Device for de-icing a blade of a propeller, blade of a propeller comprising such a device, propeller, Turbomachine and aircraft

摘要

The de-icing device has at least one first heating device in contact with a surface portion 8 of a rotor blade 1; a second heating device having heating elements 26 circumscribing a closed-contour zones (fig.2b,25); the first heater extends at least partially facing the inside of the closed-contour zones. The first heating device may be a thin film of electrical resistors (fig.2a,21); alternatively the first heater may be a lattice of resistors (fig.3a,31) forming cells, each of which are smaller than the closed-contour zones. Preferably, the heating elements of the second heater are filiform and extend in a pattern of convex polygons or curves, forming a coarse lattice of adjacent closed-contour zones separated by the heating elements; this enables the size of the ice pieces removed from the blade to be controlled. Preferably, the heating devices extend in a recess in the blade surface; the heating lattices may have a power supply 24 which supplies more power to the second heater lattice than to the first heater lattice.