A de-icing splitter nose of an axial turbine engine, specifically, a de-icing splitter nose of a turbo-jet engine compressor includes an annular row of vanes, each of which has a radially extending leading edge, and a de-icing system based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system includes an annular row of injection orifices for injecting de-icing fluid onto the vanes in respective injection directions. Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge of the related vane, enabling said vane to be de-iced.
DEICING NOSE OF AN AXIAL TURBINE ENGINE COMPRESSOR
BUSE DE DEGLACAGE D'UN COMPRESSEUR DE TURBINE AXIALE
2018-04-21
Patent
Electronic Resource
English
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