Patents by Inventor Loic Pora
Loic Pora 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: 11927141Abstract: The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: —a fuel inlet (E), —a metering device (FMV) and a cut-off device (HPSOV) arranged in series, —an adjustment valve (VR) arranged on a fuel recirculation branch, such that any excess fuel supplied by the pumping system is fed back into the fuel circuit, wherein at least one flow-metric sensor (WFM1) is arranged on the recirculation branch, a density value for the metered fuel is determined according to the sensor measurements and the metering device is controlled according to the fuel density value thus determined.Type: GrantFiled: July 3, 2020Date of Patent: March 12, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Arnaud Bernard Clément Thomas Joudareff, Loïc Pora
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Patent number: 11920606Abstract: Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.Type: GrantFiled: July 16, 2021Date of Patent: March 5, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Petar Dimitrov Tomov, Loïc Pora, Sébastien Christophe Loval
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Patent number: 11905885Abstract: A fuel supply circuit including a supply duct in which a first flow (Fl) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (Fl), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.Type: GrantFiled: October 5, 2021Date of Patent: February 20, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Kevin Didier Pierre Le Normand, Frederic Brettes, Loic Pora
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Patent number: 11867076Abstract: The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).Type: GrantFiled: May 18, 2020Date of Patent: January 9, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Loic Pora, Huguette De Wergifosse
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Publication number: 20230407792Abstract: A fuel supply circuit including a supply duct in which a first flow (F1) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (F1), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.Type: ApplicationFiled: October 5, 2021Publication date: December 21, 2023Inventors: Kevin Didier Pierre LE NORMAND, Frederic BRETTES, Loic PORA
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Publication number: 20230392550Abstract: A device for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbo machine, in particular of an aircraft, the device including a rotating main body extending about a longitudinal axis, the main body including an internal flow duct for a first flow of fuel, extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second flow of fuel, and including at least one orifice for the second flow of fuel to pass through, and an external annular groove in fluidic communication with the at least one orifice in the first portion.Type: ApplicationFiled: October 5, 2021Publication date: December 7, 2023Inventors: Kevin Didier Pierre LE NORMAND, Frederic BRETTES, Loic PORA
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Patent number: 11815034Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, the system includes a pump, a hydromechanical group, a drive device positioned to drive the pump, and a branch comprising actuators for controlling variable geometry. In some embodiments, the system regulates a fuel flow rate based at least in part on a flow rate set point value. In some embodiments, the system may include a flow rate sensor. A flow rate loop may be arranged to determine a pressure set point value at the outlet of the pump according to the flow rate set point value and a measurement supplied by the flow rate sensor. In some embodiments, a pressure sensor may be positioned in the fuel circuit at the outlet of the pump. In further embodiments, a pressure loop may control the speed of the drive device based at least on a difference between a pressure measurement supplied by the pressure sensor and the pressure set point value.Type: GrantFiled: January 30, 2018Date of Patent: November 14, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Huguette De Wergifosse, Loïc Pora, Eric De Wergifosse
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Publication number: 20230279867Abstract: Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.Type: ApplicationFiled: July 16, 2021Publication date: September 7, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Petar Dimitrov TOMOV, Loïc PORA, Sébastien Christophe LOVAL
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Patent number: 11691751Abstract: An accumulator designed to damp the pressure waves of the hydraulic shocks originating in a downstream section of a duct is arranged inside the duct, with the opening of the accumulator pointing downstream. This results in excellent absorption of the pressure wave and protection of the circuit from possible accumulations of air, water or ice, there being no areas where the flow stagnates. Immersing the accumulator in the flow also makes it possible to ensure that the equipment is protected in the event of a fire.Type: GrantFiled: December 15, 2017Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventor: Loic Pora
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Patent number: 11561147Abstract: Device (1) for testing a hydraulic part (10) for a turbomachine, the device comprising a closed loop for circulation of a working fluid, the loop comprising at least one recirculation pump (7) configured to circulate the working fluid in the loop according to a direction of circulation, at least one valve (4) for regulating the flow rate of a working fluid, at least one reservoir (A) configured to store the working fluid, a test section (2) configured to accommodate the hydraulic part (10), the device (1) further comprising a gas injection means (8) configured to inject and dissolve, at atmospheric pressure, a gas in the working fluid stored in the reservoir (A).Type: GrantFiled: May 15, 2020Date of Patent: January 24, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Loïc Pora, Petar Tomov, Théodore Magne
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Publication number: 20220268217Abstract: The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: —a fuel inlet (E), —a metering device (FMV) and a cut-off device (HPSOV) arranged in series, —an adjustment valve (VR) arranged on a fuel recirculation branch, such that any excess fuel supplied by the pumping system is fed back into the fuel circuit, wherein at least one flow-metric sensor (WFM1) is arranged on the recirculation branch, a density value for the metered fuel is determined according to the sensor measurements and the metering device is controlled according to the fuel density value thus determined.Type: ApplicationFiled: July 3, 2020Publication date: August 25, 2022Applicant: Safran Aircraft EnginesInventors: Arnaud Bernard Clément Thomas JOUDAREFF, Loïc PORA
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Publication number: 20220213806Abstract: The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).Type: ApplicationFiled: May 18, 2020Publication date: July 7, 2022Inventors: Loic PORA, Huguette DE WERGIFOSSE
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Publication number: 20220195926Abstract: The invention relates to a fuel supply system of a turbomachine, including a fuel circuit having a pressurizing means at the outlet of the circuit, a pump arranged to send a flow of fuel into the circuit, and a flow sensor placed in a fuel supply duct between an outlet of the pump and the pressurizing means. The fuel circuit includes a device for regulating a flow cross section between the pump and the flow sensor, the device being activated by control means, the shaft of the pump being associated with detection means recording a speed of rotation of the shaft, and, if these detection means record a speed of rotation above a variable predetermined threshold, the regulating device is activated in order to reduce the flow sent to the flow sensor.Type: ApplicationFiled: May 20, 2020Publication date: June 23, 2022Inventors: Loic PORA, Huguette DE WERGIFOSSE
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Patent number: 11365692Abstract: A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit.Type: GrantFiled: July 13, 2018Date of Patent: June 21, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Loic Pora, Arnaud Bernard Clement Thomas Joudareff
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Patent number: 11105271Abstract: A circuit for metering fuel for a turbomachine, including a fuel metering element, a pump designed to pump a flow of fuel to the metering element, and a control valve designed to return, toward the pump, an excess flow of fuel delivered to the metering element as a function of a fuel pressure difference at the terminals of the metering element, the control valve is designed to modulate the excess flow returned toward the pump as a function of variations in the density of the fuel delivered to the metering element. A turbomachine can include such a circuit.Type: GrantFiled: June 27, 2017Date of Patent: August 31, 2021Assignee: Safran Aircraft EnginesInventor: Loic Pora
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Publication number: 20210087980Abstract: A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit.Type: ApplicationFiled: July 13, 2018Publication date: March 25, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Loic PORA, Arnaud Bernard Clement Thomas JOUDAREFF
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Publication number: 20200363280Abstract: Device (1) for testing a hydraulic part (10) for a turbomachine, the device comprising a closed loop for circulation of a working fluid, the loop comprising at least one recirculation pump (7) configured to circulate the working fluid in the loop according to a direction of circulation, at least one valve (4) for regulating the flow rate of a working fluid, at least one reservoir (A) configured to store the working fluid, a test section (2) configured to accommodate the hydraulic part (10), the device (1) further comprising a gas injection means (8) configured to inject and dissolve, at atmospheric pressure, a gas in the working fluid stored in the reservoir (A).Type: ApplicationFiled: May 15, 2020Publication date: November 19, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Loïc PORA, Petar TOMOV, Théodore MAGNE
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Patent number: 10760696Abstract: A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.Type: GrantFiled: April 20, 2017Date of Patent: September 1, 2020Assignee: Safran Aircraft EnginesInventors: Clement Bernard, Loic Pora, Christophe Cebille
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Patent number: 10690264Abstract: A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.Type: GrantFiled: April 20, 2017Date of Patent: June 23, 2020Assignee: Safran Aircraft EnginesInventors: Clement Bernard, Loic Pora, Christophe Cebille
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Publication number: 20200003123Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, a fuel circuit includes a pressurisation valve at an outlet of the system and a pump. The circuit may include a flow rate sensor arranged between the outlet of the pump and the pressurisation valve. In some embodiments, the flow rate sensor may include a sliding drawer, a restoring spring, and a sensor for detecting the position of said drawer in order to indicate the flow passing through the flow rate sensor. The system may include a device arranged to drive the pump with a controllable rotational speed and a control configured to control the device on the basis of a measurement supplied by the flow rate sensor, in such a way as to adapt the rotational speed of the pump shaft.Type: ApplicationFiled: January 29, 2018Publication date: January 2, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Loïc Pora, Huguette De Wergifosse