IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0565930
(2009-09-24)
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등록번호 |
US-8516792
(2013-08-27)
|
우선권정보 |
FR-08 56459 (2008-09-25) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
9 |
초록
▼
A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulati
A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulating in the cell cooling circuit and air flow channeled into a cooling air channel extending from an air intake to an exhaust; and a second heat exchanger ensuring a heat transfer between the coolant circulating in the cell cooling circuit and the fuel. The air intake includes a blocker to open/close it. The system includes a fuel transfer circuit, which connects the fuel tank to the second heat exchanger and provides fuel to the second heat exchanger, including a valve selectively changing a fuel supply direction from the second heat exchanger between the directions of the tank and the fuel supply circuit.
대표청구항
▼
1. A system for managing the heat fluxes of an aircraft that includes at least one propulsion system that integrates a turbomachine, and a cell, the system comprising: at least one fuel tank configured to supply the turbomachine with fuel via a fuel supply circuit;a cell cooling circuit connected to
1. A system for managing the heat fluxes of an aircraft that includes at least one propulsion system that integrates a turbomachine, and a cell, the system comprising: at least one fuel tank configured to supply the turbomachine with fuel via a fuel supply circuit;a cell cooling circuit connected to at least one source of thermal effluents, the cell cooling circuit integrating first means for ensuring a heat transfer between a coolant that circulates in the cell cooling circuit and an air flow that is channeled into at least one cooling air channel that extends from at least one air intake up to at least one air exhaust;second means for ensuring a heat transfer between the coolant that circulates in the cell cooling circuit and the fuel; anda fuel transfer circuit that connects the at least one fuel tank to the second heat transfer means and that is configured to provide the fuel from the at least one fuel tank to the second heat transfer means, the fuel transfer circuit including at least one control valve configured in the fuel transfer circuit to selectively change a supply direction of the fuel from the second heat transfer means between the direction toward the tank and the direction toward the fuel supply circuit that is designed for the propulsion system,wherein the air intake includes means for blocking air configured to occupy a first open state in which the blocking means allows the air flow to pass inside the cooling air channel and a second closed state in which the blocking means blocks the air intake to prohibit the air flow to pass inside the cooling air channel. 2. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the first heat transfer means comprises a first fluid/air exchanger that is arranged in one of the at least one cooling air channel, the second heat transfer means comprises a second fluid/fuel exchanger that is distant from the first exchanger,the cell cooling circuit comprising the first fluid/air exchanger,the second fluid/fuel exchanger, anda circuit that ensures the supply of said second exchanger with fuel, the fuel being re-injected in the tank or oriented to the supply circuit that is designed for one of the at least one propulsion system. 3. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the first heat transfer means and the second heat transfer means together comprise a single fuel/fluid/air exchanger that is arranged in one of the at least one cooling air channel, the cell cooling circuit comprising the single fuel/fluid/air exchanger, wherein the system includes a circuit that ensures the supply of said exchanger with fuel, the fuel being re-injected in the tank or oriented to the supply circuit that is designed for one of the at least one propulsion system. 4. The system for managing the heat fluxes of an aircraft according to claim 1, further comprising means for forcing the flow of air into the cooling air channel. 5. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the blocking means comprises a door that is connected to the aircraft by a hinge, the door being in closed position at a surface that is in contact with aerodynamic fluxes. 6. The system for managing the heat fluxes of an aircraft according to claim 5, wherein the door is configured to open toward the outside of the cooling air channel, the opening being facilitated by the hinge. 7. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the cooling air channel has a V shape and comprises two coupled exchangers, arranged at the point of the V, and the system further comprises a fan inserted between the exchangers and the air exhaust. 8. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the cooling air channel has a U shape and comprises two coupled exchangers, arranged at the branch of the U that is connected to the air exhaust, and the system further comprises a fan is inserted between the exchangers and the air exhaust. 9. The system for managing the heat fluxes of an aircraft according to claim 1, wherein first heat transfer means is sized so as to optimize the operation of the first heat transfer means during the ground phases of the aircraft. 10. The system for managing the heat fluxes of an aircraft according to claim 1, wherein the second heat transfer means is sized so as to optimize the operation of the second heat transfer means during flight phases of the aircraft at high speeds. 11. A method for managing heat fluxes of an aircraft that comprises at least one propulsion system that integrates a turbomachine and a cell that includes at least one fuel tank configured to supply the turbomachine with fuel via a fuel supply circuit and, at least one source of thermal effluents connected to a cell cooling circuit that integrates first means to ensure a heat transfer between a coolant that circulates in the cell cooling circuit and an air flow that is channeled into at least one cooling air channel that extends from at least one air intake up to at least one air exhaust, the method comprising:during flight phases of the aircraft, blocking the air intake of the cooling air channel to prohibit the air flow to pass inside the cooling air channel and ensuring a heat transfer between a coolant that circulates in the cell cooling circuit and the fuel; andduring ground phases of the aircraft, ensuring a heat transfer between the coolant that circulates in the cell cooling circuit and the air flow. 12. The method for managing heat fluxes of an aircraft according to claim 11, wherein forcing the air flow into the cooling air channel during the ground phases. 13. A system for managing the heat fluxes of an aircraft that includes at least one propulsion system that integrates a turbomachine, and a cell, the system comprising: at least one fuel tank configured to supply the turbomachine with fuel via a fuel supply circuit;a cell cooling circuit connected to at least one source of thermal effluents, the cell cooling circuit integrating a first heat exchanger configured to ensure a heat transfer between a coolant that circulates in the cell cooling circuit and an air flow that is channeled into at least one cooling air channel that extends from at least one air intake to at least one air exhaust;a second heat exchanger configured to ensure a heat transfer between a coolant that circulates in the cell cooling circuit and the fuel; anda fuel transfer circuit that connects the at least one fuel tank to the second heat exchanger and that is configured to provide the fuel from the at least one fuel tank to the second heat exchanger, the fuel transfer circuit including at least one control valve configured in the fuel transfer circuit to selectively change a supply direction of the fuel from the second heat exchanger between the direction toward the tank and the direction toward the fuel supply circuit that is designed for the propulsion system,wherein the air intake includes a blocking device configured to occupy a first open state of the air intake in which the blocking device allows the air flow to pass inside the cooling air channel and a second closed state in which the blocking device blocks the air intake to prohibit the air flow to pass inside the cooling air channel.
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