IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0256828
(2010-03-05)
|
등록번호 |
US-8794571
(2014-08-05)
|
우선권정보 |
DE-10 2009 013 159 (2009-03-16) |
국제출원번호 |
PCT/EP2010/001391
(2010-03-05)
|
§371/§102 date |
20120319
(20120319)
|
국제공개번호 |
WO2010/105744
(2010-09-23)
|
발명자
/ 주소 |
- Baumgardt, Torben
- Stolte, Ralf-Henning
- Weber, Carsten
- Reynaud, Remy
- Mueller, Christian
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
12 |
초록
▼
This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. T
This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. The matrix body of the cooler is designed to form a section of the outer skin of the aircraft.
대표청구항
▼
1. An aircraft cooling system comprising: a cooler having a matrix body in which a plurality of coolant channels are formed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body, the matrix body of the cooler for
1. An aircraft cooling system comprising: a cooler having a matrix body in which a plurality of coolant channels are formed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body, the matrix body of the cooler forming a section of an aircraft outer skin with the first and second surfaces of the matrix body, in the state of the cooler mounted to an aircraft, forming outer and inner surfaces respectively of the aircraft outer skin, anda control unit to control the coolant flow through the coolant channels, at least in some operating phases of the aircraft cooling system, such that the coolant in the region of the first surface of the matrix body passes into the coolant channels, and in the region of the second surface of the matrix body passes out of the coolant channels, and to control the coolant flow through the coolant channels, at least in other operating phases of the aircraft cooling system, such that the coolant in the region of the second surface of the matrix body passes into the coolant channels, and in the region of the first surface of the matrix body passes out of the coolant channels. 2. An aircraft cooling system according to claim 1, characterised in that the first surface of the matrix body has a structure suitable for reducing the frictional drag of the first matrix body surface when air is flowing over the first matrix body surface while the aircraft is flying. 3. An aircraft cooling system according to claim 1, characterised in that the matrix body of the cooler is of multilayer construction in the direction of the coolant flow through the coolant channels formed in the matrix body. 4. An aircraft cooling system according to claim 1, characterised by the control unit to control, by appropriate control of the position of a flap defining a flow cross-section of an opening connecting the interior of the aircraft fuselage to the aircraft environment, at least one of a coolant volume flow flowing through the opening and aerodynamic drag caused by the flap while the aircraft is flying. 5. An aircraft cooling system according to claim 1, characterised in that the matrix body of the cooler comprises a plurality of lamellae delimiting the coolant channels formed in the matrix body. 6. A method according to claim 5, characterised in that, in the operating phases of the aircraft cooling system in which the coolant flows over the first matrix body surface, a conveying device which serves to convey, in operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler, coolant through the coolant channels formed in the matrix body of the cooler is switched off. 7. An aircraft cooling system according to claim 1, characterised in that the matrix body of the cooler is designed to form an aircraft outer skin section arranged in the region of a tail or a belly fairing of the aircraft. 8. An aircraft cooling system according to claim 7, characterised in that the matrix body of the cooler is designed to form at least one of a lower and an upper region of an aircraft outer skin section adjacent to a tail end of the aircraft. 9. An aircraft cooling system according to claim 1, characterised by a plurality of ribs extending from the first surface of the matrix body. 10. An aircraft cooling system according to claim 9, characterised in that the ribs at least one of extend substantially parallel to flow lines of an air flow flowing over the first surface of the matrix body while the aircraft is flying and have a contour curved in the direction of the first surface of the matrix body. 11. An aircraft cooling system according to claim 1, characterised in that an opening connecting an interior of an aircraft fuselage to the aircraft environment is designed to act, in the operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler from the second matrix body surface in the direction of the first matrix body surface, as a coolant inlet, through which the coolant can be withdrawn from the aircraft environment before flowing through the matrix body. 12. An aircraft cooling system according to claim 11, characterised in that the opening connecting the interior of the aircraft fuselage to the aircraft environment is arranged in at least one of the region of a tail end of the aircraft, the region of an edge, facing away from a tail of the aircraft, the region of an aircraft rudder unit and the region of a belly fairing of the aircraft. 13. An aircraft cooling system according to claim 1, characterised in that an opening connecting an interior of an aircraft fuselage to the aircraft environment is designed to act, in the operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler from the first matrix body surface in the direction of the second matrix body surface, as a coolant outlet, through which the coolant can be led back into the aircraft environment after flowing through the matrix body. 14. An aircraft cooling system according to claim 13, characterised in that the opening connecting the interior of the aircraft fuselage to the aircraft environment is arranged in a region of the aircraft outer skin on which, while the aircraft is flying, a lower pressure acts than on the aircraft outer skin section formed by the matrix body of the cooler. 15. An aircraft cooling system according to claim 13, characterised in that the opening connecting the interior of the aircraft fuselage to the aircraft environment is arranged in at least one of the region of a tail end of the aircraft, the region of an edge, facing away from a tail of the aircraft, of an aircraft rudder unit and the region of a belly fairing of the aircraft. 16. An aircraft cooling system according to claim 1, characterised by the control unit to control the coolant flow in such a way that, at least in certain operating phases of the aircraft cooling system, the coolant flows over the first surface of the matrix body. 17. An aircraft cooling system according to claim 16, characterised in that the control unit is designed to close, in the operating phases of the aircraft cooling system in which the coolant flows over the first matrix body surface, an opening connecting an interior of an aircraft fuselage to the aircraft environment and acting as a coolant outlet or as a coolant inlet in operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler. 18. An aircraft cooling system according to claim 16 characterised in that the control unit is designed to switch off, in the operating phases of the aircraft cooling system in which the coolant flows over the first matrix body surface, a conveying device which serves to convey, in operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler, coolant through the coolant channels formed in the matrix body of the cooler. 19. A method for operating an aircraft cooling system, wherein at least in certain operating phases of the aircraft cooling system, a coolant flows through a matrix body of a cooler, in which a plurality of coolant channels are formed and extend from a first surface of the matrix body to a second surface of the matrix body, and which forms a section of an aircraft outer skin with the first and second surfaces of the matrix body, in the state of the cooler mounted to an aircraft, forming outer and inner surfaces respectively of the aircraft outer skin, the method comprising: controlling the coolant flow through the coolant channels at least in some operating phases of the aircraft cooling system, such that the coolant in the region of the first surface of the matrix body passes into the coolant channels, and in the region of the second surface of the matrix body passes out of the coolant channels, andcontrolling the coolant flow through the coolant channels, at least in other operating phases of the aircraft cooling system, such that the coolant in the region of the second surface of the matrix body passes into the coolant channels, and in the region of the first surface of the matrix body passes out of the coolant channels. 20. A method according to claim 19, characterised in that the coolant flow is withdrawn from the aircraft environment, before flowing through the matrix body of the cooler, through an opening connecting an interior of an aircraft fuselage to the aircraft environment and acting as a coolant inlet. 21. A method according to claim 19, characterised in that, by appropriate control of the position of a flap defining a flow cross-section of an opening connecting the interior of the aircraft fuselage to the aircraft environment, at least one of a coolant volume flow flowing through the opening and an aerodynamic drag caused by the flap while the aircraft is flying is controlled. 22. A method according to claim 19, characterised in that the coolant flow, after flowing through the matrix body of the cooler, is led back into the aircraft environment through an opening connecting an interior of an aircraft fuselage to the aircraft environment and acting as a coolant outlet. 23. A method according to claim 22, characterised in that a lower pressure acts on the opening connecting the interior of the aircraft fuselage to the aircraft environment and acting as a coolant outlet, while the aircraft is flying, than on the aircraft outer skin section formed by the matrix body of the cooler. 24. A method according to claim 19, characterised in that, at least in certain operating phases of the aircraft cooling system, the coolant flows over the first surface of the matrix body. 25. A method according to claim 24, characterised in that, in the operating phases of the aircraft cooling system in which the coolant flows over the first matrix body surface, an opening connecting an interior of an aircraft fuselage to the aircraft environment and acting as a coolant outlet or as a coolant inlet in operating phases of the aircraft cooling system in which the coolant flows through the matrix body of the cooler is closed. 26. A method according to claim 24, characterised in that, in the operating phases of the aircraft cooling system in which the coolant flows over the first matrix body surface, the coolant flow over the first matrix body surface is controlled by a plurality of ribs extending from the first matrix body surface.
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