Patents by Inventor Pascal Laurent
Pascal Laurent 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: 11891958Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (O1) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.Type: GrantFiled: May 15, 2020Date of Patent: February 6, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Jean Fernand Deneuve, Jérôme Pascal Laurent Patrick Tronche
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Patent number: 11480110Abstract: The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closing the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined from the static angle, corresponding to the fact that the joint (J1) remains compressed and seals the closing of the orifice (O1), the dead zone is recorded and the signal (SC1) for controlling the actuator (V1) is generated by the computer as a function of the dead zone.Type: GrantFiled: May 15, 2020Date of Patent: October 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Jean Fernand Deneuve, Jérôme Pascal Laurent Patrick Tronche
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Publication number: 20220260023Abstract: The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closing the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined from the static angle, corresponding to the fact that the joint (J1) remains compressed and seals the closing of the orifice (O1), the dead zone is recorded and the signal (SC1) for controlling the actuator (V1) is generated by the computer as a function of the dead zone.Type: ApplicationFiled: May 15, 2020Publication date: August 18, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Jean Fernand DENEUVE, Jérôme Pascal Laurent Patri TRONCHE
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Publication number: 20220213841Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (01) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.Type: ApplicationFiled: May 15, 2020Publication date: July 7, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Jean Fernand DENEUVE, Jérôme Pascal Laurent Patri TRONCHE
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Patent number: 11066940Abstract: A turbine engine assembly includes a rotor disk extending around an axis A, a sealing flange centered on the axis A, the flange including a radially external portion that can come into contact with a face axially opposite the rotor disk in order to provide the tightness and a radially internal portion including a groove open axially towards the rotor disk and including a ring which is received in the groove of the flange and which is received in the groove of the flange. The ring includes at least one protruding tappet that is received in a notch formed in the flange.Type: GrantFiled: February 13, 2020Date of Patent: July 20, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Pascal Laurent Jean Robert Allouis, Sebastien Georges Roger Goux
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Publication number: 20200263556Abstract: A turbine engine assembly includes a rotor disk extending around an axis A, a sealing flange centered on the axis A, the flange including a radially external portion that can come into contact with a face axially opposite the rotor disk in order to provide the tightness and a radially internal portion including a groove open axially towards the rotor disk and including a ring which is received in the groove of the flange and which is received in the groove of the flange. The ring includes at least one protruding tappet that is received in a notch formed in the flange.Type: ApplicationFiled: February 13, 2020Publication date: August 20, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christophe Pascal Laurent Jean Robert ALLOUIS, Sebastien Georges Roger GOUX
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Patent number: 9091217Abstract: High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.Type: GrantFiled: April 15, 2010Date of Patent: July 28, 2015Assignee: SNECMAInventors: Laurent Gilbert Yves Hodinot, Celine Marie Anne Issert, Pascal Laurent Marly
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Publication number: 20120042657Abstract: High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.Type: ApplicationFiled: April 15, 2010Publication date: February 23, 2012Applicant: SNECMAInventors: Laurent Gilbert Yves Hodinot, Celine Marie Anne Issert, Pascal Laurent
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Patent number: 6547185Abstract: In a door closing procedure, an aircraft passenger door is pivoted from an open position to a pivoted-in position, shifted to a closed position, locked into a locked condition, and then secured into a secured locked condition. A control method and arrangement for controlling the closing procedure includes sensors that respectively each sense the completion of a respective allocated one of the steps of the closing procedure, and then responsively initiate the next following step of the procedure. The closing procedure is carried out in an automatic sequential step-wise manner using a simple robust arrangement, without requiring a computer control.Type: GrantFiled: July 31, 2001Date of Patent: April 15, 2003Assignee: Eurocopter Deutschland GmbHInventors: Hannes Erben, Pascal Laurent
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Publication number: 20020014557Abstract: In a door closing procedure, an aircraft passenger door is pivoted from an open position to a pivoted-in position, shifted to a closed position, locked into a locked condition, and then secured into a secured locked condition. A control method and arrangement for controlling the closing procedure includes sensors that respectively each sense the completion of a respective allocated one of the steps of the closing procedure, and then responsively initiate the next following step of the procedure. The closing procedure is carried out in an automatic sequential step-wise manner using a simple robust arrangement, without requiring a computer control.Type: ApplicationFiled: July 31, 2001Publication date: February 7, 2002Inventors: Hannes Erben, Pascal Laurent