| 摘要 |
The firewall (12) has a metallic wall (3) inserted in an aircraft structure (5) and including a surface (3`) placed opposite to a compartment (1). An adjusting unit (11) with another wall (4), maintains a surface maximum temperature at a predetermined temperature value lower than a self-ignition temperature of compartment elements i.e. oil, where the maximum temperature ranges between 300 and 310 degree Celsius. The unit has an aspirating unit i.e. pump, with a pipe (13) that connects an outlet orifice (7) to a gas exhaust duct (10) of a turboshaft engine (9) of another compartment (2). |
