Abstract: The present invention relates to a cooling arrangement in which a fractal passage network is provided incorporating several passage stages. Each passage stage 4, 5, 6, 7 has substantially the same passage cross-section for consistency with other passage stages to facilitate flow pressure control across the fractal passage network. Normally, the length of passages in each passage stage are also specifically determined in order to achieve a consistent flow pressure control. The arrangement is particularly utilized with regard to cooling within turbine engine components such as blade aerofoils.

Abstract: A vane for directing hot gases of a gas turbine engine and comprising at least one platform and a hollow aerofoil portion having an air entry tube extending spanwise therein, the tube being provided with a plurality of apertures, the size and the spacing therebetween being chosen to cause cooling fluid to impinge on the interior surface of the aerofoil portion in the form of a plurality of jets. A plurality of columnar projections extend between the interior surface of the aerofoil portion and the exterior of the air entry tube, each projection being positioned directly upstream of one of the apertures in the air entry tube with respect to the general flow of impinged fluid in the space between the interior surface of the aerofoil portion and the exterior of the air entry tube.