| 发明名称 | Method and apparatus for cooling fuel in an aircraft fuel tank | ||
| 摘要 | Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air. | ||
| 申请公布号 | US8757550(B2) | 申请公布日期 | 2014.06.24 |
| 申请号 | US201012786474 | 申请日期 | 2010.05.25 |
| 申请人 | Airbus Operations Limited;Airbus Operations SAS | 发明人 | Wilde Andrew;Bossut Jean-Claude;Revel Marc;Hayles Alan John;Dayal Ruchir;Kendall Hannah |
| 分类号 | B64D15/04;B64D15/16;B64F5/00;B64D37/04;B64D37/32;B64D37/02;B64D37/06 | 主分类号 | B64D15/04 |
| 代理机构 | Lowe Hauptman & Ham, LLP | 代理人 | Lowe Hauptman & Ham, LLP |
| 主权项 | 1. An aircraft comprising: a fuselage fuel tank having a tank wall, the aircraft having an external surface which is located on a fuselage or on a lower surface of a fixed-wing of the aircraft, a ram air intake disposed on said external surface, and an air supply passage extending from the ram air intake to a cooling region, said cooling region being (a) located to the exterior of the fuel tank and directly adjacent to the tank wall, (b) in thermal communication with the fuel tank and (c) in fluid communication with a downstream region downstream of, and remote from, said cooling region, whereby in use, during flight, air flows from the exterior of the aircraft via said cooling region thereby cooling the fuel tank. | ||
| 地址 | Bristol GB | ||