Patents by Inventor Carlos Casado Montero
Carlos Casado Montero 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).
-
Patent number: 11952140Abstract: A cooling system for an aircraft, including a heat exchanger for cooling a hot fluid with cooling air, an air intake for the supply of cooling air and a Coand?-effect air amplifier for the creation of a flow of cooling air.Type: GrantFiled: October 19, 2020Date of Patent: April 9, 2024Assignee: Airbus Operations S.L.U.Inventors: Carlos Casado-Montero, Alberto Molina Parga
-
Patent number: 11724817Abstract: An aircraft including a combustion engine with a combustion chamber an injection device for injecting fuel in the combustion chamber and an air separation device adapted to separate air into an oxygen-enriched gas mix and an nitrogen-enriched gas mix, wherein the oxygen-enriched gas mix is injected into the combustion chamber with the fuel while the nitrogen-enriched gas mix is used to inert at least some portions of the aircraft in the environment of said combustion engine.Type: GrantFiled: December 14, 2021Date of Patent: August 15, 2023Assignee: AIRBUS OPERATIONS SLInventors: Pablo Manuel Calderon Gomez, Carlos Casado-Montero
-
Patent number: 11555448Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.Type: GrantFiled: June 13, 2019Date of Patent: January 17, 2023Assignee: Airbus Operations S.L.Inventors: Carlos Casado-Montero, Pio Fernandez-Lopez
-
Publication number: 20220185495Abstract: An aircraft including a combustion engine with a combustion chamber an injection device for injecting fuel in the combustion chamber and an air separation device adapted to separate air into an oxygen-enriched gas mix and an nitrogen-enriched gas mix, wherein the oxygen-enriched gas mix is injected into the combustion chamber with the fuel while the nitrogen-enriched gas mix is used to inert at least some portions of the aircraft in the environment of said combustion engine.Type: ApplicationFiled: December 14, 2021Publication date: June 16, 2022Inventors: Pablo Manuel CALDERON GOMEZ, Carlos CASADO-MONTERO
-
Publication number: 20220161940Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.Type: ApplicationFiled: November 15, 2021Publication date: May 26, 2022Inventors: Pedro Manuel MARTIN CANDELARIO, Lucas GRANJA PAREJO, Carlos CASADO-MONTERO
-
Patent number: 11167854Abstract: The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.Type: GrantFiled: June 4, 2018Date of Patent: November 9, 2021Inventors: Carlos Casado-Montero, Alberto Molina Parga
-
Patent number: 11091271Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.Type: GrantFiled: September 29, 2016Date of Patent: August 17, 2021Assignee: AIRBUS OPERATIONS S.L.Inventors: Carlos Casado-Montero, Victor Barreiro Rodriguez, Alexandra Carrasco Carrascal
-
Patent number: 11084602Abstract: An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.Type: GrantFiled: November 27, 2018Date of Patent: August 10, 2021Assignee: AIRBUS OPERATIONS S.L.Inventors: Carlos Casado-Montero, Javier Linde Ayllon
-
Publication number: 20210114742Abstract: A cooling system for an aircraft, including a heat exchanger for cooling a hot fluid with cooling air, an air intake for the supply of cooling air and a Coand?-effect air amplifier for the creation of a flow of cooling air.Type: ApplicationFiled: October 19, 2020Publication date: April 22, 2021Inventors: Carlos CASADO-MONTERO, Alberto MOLINA PARGA
-
Patent number: 10836497Abstract: Air conditioning system for a cabin 6 of an aircraft, the air conditioning system 1 including a pressurized air source 2, a ram air duct 3, an air amplifier 4 and a heat exchanger 5. The air amplifier 4 includes an inlet 41 for work air, a slot 42 suitable for letting the work air exit the air amplifier, and a main fluid zone 43. The inlet 41 is in fluid communication with the pressurized air source 2 and the slot 42 is arranged in fluid communication with the ram air duct 3, in such a way that the work air exiting from the slot 42 produces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct 3. The air amplifier 4 is arranged so that the ambient air is forced by the suction effect to pass from the inlet 51 to the outlet 52 of the cold side of the heat exchanger 5.Type: GrantFiled: December 30, 2016Date of Patent: November 17, 2020Assignee: Airbus Operations S.L.Inventor: Carlos Casado Montero
-
Patent number: 10640191Abstract: A drain mast for draining liquids from an aircraft, comprising a tube that comprises an internal rim connected to the internal surface of the tube, the internal rim being located in a plane inclined with respect to the horizontal plane of the aircraft and having its lowest part located on the second end of the tube, an aperture for evacuating the liquid, the aperture being located at the lowest part of the internal rim and in the face of the tube facing the incoming airflow, the internal rim and the aperture being configured such that at the second end, the liquid is directed by gravity through the internal rim to the aperture and wherein, in use, the drained liquid flowing from the aperture is pushed by the incoming airflow to the atmosphere.Type: GrantFiled: October 18, 2017Date of Patent: May 5, 2020Assignee: AIRBUS OPERATIONS S.L.Inventors: Carlos Casado Montero, José Ángel Hernanz Manrique, Alberto Molina Parga
-
Publication number: 20190390601Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.Type: ApplicationFiled: June 13, 2019Publication date: December 26, 2019Inventors: Carlos CASADO-MONTERO, Pio FERNANDEZ-LOPEZ
-
Patent number: 10472073Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.Type: GrantFiled: December 30, 2016Date of Patent: November 12, 2019Assignee: Airbus Operations S.L.Inventor: Carlos Casado Montero
-
Publication number: 20190263528Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.Type: ApplicationFiled: September 29, 2016Publication date: August 29, 2019Inventors: Carlos CASADO-MONTERO, Victor BARREIRO RODRIGUEZ, Alexandra CARRASCO CARRASCAL
-
Publication number: 20190161209Abstract: An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.Type: ApplicationFiled: November 27, 2018Publication date: May 30, 2019Inventors: Carlos CASADO-MONTERO, Javier LINDE AYLLON
-
Publication number: 20180346132Abstract: The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.Type: ApplicationFiled: June 4, 2018Publication date: December 6, 2018Inventors: Carlos CASADO-MONTERO, Alberto MOLINA PARGA
-
Patent number: 10125690Abstract: A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up. The start-up turbine is capable of turning a rotor of the turbomachine for the purpose of the start-up, so as to prevent the rotor from encountering critical frequencies of the turbomachine.Type: GrantFiled: June 25, 2014Date of Patent: November 13, 2018Assignees: AIRBUS OPERATIONS SAS, AIRBUS OPERATIONS S.L., GENERAL ELECTRIC COMPANYInventors: Patrick Zaccaria, Philippe Chareyre, Pio Fernandez-Lopez, Carlos Casado-Montero, Amid Ansari, Thomas Earl Gillingham, Robert Charles Hon, Daniel Roy Kiracofe, Kenneth Kirchmayer, Michael Scott McCambridge, Tod Robert Steen
-
Patent number: 10041414Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.Type: GrantFiled: June 25, 2014Date of Patent: August 7, 2018Assignees: AIRBUS OPERATIONS S.L., AIRBUS OPERATIONS SAS, GENERAL ELECTRIC COMPANYInventors: Patrick Zaccaria, Philippe Chareyre, Pio Fernandez-Lopez, Carlos Casado-Montero
-
Publication number: 20180111673Abstract: A drain mast for draining liquids from an aircraft, comprising a tube that comprises an internal rim connected to the internal surface of the tube, the internal rim being located in a plane inclined with respect to the horizontal plane of the aircraft and having its lowest part located on the second end of the tube, an aperture for evacuating the liquid, the aperture being located at the lowest part of the internal rim and in the face of the tube facing the incoming airflow, the internal rim and the aperture being configured such that at the second end, the liquid is directed by gravity through the internal rim to the aperture and wherein, in use, the drained liquid flowing from the aperture is pushed by the incoming airflow to the atmosphere.Type: ApplicationFiled: October 18, 2017Publication date: April 26, 2018Inventors: Carlos CASADO MONTERO, José Ángel HERNANZ MANRIQUE, Alberto MOLINA PARGA
-
Publication number: 20180050786Abstract: A drain mast for draining liquids from an aircraft. The drain mast comprises a tube and further comprises a pipe coupled to the inner longitudinal surface of the tube and configured such that the drained liquid flows from the tube to the pipe. The pipe has an inlet having its longitudinal axis configured to confront the coming airflow for allowing the inlet of the coming airflow into the pipe, and an outlet having its longitudinal axis inclined with respect to the longitudinal axis of the inlet and configured to discharge the airflow flowing through the pipe in a direction inclined with a component perpendicular to the fuselage of the aircraft.Type: ApplicationFiled: August 15, 2017Publication date: February 22, 2018Inventors: Carlos CASADO MONTERO, José Ángel HERNANZ MANRIQUE, Alberto MOLINA