SPLITTER OF AN AXIAL TURBOMACHINE, CORRESPONDING COMPRESSOR AND AXIAL TURBOMACHINE

The nose (122) has guide walls which are provided to extend from a leading edge. A leading edge de-icing channel (140) is provided to extend annularly along the edge. The channel is designed to conduct a fluid. The channel is provided with a wall (142) forming the leading edge. The guide surfaces of the primary and secondary flows are attached to the wall. Independent claims are included for the following: (1) a compressor of an axial turbomachine; and (2) a axial turbomachine.