Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Abstract: A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

Abstract: A method of casting a blade or vane for a gas turbine engine which enables the production of more complex internal shapes than those which may be made by prior art methods. The method of the invention includes the steps of:making a temporary filler piece from a disposable material,holding the filler piece in place in a die,injecting the core material into the die and causing it to solidify round the filler piece,removing the core from the die,causing the filler to be removed from the core to leave within the core a cavity having the shape of the filler, andusing the core thus produced in an investment casting process to form the blade or vane shape.

Abstract: A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

Abstract: An aerofoil blade or vane for a gas turbine engine comprises an aerofoil which includes one only of the two flanks of the trailing edge of the aerofoil and which is an integrally cast structure. The other flank of the trailing edge is formed as a separate piece which is metallurgically bonded to the remainder of the aerofoil through a joint face. The aerofoil is adapted for the supply of cooling fluid to its interior and the joint face is cut away to form an exit passage or passages for cooling fluid which leaves the interior of the aerofoil.

Abstract: A cooled rotor blade for a gas turbine has an aerofoil in which there are longitudinally extending cooling fluid passages. At the tip of the aerofoil is located a separate, chordwise extending tube. The tube has apertures in its wall which correspond with at least some of the cooling fluid passages, whereby the spent cooling fluid from these passages may pass through the tube to rejoin the gas flow of the engine.

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.