Patents by Inventor Philippe Galozio
Philippe Galozio 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: 8549863Abstract: A fuel supply device includes a fuel supply pipe receiving fuel at a non-regulated pressure delivered by a pump, a device for measuring the flow rate of fuel in the pipe, a first controlled variable-restriction valve mounted in the supply pipe, a control system connected to the flow rate measurement device and to the first valve to control the valve to deliver fuel to the engine at a desired flow rate under normal operating conditions of the engine, a second controlled variable-restriction valve mounted in the supply pipe in series with the first valve, and a control for controlling the second valve to enable the engine to be supplied with fuel at an adjustable, reduced flow rate in response to detecting over-speed or over-thrust of the engine.Type: GrantFiled: February 17, 2006Date of Patent: October 8, 2013Assignee: SNECMAInventors: Jean-Marie Brocard, Regis Deldalle, Philippe Galozio, Michel Martini, Alain Varizat
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Patent number: 8205597Abstract: A centrifugal pump driven by mechanical coupling with an engine has a low pressure inlet receiving fuel from a fuel circuit of an aircraft, a high pressure outlet connected to a regulator circuit for regulating the flow rate of fuel supplied to the engine, and an assistance pump unit that is electrically controlled, having an inlet connected to the aircraft fuel circuit and an outlet connected to the flow rate regulator circuit so as to deliver, via its outlet, fuel that is at a predetermined minimum pressure, the pressure of the fuel supplied to the regulator circuit being the higher of the pressures delivered by the centrifugal pump and the assistance pump unit.Type: GrantFiled: February 17, 2006Date of Patent: June 26, 2012Assignee: SNECMAInventors: Jean-Marie Brocard, Regis Michel Paul Deldalle, Philippe Galozio, Michel Martini, Alain Michel Varizat
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Publication number: 20110139123Abstract: A centrifugal pump driven by mechanical coupling with an engine has a low pressure inlet receiving fuel from a fuel circuit of an aircraft, a high pressure outlet connected to a regulator circuit for regulating the flow rate of fuel supplied to the engine, and an assistance pump unit that is electrically controlled, having an inlet connected to the aircraft fuel circuit and an outlet connected to the flow rate regulator circuit so as to deliver, via its outlet, fuel that is at a predetermined minimum pressure, the pressure of the fuel supplied to the regulator circuit being the higher of the pressures delivered by the centrifugal pump and the assistance pump unit.Type: ApplicationFiled: February 17, 2006Publication date: June 16, 2011Applicant: HISPANO SUIZAInventors: Jean-Marie Brocard, Regis Deldalle, Philippe Galozio, Michel Martini, Alain Varizat
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Patent number: 7950232Abstract: A head loss element is interposed between the outlet from the pump delivering high pressure fuel and the pipe feeding combustion chamber injectors. A servo-valve for feeding a hydraulic actuator of a variable-geometry component of the engine has an HP admission inlet connected to the outlet from the pump upstream from the head loss element and an LP outlet connected to the feed pipe downstream from the head loss element. Thus, the flow rate taken upstream from the head loss element for driving the actuator is compensated by the flow rate reinjected downstream from the head loss element, thereby avoiding any movement of the variable-geometry component giving rise to a disturbance in the flow rate delivered to the injectors.Type: GrantFiled: October 7, 2008Date of Patent: May 31, 2011Assignee: Hispano SuizaInventors: Philippe Galozio, Cédric Montarou, Denis Morin
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Publication number: 20090094974Abstract: A head loss element is interposed between the outlet from the pump delivering high pressure fuel and the pipe feeding combustion chamber injectors. A servo-valve for feeding a hydraulic actuator of a variable-geometry component of the engine has an HP admission inlet connected to the outlet from the pump upstream from the head loss element and an LP outlet connected to the feed pipe downstream from the head loss element. Thus, the flow rate taken upstream from the head loss element for driving the actuator is compensated by the flow rate reinjected downstream from the head loss element, thereby avoiding any movement of the variable-geometry component giving rise to a disturbance in the flow rate delivered to the injectors.Type: ApplicationFiled: October 7, 2008Publication date: April 16, 2009Applicant: HISPANO - SUIZAInventors: Philippe Galozio, Cedric Montarou, Denis Morin
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Publication number: 20080163931Abstract: A fuel supply device includes a fuel supply pipe receiving fuel at a non-regulated pressure delivered by a pump, a device for measuring the flow rate of fuel in the pipe, a first controlled variable-restriction valve mounted in the supply pipe, a control system connected to the flow rate measurement device and to the first valve to control the valve to deliver fuel to the engine at a desired flow rate under normal operating conditions of the engine, a second controlled variable-restriction valve mounted in the supply pipe in series with the first valve, and a control for controlling the second valve to enable the engine to be supplied with fuel at an adjustable, reduced flow rate in response to detecting over-speed or over-thrust of the engine.Type: ApplicationFiled: February 17, 2006Publication date: July 10, 2008Applicant: HISPANO SUIZAInventors: Jean-Marie Brocard, Regis Michel Paul Deldalle, Philippe Galozio, Michel Martini, Alain Michel Varizat
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Patent number: 6655123Abstract: An aircraft engine fuel supply circuit includes a high pressure pump for supplying the engine fuel injectors and supplying a plurality of servovalves for operating various auxiliary mechanisms. In an in-flight re-ignition configuration, with the rotational speed of the engine drops below a threshold value, a fuel economizer valve receives a command to close, thereby shutting off the supply of high pressure fuel to the servovalves. Consequently, the dimensions of the high pressure pump and other associated components in the circuit, especially heat exchangers, may be reduced.Type: GrantFiled: October 25, 2001Date of Patent: December 2, 2003Assignee: SNECMA MoteursInventors: Marie-Trinité Rose Blot-Carretero, Philippe Galozio, Jean-Marie Brocard, Claude Marcel Maillard
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Patent number: 6568189Abstract: A device for controlling fuel pressure and delivery as necessary for the operation of the servovalves of an aircraft engine is disposed downstream of a fuel injector feed unit of the engine. The device comprises a chamber maintained at the servovalve feed pressure by the movement of a closure member to vary the opening of a port of the chamber. The closure member moves under the action of opposing forces comprising inter alia a force in the opening direction proportional to the servovalve feed pressure. An equilibrium position of the closure member is a function of pressure resulting from the engine speed. An injector delivery control loop is therefore isolated from a servovalve pressure and delivery control loop.Type: GrantFiled: August 9, 2002Date of Patent: May 27, 2003Assignee: Snecma MoteursInventors: Marie-Trinité Rose Blot-Carretero, Jean-Marie Brocard, Philippe Galozio, Claude Marcel Maillard
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Patent number: 6497100Abstract: A device for controlling fuel pressure and delivery as necessary for the operation of the servovalves of an aircraft engine is disposed downstream of a fuel injector feed unit of the engine. The device comprises a chamber maintained at the servovalve feed pressure by the movement of a closure member to vary the opening of a port of the chamber. The closure member moves under the action of opposing forces comprising inter alia a force in the opening direction proportional to the servovalve feed pressure. An equilibrium position of the closure member is a function of pressure resulting from the engine speed. An injector delivery control loop is therefore isolated from a servovalve pressure and delivery control loop.Type: GrantFiled: March 14, 2001Date of Patent: December 24, 2002Assignee: Snecma MoteursInventors: Marie-Trinitë Rose Blot-Carretero, Jean-Marie Brocard, Philippe Galozio, Claude Marcel Maillard
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Publication number: 20020184885Abstract: A device for controlling fuel pressure and delivery as necessary for the operation of the servovalves of an aircraft engine is disposed downstream of a fuel injector feed unit of the engine. The device comprises a chamber maintained at the servovalve feed pressure by the movement of a closure member to vary the opening of a port of the chamber. The closure member moves under the action of opposing forces comprising inter alia a force in the opening direction proportional to the servovalve feed pressure. An equilibrium position of the closure member is a function of pressure resulting from the engine speed. An injector delivery control loop is therefore isolated from a servovalve pressure and delivery control loop.Type: ApplicationFiled: August 9, 2002Publication date: December 12, 2002Applicant: SNECMA MOTEURSInventors: Marie-Trinite Rose Blot-Carretero, Jean-Marie Brocard, Philippe Galozio, Claude Marcel Maillard
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Publication number: 20020050140Abstract: An aircraft engine fuel supply circuit includes a high pressure pump for supplying the engine fuel injectors and supplying a plurality of servovalves for operating various auxiliary mechanisms. In an in-flight re-ignition configuration, with the rotational speed of the engine drops below a threshold value, a fuel economizer valve receives a command to close, thereby shutting off the supply of high pressure fuel to the servovalves. Consequently, the dimensions of the high pressure pump and other associated components in the circuit, especially heat exchangers, may be reduced.Type: ApplicationFiled: October 25, 2001Publication date: May 2, 2002Applicant: SNECMA MOTEURSInventors: Marie-Trinite Rose Blot-Carretero, Philippe Galozio, Jean-Marie Brocard, Claude Marcel Maillard
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Publication number: 20010022079Abstract: A device for controlling fuel pressure and delivery as necessary for the operation of the servovalves of an aircraft engine is disposed downstream of a fuel injector feed unit of the engine. The device comprises a chamber maintained at the servovalve feed pressure by the movement of a closure member to vary the opening of a port of the chamber. The closure member moves under the action of opposing forces comprising inter alia a force in the opening direction proportional to the servovalve feed pressure. An equilibrium position of the closure member is a function of pressure resulting from the engine speed. An injector delivery control loop is therefore isolated from a servovalve pressure and delivery control loop.Type: ApplicationFiled: March 14, 2001Publication date: September 20, 2001Applicant: Snecma moteursInventors: Marie-Trinite Rose Blot-carretero, Jean-Marie Brocard, Philippe Galozio, Claude Marcel Maillard