Tooling and method for manufacturing a composite vane for an aircraft engine

A tooling for manufacturing a vane made of composite material for a turbomachine, in particular of an aircraft, said vane comprising a blade comprising a pressure side and a suction side which extend from a leading edge to a trailing edge of the blade, the vane also comprising a root and an upper edge opposite its root, the vane further comprising at least one metal shield extending along at least one of said edges of the blade the tooling comprising:

• a mold and a counter-mold which define between them a cavity configured to receive a woven preform of the blade the cavity comprising a first portion configured to receive the shield and the edge or edges of the preform intended to receive this shield and a second portion configured to receive at least part of the remainder of the preform,
• at least one port for injecting resin into the cavity in order to impregnate said preform, and
• elements for managing the temperature of the cavity,
• wherein the temperature management elements comprise first elements for managing the temperature of the first portion of the cavity, and second elements for managing the temperature of the second portion of the cavity which are independent of the first temperature management elements so that the first and second management elements can heat the first and second portions of the cavity to different temperatures during at least one step of a method for manufacturing the vane.