| 发明名称 | Deicing device for propfan-type propeller blades | ||
| 摘要 | A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades. | ||
| 申请公布号 | US8932016(B2) | 申请公布日期 | 2015.01.13 |
| 申请号 | US201013318505 | 申请日期 | 2010.05.03 |
| 申请人 | Airbus Operations S.A.S. | 发明人 | Bulin Guillaume;Rogero Jean-Michel;Fabre Christian |
| 分类号 | F01D5/18;B64C11/48;B64D15/04;B64D27/02 | 主分类号 | F01D5/18 |
| 代理机构 | Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P. | 代理人 | Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P. |
| 主权项 | 1. A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation, through a transmission system, at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with an outer wall of the annular crown part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via a substantially annular vein, which is concentric with the moving annular crown, and defined in part by an inner wall of the moving annular crown, the deicing device comprising: at least one hot air collection point that captures thermal energy from the annular vein, the at least one hot air collection point being on the inner wall of the annular crown; a duct that transfers the thermal energy from the annular vein towards the blades; and means for distributing the thermal energy onto at least a part of a surface of the blades. | ||
| 地址 | Toulouse FR | ||