressor-evaporator system for liquefied gas contained in a tank comprises, in addition to a deice for evaporation by heat exchange with a liquid and devices for conditioning and transferring gas to a pipeline, a motor-driven turbopump comprising a rotary assembly of high bending stiffness on a common shaft line, with at least one high pressure pump, a turbine, and a central electrical machine capable of being used in motor mode or in generator mode. The rotary assembly of the motor-driven turbopump is adapted to present a high speed of rotation, greater than 12,000 rpm, while remaining outside ranges for exciting critical speeds in rotation. All of the internal portions of the motor-driven turbopump are immersed in a cryogenic fluid that is the same as the liquefied gas contained in the tank. The internal cavities of the motor-driven turbopump that are under different thermodynamic conditions are separated by contactless dynamic seals.
    Type: Grant
    Filed: December 16, 2005
    Date of Patent: August 5, 2008
    Assignee: Snecma
    Inventors: Dominique Valentian, Damien Feger, Noël Marchal, François Danguy, Olivier Lagnel
  • Publication number: 20080080965
    Abstract: The invention relates to a pump (10) for the drawing-in of a fluid, comprising at least one centrifugal wheel (14) having a fluid inlet edge (48) and a fluid outlet edge (44), the pump further comprising an axial balancing system (32) comprising a high-pressure flow space (34) defined between the housing and an upstream face (36) of the centrifugal wheel (14). The invention is characterised by the fact that the axial balancing system (32) further comprises means (52) for substantially increasing the hydrostatic pressure of the fluid circulating in the high-pressure flow space (34) during operation of the pump (10).
    Type: Application
    Filed: October 13, 2006
    Publication date: April 3, 2008
    Applicant: SNECMA
    Inventors: Fabien Wahl, Francois Danguy, Stephane Laffite, Philippe Bourdin