| 发明名称 | Heat exchanger for the outer skin of an aircraft | ||
| 摘要 | A heat exchanger for an outer skin of an aircraft comprises at least one feed line for a coolant, at least one discharge line for the coolant and at least one bundle of coolant channels through which coolant flows, wherein in the case of the heat exchanger being attached to the outer skin, the coolant channels are positioned directly on the outer skin of the aircraft, at least in areas, for dissipating heat to the surrounding environment of the aircraft. The heat exchanger may comprise cooling fins around which air flows for increasing the heat dissipation. | ||
| 申请公布号 | US9309000(B2) | 申请公布日期 | 2016.04.12 |
| 申请号 | US200913056509 | 申请日期 | 2009.07.27 |
| 申请人 | Airbus Operations GmbH | 发明人 | Piesker Markus |
| 分类号 | B64D13/06;B64D13/00;F28F3/12;F28F1/00;F28D21/00 | 主分类号 | B64D13/06 |
| 代理机构 | Lerner, David, Littenberg, Krumholz & Mentlik, LLP | 代理人 | Lerner, David, Littenberg, Krumholz & Mentlik, LLP |
| 主权项 | 1. A heat transfer device for an outer skin of an aircraft, comprising: at least one supply line for a coolant; at least one discharge line for the coolant; at least one bundle of coolant ducts through which the coolant flows; at least one gap between the coolant ducts and at least one of a pressure bulkhead, the outer skin of the aircraft, or a cover of a housing for receiving the coolant ducts; and at least one slit in the outer skin of the aircraft for enabling an air flow from the surroundings of the aircraft into the at least one gap, the at least one slit comprising first and second slits arranged at a distance from one another and parallel to one another and parallel to the flight direction, wherein the heat transfer device is attached to the outer skin of the aircraft and the coolant ducts are positioned directly on at least some regions of the outer skin of the aircraft for dissipating heat to the surrounding environment of the aircraft. | ||
| 地址 | DE | ||