A device for de-icing a splitter nose of an aviation turbine engine

摘要

The invention relates to a device for de-icing a splitter nose 5 of an aviation turbine engine. The device comprises a splitter nose having an outer annular wall 12 defining the inside of the bypass stream flow channel 4 and an inner annular wall 10 defining an inlet of the core stream flow channel 3. An inner shroud 1 is mounted at a splitter nose upstream end on the inner annular wall of the splitter nose and has inlet guide vanes 7. The splitter nose and the inner shroud defining an annular volume 18. The device also comprises an annular deflector 26 positioned inside the annular volume so as to subdivide said annular volume into a first annular cavity 28 and a second annular cavity 30. The deflector may comprise a thermally insulating layer comprising silicone, and a silica powder based lagging. A nozzle 56 opens into the first annular cavity for feeding hot air into the cavity. Injection orifices 20 inject hot air from the cavity into the core stream flow channel. The invention also provides a fan module including such a device, and an aviation turbine engine.