Abstract: A vane for a gas turbine engine comprising a hollow body externally of aerofoil form. The inner surface of the body is provided with confronting grooves, extending in a direction along the length of the aerofoil form, at a location intermediate the leading and trailing edges of the aerofoil form for receiving two inserts. The first insert comprises two perforated panels situated inside a trailing region of the aerofoil form and defining therewith one or more air passages between the insert and the wall of the body. The first insert has portions which engage in the grooves in the wall of the body, and is provided with confronting grooves extending in a direction along the length of the aerofoil form at a location intermediate the leading and trailing edges of the aerofoil form. The second insert comprises a first panel extending across the void in the body, and has edges which engage in the confronting grooves in the first insert.