| 摘要 |
An aircraft anti-icing system is provided. The system includes a source of high temperature gas, a housing (14), at least one conduit (30) configured to carry the high temperature gas from the source to the at least one conduit coupled to the housing and the source, at least one nozzle (34) coupled to the at least one conduit, the at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing, and a port (36) for exhausting air from the housing. |
