Patents by Inventor Nicolas Raimarckers
Nicolas Raimarckers 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: 11530643Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.Type: GrantFiled: October 3, 2019Date of Patent: December 20, 2022Assignee: SAFRAN AERO BOOSTERS S.A.Inventors: Nicolas Raimarckers, Maxime Dumont, Rafael Perez, Frédéric Vallino
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Patent number: 11408907Abstract: A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient ? of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient ? on the basis of the measurement of the temperature of the gas stream.Type: GrantFiled: February 7, 2020Date of Patent: August 9, 2022Assignee: SAFRAN AERO BOOSTERS SAInventors: Nicolas Raimarckers, Frédéric Vallino
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Patent number: 11261755Abstract: System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil. The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil. The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.Type: GrantFiled: April 18, 2019Date of Patent: March 1, 2022Assignee: SAFRAN AERO BOOSTERS SAInventors: Albert Cornet, Nicolas Raimarckers
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Patent number: 10907488Abstract: The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.Type: GrantFiled: November 8, 2017Date of Patent: February 2, 2021Assignee: SAFRAN AERO BOOSTERS SAInventors: Olivier De Vriendt, Nicolas Raimarckers
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Patent number: 10773810Abstract: An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.Type: GrantFiled: May 14, 2018Date of Patent: September 15, 2020Assignee: SAFRAN AERO BOOSTERS SAInventor: Nicolas Raimarckers
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Publication number: 20200256887Abstract: A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient ? of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient ? on the basis of the measurement of the temperature of the gas stream.Type: ApplicationFiled: February 7, 2020Publication date: August 13, 2020Applicant: SAFRAN AERO BOOSTERS SAInventors: Nicolas Raimarckers, Frédéric Vallino
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Patent number: 10676215Abstract: A jet engine includes an external cowling, a member such as an oil reservoir, and a monitoring system for the member that is able to determine information relating to the member. The external cowling includes a visualization screen that is able to communicate with the monitoring system or directly with the member, so as to display the information specific to the member. When installed in the nacelle of the jet engine, this cowling becomes a smart cowling. The system also includes a method for inspecting a member of an aircraft jet engine and a corresponding computer program.Type: GrantFiled: March 22, 2018Date of Patent: June 9, 2020Assignee: SAFRAN AERO BOOSTERS SAInventor: Nicolas Raimarckers
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Publication number: 20200149430Abstract: System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil. The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil. The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.Type: ApplicationFiled: April 18, 2019Publication date: May 14, 2020Applicant: SAFRAN AERO BOOSTERS SAInventors: Albert Cornet, Nicolas Raimarckers
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Publication number: 20200109661Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.Type: ApplicationFiled: October 3, 2019Publication date: April 9, 2020Applicant: Safran Aero Boosters S.A.Inventors: Nicolas Raimarckers, Maxime Dumont, Rafael Perez, Frédéric Vallino
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Publication number: 20200088600Abstract: A measuring system for a turbine engine includes a piezoresistive sensor and an analysis module, the sensor and the module being such that the module can determine, from measuring two electrical voltages, a pressure value (p) and a temperature value (T) in the vicinity of the sensor. The sensor can include a Wheatstone bridge arranged on a flexible membrane.Type: ApplicationFiled: September 17, 2019Publication date: March 19, 2020Applicant: SAFRAN AERO BOOSTERS SAInventors: Nicolas Raimarckers, Frederic Vallino
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Publication number: 20200080433Abstract: The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.Type: ApplicationFiled: November 8, 2017Publication date: March 12, 2020Applicant: SAFRAN AERO BOOSTERS SAInventors: Olivier De Vriendt, Nicolas Raimarckers
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Patent number: 10393314Abstract: An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.Type: GrantFiled: July 7, 2017Date of Patent: August 27, 2019Assignee: Safran Aero Boosters SAInventors: Nicolas Raimarckers, Frederic Vallino, Giuseppe Giordano
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Patent number: 10226651Abstract: A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.Type: GrantFiled: January 26, 2017Date of Patent: March 12, 2019Assignee: Safran Aero Boosters SAInventors: Nicolas Raimarckers, Gaetano Taccogna
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Publication number: 20180346134Abstract: An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.Type: ApplicationFiled: May 14, 2018Publication date: December 6, 2018Inventor: Nicolas Raimarckers
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Publication number: 20180273210Abstract: A jet engine includes an external cowling, a member such as an oil reservoir, and a monitoring system for the member that is able to determine information relating to the member. The external cowling includes a visualization screen that is able to communicate with the monitoring system or directly with the member, so as to display the information specific to the member. When installed in the nacelle of the jet engine, this cowling becomes a smart cowling. The system also includes a method for inspecting a member of an aircraft jet engine and a corresponding computer program.Type: ApplicationFiled: March 22, 2018Publication date: September 27, 2018Applicant: SAFRAN AERO BOOSTERS SAInventor: Nicolas Raimarckers
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Publication number: 20180045367Abstract: An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.Type: ApplicationFiled: July 7, 2017Publication date: February 15, 2018Inventors: Nicolas Raimarckers, Frederic Vallino, Giuseppe Giordano
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Publication number: 20170216637Abstract: A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.Type: ApplicationFiled: January 26, 2017Publication date: August 3, 2017Inventors: Nicolas Raimarckers, Gaetano Taccogna
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Publication number: 20170211412Abstract: System for maintaining a turbine engine comprising said turbine engine of an aircraft comprising: an oil reservoir, a sensor able to measure an oil level in the oil reservoir, a transmission device, such as electrical wires, wireless transmitter circuit, etc., for transmitting a signal coupled to said sensor in order to transmit information relating to an oil level measured by said sensor, communication means, such as a display or a near field communications circuit coupled to said transmission devices, for communicating to the outside of the aircraft information representing an oil level measured by said sensor. The maintenance system further comprises a mobile apparatus able to communicate with said communication means and comprising a display for displaying said information representing an oil level to an operator situated on the ground outside the aircraft.Type: ApplicationFiled: January 19, 2017Publication date: July 27, 2017Applicant: SAFRAN AERO BOOSTERS S.A.Inventors: Nicolas Raimarckers, Vincent Thomas, Bruno Servais
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Patent number: 8967958Abstract: A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.Type: GrantFiled: December 17, 2010Date of Patent: March 3, 2015Assignee: Techspace Aero S.A.Inventors: Denis Bajusz, David Depaepe, Jacques Charlier, Nicolas Raimarckers
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Publication number: 20140331639Abstract: The present application relates an oil feed system for a turbomachine having a tank designed to contain a volume of oil, a pump designed to suck the oil from the tank and discharge it to at least one device on the turbomachine, and an anti-siphon valve designed to prevent the flow of oil to the device or devices. The anti-siphon valve is located upstream of the pump and is designed to allow the flow of oil when the speed of the pump becomes higher than a speed R1. The present application also relates to a turbojet fitted with a fan and two anti-siphon valves designed to open at different rotational speeds of the first pump.Type: ApplicationFiled: May 10, 2014Publication date: November 13, 2014Applicant: Techspace Aero S.A.Inventors: Nicolas Raimarckers, Albert Cornet