System for deicing an air inlet cowl for a turbine engine

A system for deicing the hollow leading edge (11) of an air inlet cowl (8) for a turbine engine (1), in particular for an aircraft, said deicing system comprising:

• an injector (12) designed to inject pressurized hot air inside said hollow leading edge (11);
• means (13) for bleeding off pressurized hot air that are mounted on the hot-stream generator (2) of said turbine engine (1);
• a hot-air circulation circuit (9, 14, 18) for conveying said pressurized hot air from said bleed means (13) to said injector (12), said hot-air circulation circuit comprising two branches forming a right-angled structure, namely:
• a transverse branch (14) whose end is rigidly connected to said bleed means (13), and
• a longitudinal branch (9, 18) which is arranged laterally with respect to said turbine engine (1) and whose end is connected to said injector (12);
• and
• fastening means (23) arranged in the region of said injector (12) and intended to fasten said longitudinal branch (9, 18) to said air inlet cowl (8),
• wherein a sealed articulation device (27) is mounted on at least one of said branches of said hot-air circulation circuit to provide said right-angled structure with capabilities of deforming about said articulation device.