Patent ID: 8047470

Claim:
A system for deicing a hollow leading edge of an air inlet cowl of an aircraft turbine engine said deicing system comprising: an injector designed to inject pressurized hot air inside said hollow leading edge; a hot air intake mounted on a hot-stream generator of said turbine engine; a hot-air circulation circuit for conveying said pressurized hot air from said hot air intake to said injector, said hot-air circulation circuit forming a right-angled structure comprised of a transverse branch rigidly connected to said hot air intake, and a longitudinal branch arranged laterally with respect to said turbine engine and whose end is connected to said injector; a fastening unit arranged in the region of said injector for fastening said longitudinal branch to said air inlet cowl; and a sealed articulation device comprised of two mutually secured swivels mounted on at least one of said transverse branch and said longitudinal branch of said hot-air circulation circuit to provide said right-angled structure with capabilities of deforming about said articulation device; and an external protective casing surrounding said transverse branch and provided with a conjoint articulation device arranged and produced in correspondence with said sealed articulation device.