| 摘要 |
<p>The invention relates to a system (10) for cooling a heat exchanger (12) on board an aircraft, comprising a process air line (28) whose first end is connected to an engine (16) of the aircraft in order to supply the process air line (28) with engine bleed air. A second end of the process air line (28) is connected with a turbine (30) in order to supply the engine bleed air flowing through the process air line (28) to the turbine (30). A first end of a cooling air line (34) is connected to the turbine (30) in order to supply the cooling air line (34) with cooling air created by decompressing the engine bleed air in the turbine (30). The cooling air line (34) is constructed to supply the cooling air flowing through the cooling air line (34) to the heat exchanger (12) that is to be cooled.</p> |
