Patents by Inventor Juan Tomas Prieto Padilla
Juan Tomas Prieto Padilla 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: 11814180Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.Type: GrantFiled: November 18, 2021Date of Patent: November 14, 2023Assignee: AIRBUS OPERATIONS, S.L.U.Inventors: Juan Tomas Prieto Padilla, Lucía Bayona Revilla, Diego Barron Vega
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Publication number: 20230194185Abstract: An aircraft heat exchanger arranged longitudinally and including a casing with an inner chamber configured so that coolant flows longitudinally from an inlet to an outlet, a plurality of laterally spaced longitudinally extending inner chamber plates, and a plurality of channels defined between contiguous plates. Each plate includes a leading edge oriented towards the inlet and configured to divert coolant towards the channels. A plurality of the plates include an inner hollow area configured to conduct a flow of hot bleed air therethrough. Leading edges of a first group of plates are arranged in a stepped pattern. A gap defined between the first group of plates and a first casing lateral wall establishes a fluid coolant communication through the first group of plates between the casing inlet and outlet. The lateral distance between each leading edge of the first group of plates and the first lateral wall decreases longitudinally.Type: ApplicationFiled: December 14, 2022Publication date: June 22, 2023Inventors: Juan Tomás PRIETO PADILLA, Diego BARRÓN VEGA
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Patent number: 11623752Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.Type: GrantFiled: June 30, 2020Date of Patent: April 11, 2023Assignee: AIRBUS OPERATIONS S.L.Inventors: Angel Garcia Zuazo, Serafin Escudero Fraile, Esteban Martino-Gonzalez, Juan Tomas Prieto Padilla, Diego Barron Vega
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Patent number: 11597523Abstract: An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.Type: GrantFiled: June 30, 2020Date of Patent: March 7, 2023Assignee: Airbus Operations S.L.Inventors: Esteban Martino-Gonzalez, Juan Tomas Prieto Padilla
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Patent number: 11408338Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.Type: GrantFiled: March 10, 2020Date of Patent: August 9, 2022Assignees: AIRBUS SAS, AIRBUS OPERATIONS SAS, AIRBUS OPERATIONS S.L.Inventors: Bruno Medda, Esteban Martino-Gonzalez, Thomas Stevens, Julien Cayssials, Juan Tomas Prieto Padilla, Adeline Soulie, Didier Poirier, Pierre-Alain Pinault, Diego Barron Vega
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Publication number: 20220153420Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.Type: ApplicationFiled: November 18, 2021Publication date: May 19, 2022Inventors: Juan Tomas PRIETO PADILLA, Lucía BAYONA REVILLA, Diego BARRON VEGA
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Patent number: 11215118Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.Type: GrantFiled: December 12, 2019Date of Patent: January 4, 2022Assignees: Airbus (S.A.S.), Airbus Operations (S.A.S.), Airbus Operations, S.L.Inventors: Bruno Medda, Thomas Stevens, Julien Cayssials, Adeline Soulie, Didier Poirier, Pierre-Alain Pinault, Esteban Martino González, Juan Tomas Prieto Padilla, Diego Barron Vega
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Patent number: 11136921Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.Type: GrantFiled: March 10, 2020Date of Patent: October 5, 2021Assignees: AIRBUS OPERATIONS SAS, AIRBUS SAS, AIRBUS OPERATIONS S.L.Inventors: Bruno Medda, Esteban Martino-Gonzalez, Thomas Stevens, Julien Cayssials, Juan Tomas Prieto Padilla, Adeline Soulie, Didier Poirier, Pierre-Alain Pinault, Diego Barron Vega
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Patent number: 10961907Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.Type: GrantFiled: June 26, 2018Date of Patent: March 30, 2021Assignee: Airbus Operations, S.L.Inventors: Marta Castillo De Alvear, Juan Tomas Prieto Padilla
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Publication number: 20210001991Abstract: An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.Type: ApplicationFiled: June 30, 2020Publication date: January 7, 2021Inventors: Esteban MARTINO-GONZALEZ, Juan Tomas PRIETO PADILLA
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Publication number: 20210001990Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.Type: ApplicationFiled: June 30, 2020Publication date: January 7, 2021Inventors: Angel GARCIA ZUAZO, Serafin ESCUDERO FRAILE, Esteban MARTINO-GONZALEZ, Juan Tomas PRIETO PADILLA, Diego BARRON VEGA
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Publication number: 20200347782Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.Type: ApplicationFiled: March 10, 2020Publication date: November 5, 2020Inventors: Bruno MEDDA, Esteban MARTINO-GONZALEZ, Thomas STEVENS, Julien CAYSSIALS, Juan Tomas PRIETO PADILLA, Adeline SOULIE, Didier POIRIER, Pierre-Alain PINAULT, Diego BARRON VEGA
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Publication number: 20200291854Abstract: An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.Type: ApplicationFiled: March 10, 2020Publication date: September 17, 2020Inventors: Bruno MEDDA, Esteban MARTINO-GONZALEZ, Thomas STEVENS, Julien CAYSSIALS, Juan Tomas PRIETO PADILLA, Adeline SOULIE, Didier POIRIER, Pierre-Alain PINAULT, Diego BARRON VEGA
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Publication number: 20200291869Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.Type: ApplicationFiled: March 10, 2020Publication date: September 17, 2020Inventors: Bruno MEDDA, Esteban MARTINO-GONZALEZ, Thomas STEVENS, Julien CAYSSIALS, Juan Tomas PRIETO PADILLA, Adeline SOULIE, Didier POIRIER, Pierre-Alain PINAULT, Diego BARRON VEGA
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Publication number: 20200191056Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.Type: ApplicationFiled: December 12, 2019Publication date: June 18, 2020Inventors: Bruno Medda, Thomas Stevens, Julien Cayssials, Adeline Soulie, Didier Poirier, Pierre-Alain Pinault, Esteban Martino González, Juan Tomas Prieto Padilla, Diego Barron Vega
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Publication number: 20180371991Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.Type: ApplicationFiled: June 26, 2018Publication date: December 27, 2018Inventors: Marta Castillo De Alvear, Juan Tomas Prieto Padilla