Axial Turbine Engine Compressor De-Icing Blade
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United States of America Patent
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Oct 19, 2017
app pub date -
Apr 7, 2017
filing date -
Apr 8, 2016
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Abstract
An aeroplane turbojet low-pressure compressor vane includes a leading edge, a trailing edge, a surface, and an extrados surface which extend from the leading edge to the trailing edge. To combat the presence and the formation of ice, the vane is provided with an electric de-icing device with a thermistor. The thermistor forms a heating electrical track suitable for de-icing the vane. The present application also proposes a method for producing a turbine engine vane.
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