Abstract: A double-wall blade for a turbine, particularly for aeronautical applications, has a streamlined lateral wall, which extends along an axis, surrounds the axis itself, and is defined by an inner wall and an outer wall facing and integral with each other; the blade is provided with inner channeling, which has a cavity into which, in use, cooling air is admitted, and a number of ducts, which are provided tangentially between the inner wall and outer wall, are separated from one another by baffles which are transverse to the axis and have respective intakes which are separate from one another and communicate with the cavity in order, in use, each to have a corresponding flow of cooling air pass through them.