Patents by Inventor Nicolas BOUCHOUT
Nicolas BOUCHOUT 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: 11994069Abstract: An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.Type: GrantFiled: September 30, 2021Date of Patent: May 28, 2024Assignee: Safran NacellesInventors: Julien Corbin, Jean-Nicolas Bouchout, Caroline Dang
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Patent number: 11883874Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.Type: GrantFiled: October 4, 2021Date of Patent: January 30, 2024Assignee: Safran NacellesInventors: Vincent Peyron, Jean-Nicolas Bouchout, Flavie Hubert-Choinard, Alexandra Dugardin
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Patent number: 11772810Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).Type: GrantFiled: April 3, 2020Date of Patent: October 3, 2023Assignee: Safran NacellesInventors: Vincent Peyron, Jean-Nicolas Bouchout
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Patent number: 11512638Abstract: A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.Type: GrantFiled: April 3, 2020Date of Patent: November 29, 2022Assignee: Safran NacellesInventors: Vincent Peyron, Jean-Nicolas Bouchout
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Publication number: 20220186665Abstract: An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.Type: ApplicationFiled: September 30, 2021Publication date: June 16, 2022Applicant: Safran NacellesInventors: Julien CORBIN, Jean-Nicolas BOUCHOUT, Caroline DANG
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Patent number: 11268443Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.Type: GrantFiled: January 22, 2019Date of Patent: March 8, 2022Assignee: Safran NacellesInventors: Vincent Peyron, Patrick Gonidec, Jean-Nicolas Bouchout
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Publication number: 20220025816Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.Type: ApplicationFiled: October 4, 2021Publication date: January 27, 2022Applicant: Safran NacellesInventors: Julien CORBIN, David PEREIRA, Vincent PEYRON, Jean-Nicolas BOUCHOUT, Caroline DANG, Nicolas CHOUQUET
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Publication number: 20220023931Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.Type: ApplicationFiled: October 4, 2021Publication date: January 27, 2022Applicant: Safran NacellesInventors: Vincent PEYRON, Jean-Nicolas BOUCHOUT, Flavie HUBERT-CHOINARD, Alexandra DUGARDIN
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Patent number: 11230973Abstract: In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between ?70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).Type: GrantFiled: April 3, 2020Date of Patent: January 25, 2022Assignee: Safran NacellesInventors: Vincent Peyron, Jean-Nicolas Bouchout
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Publication number: 20200362758Abstract: In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between ?70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).Type: ApplicationFiled: April 3, 2020Publication date: November 19, 2020Applicant: Safran NacellesInventors: Vincent PEYRON, Nicolas BOUCHOUT
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Publication number: 20200317358Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).Type: ApplicationFiled: April 3, 2020Publication date: October 8, 2020Applicant: Safran NacellesInventors: Vincent PEYRON, Nicolas BOUCHOUT
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Publication number: 20200318546Abstract: A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.Type: ApplicationFiled: April 3, 2020Publication date: October 8, 2020Applicant: Safran NacellesInventors: Vincent PEYRON, Nicolas BOUCHOUT
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Publication number: 20190153947Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.Type: ApplicationFiled: January 22, 2019Publication date: May 23, 2019Applicant: Safran NacellesInventors: Vincent PEYRON, Patrick GONIDEC, Nicolas BOUCHOUT