Abstract: A cooled vane or blade for a gas turbine engine has a cooling arrangement for its trailing region which can be accommodated in the relatively thin section available. In this arrangement the trailing region of the hollow interior of the blade is divided off from the remainder by a partition which may be apertured to allow cooling air to enter the compartment thus formed. The concave, pressure flank of the compartment is cooled by arrays of film cooling holes while the convex, suction flank has a perforated plate spaced therefrom to provide impingement cooling. The suction flank is therefore unapertured and there is no disturbance of the high speed airflow in this region. The spent impingement air leaves the aerofoil via a slot and may pass over pedestals en route to cool the entire trailing edge.

Abstract: A vane for a gas turbine engine has an aerofoil of unconventional shape. The stacking of sections which defines the aerofoil is arranged to produce an aerofoil whose concave flank is convex in spanwise sections and whose convex flank is concave in spanwise sections. In order to reduce the problems produced by the resulting shape of trailing edge the sections are stacked so that all their trailing edges lie in a plane substantially parallel with the plane of the throat formed between the trailing edge and the next adjacent vane in an array.

Abstract: A gas turbine rotor blade has a root portion and a hollow aerofoil supported from the root. Within the hollow aerofoil is mounted an air entry tube which has a closed end at or adjacent the tip of the aerofoil, the tube being sealed to the hollow blade interior at or adjacent the closed end so as to close off the otherwise open tip of the hollow aerofoil.