Abstract: The present invention relates to a cooled blade forming an upstream guide vane element for a turbomachine, wherein the airfoil comprises a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in the first opening and a second end in the second opening, first spacers on the side of the first end and second spacers on the side of the second end of the sleeve making a space between the outer face of the sleeve and the wall of the cavity, the blade being arranged so that the sleeve is inserted into the cavity through the first opening. The blade is characterized in that the first spacers are secured to the sleeve and the second spacers are secured to the wall of the cavity of the airfoil. The invention makes it possible to mount the sleeve despite an accentuated curvature of the profile of the airfoil.