DEICING DEVICE FOR PROPFAN-TYPE PROPELLER BLADES

摘要

The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit comprises a turbine engine rotating at least one rotor having a plurality of blades (4a) disposed around a ring (5a) that moves with the blades, the outer wall (14a) of said ring forming part of the outer skin of the propulsion unit and said outer skin being subjected to the atmospheric conditions outside the propulsion unit. The aforementioned turbine engine generates a flow of hot gases that are released through a hot annular channel (10) that is concentric with the above-mentioned moving ring (5a), a portion of the surface of said channel being defined by the inner wall of the moving ring (5a). The invention includes: means (11) for capturing the heat energy from the hot channel (10), which are disposed inside the moving ring (5a); means (12, 13) for transferring the heat energy to the blades (4a) of the rotor; and means (18, 19) for distributing the heat energy over at least one portion of the surface of said blades (4a).