Patents by Inventor Matthieu François Rullaud
Matthieu François Rullaud 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).
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Patent number: 10883720Abstract: A combustion chamber of a turbomachine includes an annular outer casing and a flame tube connected to the outer casing. The flame tube includes an annular inner wall and an annular outer wall defining a first, radial portion at the inlet of the flame tube and a second, axial portion at the outlet of the flame tube. The first portion extends towards the second portion forming an elbow between the inlet and the outlet of the flame tube.Type: GrantFiled: April 28, 2016Date of Patent: January 5, 2021Assignee: Safran Aircraft EnginesInventors: Guillaume Aurelien Godel, Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu Francois Rullaud
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Patent number: 10551064Abstract: An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.Type: GrantFiled: October 25, 2012Date of Patent: February 4, 2020Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINESInventors: Matthieu Francois Rullaud, Bernard Joseph Jean-Pierre Carrere, Hubert Pascal Verdier
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Patent number: 10488049Abstract: The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).Type: GrantFiled: September 29, 2015Date of Patent: November 26, 2019Assignee: Safran Aircraft EnginesInventors: Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu François Rullaud
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Patent number: 10180256Abstract: A combustion chamber for a turbine engine, including an annular end wall provided with injection systems each centered on a respective axis and each having an upstream end forming a bushing for receiving a head of a fuel injector, and an annular shroud covering the end wall and including injector ports respectively arranged facing the injection systems, wherein the annular shroud includes air intake ports separate from the injector ports, and the bushing of each injection system crosses the corresponding injector port and includes at its upstream end a collar having a free end remote from the axis of the injection system by a first distance greater than a second distance separating a rim of the injector port from the axis.Type: GrantFiled: September 29, 2014Date of Patent: January 15, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Francois Rullaud, Romain Nicolas Lunel, Thomas Olivier Marie Noel
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Publication number: 20180299132Abstract: A combustion chamber of a turbomachine includes an annular outer casing and a flame tube connected to the outer casing. The flame tube includes an annular inner wall and an annular outer wall defining a first, radial portion at the inlet of the flame tube and a second, axial portion at the outlet of the flame tube. The first portion extends towards the second portion forming an elbow between the inlet and the outlet of the flame tube.Type: ApplicationFiled: April 28, 2016Publication date: October 18, 2018Applicant: Safran Aircraft EnginesInventors: Guillaume Aurelien GODEL, Romain LUNEL, Thomas Olivier Marie NOEL, Matthieu Francois RULLAUD
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Patent number: 10036552Abstract: An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilize the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.Type: GrantFiled: March 14, 2014Date of Patent: July 31, 2018Assignees: SNECMA, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Matthieu Francois Rullaud, Didier Hernandez, Christian Guin
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Publication number: 20170299192Abstract: The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).Type: ApplicationFiled: September 29, 2015Publication date: October 19, 2017Applicant: Safran Aircraft EnginesInventors: Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu François Rullaud
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Patent number: 9551489Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.Type: GrantFiled: September 25, 2012Date of Patent: January 24, 2017Assignee: SNECMAInventors: Matthieu Francois Rullaud, Michel Pierre Cazalens
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Publication number: 20160281991Abstract: An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilise the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.Type: ApplicationFiled: March 14, 2014Publication date: September 29, 2016Applicants: SNECMA, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Matthieu Francois RULLAUD, Didier HERNANDEZ, Christian GUIN
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Publication number: 20160215983Abstract: A combustion chamber for a turbine engine, including an annular end wall provided with injection systems each centred on a respective axis and each having an upstream end forming a bushing for receiving a head of a fuel injector, and an annular shroud covering the end wall and including injector ports respectively arranged facing the injection systems, wherein the annular shroud includes air intake ports separate from the injector ports, and the bushing of each injection system crosses the corresponding injector port and includes at its upstream end a collar having a free end remote from the axis of the injection system by a first distance greater than a second distance separating a rim of the injector port from the axis.Type: ApplicationFiled: September 29, 2014Publication date: July 28, 2016Applicant: SNECMAInventors: Matthieu Francois RULLAUD, Romain Nicolas LUNEL, Thomas Olivier, Marie NOEL
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Patent number: 9360218Abstract: A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.Type: GrantFiled: September 27, 2013Date of Patent: June 7, 2016Assignee: SNECMAInventors: Matthieu Francois Rullaud, Galadriel Dancie, Romain Nicolas Lunel, Thomas Olivier Marie Noel
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Patent number: 9303876Abstract: An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel.Type: GrantFiled: February 24, 2011Date of Patent: April 5, 2016Assignee: SNECMAInventors: Didier Hippolyte Hernandez, Thomas Olivier Marie Noel, Matthieu Francois Rullaud
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Patent number: 8955326Abstract: In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.Type: GrantFiled: May 18, 2010Date of Patent: February 17, 2015Assignee: SNECMAInventors: Sébastien Alain Christophe Bourgois, Didier Hippolyte Hernandez, Matthieu François Rullaud
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Publication number: 20140260257Abstract: An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.Type: ApplicationFiled: October 25, 2012Publication date: September 18, 2014Applicants: SNECMA, TURBOMECAInventors: Matthieu Francois Rullaud, Bernard Joseph, Jean-Pierre Carrere, Hurbert Pascal Verdier
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Publication number: 20140223912Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.Type: ApplicationFiled: September 25, 2012Publication date: August 14, 2014Applicant: SNECMAInventors: Matthieu Francois Rullaud, Michel Pierre Cazalens
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Publication number: 20140090381Abstract: A fuel injection device (110) for a turbine engine, the device comprising a pilot injector opening out into a venturi (120) and an annular row of multipoint injection orifices (136) opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall (140), the device being characterized in that the outer peripheral edge (142) of the separation wall has a diameter (B?) greater than the diameter of the annular row (A) of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.Type: ApplicationFiled: September 27, 2013Publication date: April 3, 2014Applicant: SNECMAInventors: Matthieu Francois RULLAUD, Galadriel DANCIE, Romain Nicolas LUNEL, Thomas Olivier, Marie NOEL
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Publication number: 20120304650Abstract: An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel.Type: ApplicationFiled: February 24, 2011Publication date: December 6, 2012Applicant: SNECMAInventors: Didier Hippolyte Hernandez, Thomas Oliver Marie Noel, Matthieu Francois Rullaud
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Publication number: 20120047899Abstract: In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.Type: ApplicationFiled: May 18, 2010Publication date: March 1, 2012Applicant: SNECMAInventors: Sébastien Alain Christophe Bourgois, Didier Hippolyte Hernandez, Matthieu François Rullaud