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

A de-icer device for de-icing a splitter nose of an aviation turbine engine, the device comprising:

• a splitter nose for positioning downstream from a fan of the engine in order to split air from the fan into a core stream and a bypass stream in respective annular flow channels, said splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel;
• an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume;
• a plurality of injection orifices configured to inject hot air into the core stream flow channel towards the inlet guide vanes;
• an annular deflector positioned inside the annular volume subdividing said annular volume into a first annular cavity and a second annular cavity, which second annular cavity is defined between the annular deflector and the outer annular wall of the splitter nose, the deflector having an upstream end in contact with the outer annular wall of the splitter nose;
• and
• at least one nozzle opening out to the inside of the first annular cavity, said nozzle being fed with hot air by a feed duct connected to a pressurized portion of the engine.