Patent ID: 6079670
Filing Date: 2000-06-27
Classification: B64D,F02C

Abstract:
An air inlet cowl (9) for a jet engine (1), especially for an aircraft, said air inlet cowl (9) being equipped with means for de-icing its leading edge (16) and comprising, for this purpose:a hollow leading edge (16) delimiting an annular internal peripheral chamber (21) which is closed by an internal partition (20) and equipped with at least one orifice (18) placing said internal chamber (21) in communication with the outside; anda pipe (10) which can be connected, at its rear end away from said leading edge (16), to a pressurized hot air circuit (14) and, at its front end toward said leading edge (16), to a diffuser (12) consisting of annular pipework housed in said annular internal chamber (21) and equipped with a number of orifices (12A) distributed along said diffuser and injecting said pressurized hot air into said annular internal chamber (21),wherein:said diffuser (12) consists of straight portions (22) joined together by elbows (23) to give said pipework a polygonal annular shape;said diffuser (12) is fixed inside said annular internal chamber (21) by flat support tabs (24) made of an elastic material, each support tab (24) being fixed at its rear end (24A) to said internal partition (20) and being connected at its front end (24B) to one of said straight portions (22) of said polygonal annular pipework;each flat support tab (24) has a direction at least essentially orthogonal to the axis (X--X) of said straight portion (22) to which it is connected and is arranged in such a way that its plane is at least essentially parallel to said axis (X--X) of said portion (22); andthe front end (24B) of each support tab (24) is connected to the corresponding straight portion (22) of said polygonal annular pipework by a ball joint (25).