Patent ID: 6131855
Filing Date: 2000-10-17
Classification: B64D,F02C,Y02T

Abstract:
An air inlet cowl (9) for a jet engine 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 internal peripheral chamber (21) which is closed by an internal partition (20), said internal partition (20) being equipped with a trough-shaped duct (22) directed toward a rear of said leading edge (16) and open toward the periphery of said air inlet cowl (9);a 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 an injector (12) injecting pressurized hot air into said internal chamber (21); anda part (23) made of a material that can withstand high temperatures and forms part of an external surface (9E) of said cowl (9), to the rear of said leading edge (16), said part (23) closing off said trough- shaped duct (22) and being pierced in such a way as to place said internal chamber (21) in communication with the outside, wherein:said part (23) comprises a single orifice (18) which has an oblong shape, has a front longitudinal edge (18F) and a rear longitudinal edge (18R), and is arranged parallel to said leading edge (16), said orifice serving to calibrate a jet of hot air ejected by said trough-shaped duct (22), while at the same time encouraging heat exchange between said jet of ejected hot air and the external ambient air and keeping this jet of hot air away from said cowl (9);said part (23) extends in said external surface (9E) of said cowl (9) in a parallel direction to the length of said cowl at least substantially along the entire longitudinal length of said air inlet cowl (9) to protect all of this external surface that may be subjected to an action of the flow of hot air ejected by said single orifice (18).