| 摘要 |
The main subject matter of the invention is a system (1) for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisation air collected from a portion for collecting compressed air (12), characterised in that it comprises a collection port (30) formed on a casing (12c) of the compressed air collection portion (12), a collection member (32) coupled to the collection port (30), a through port (38) of the collection member (32) formed on a casing (39) of a compartment (ZC) of the turbine engine, said casing (39) being subjected to small movements relative to the casing (12c) of the compressed air portion (12), the collection member (32) crossing the through port (38) with a freedom of movement relative to the latter during said small movements, a high-pressure space (33) crossed by the collection member (32), located between the casing (12c) of the compressed air collection portion (12) and the casing (39) of the compartment (ZC), and including pressurised air at a pressure higher than that of the collected pressurisation air, the system (1) for supplying pressurised air also including sealing means (2) located substantially between the casing (12c) of the compressed air collection portion (12) and the casing (39) of the compartment (ZC) in order to form a substantially sealed separation between the high-pressure space (33) and a free space (40) communicating with the compartment (ZC) and provided around the collection member (32), in order to prevent the entry of pressurised air from the high-pressure space (33) into the collection member (32) in the event of the latter breaking. |
