Showing papers by "Rolls-Royce Limited published in 1975"

Cooled blade for a gas turbine engine

Abstract: A cooled blade for a gas turbine engine comprises an aerofoil portion having a longitudinally extending hollow. An air entry tube is mounted within the hollow and is pressed against a locating surface within the hollow by a resilient member such as a spring tube.

Gas turbine engine

Abstract: A heat input device for a heat engine comprises a combustion device which is adapted to support surface burning of a fuel and oxidant mixture and a heat exchanger which is adapted to transfer the heat from the hot surface against which the surface burning takes place to the working fluid of the engine.

Gas turbine engine power plant with a coal burning fluidized bed

Abstract: A gas turbine engine power plant having a coal burning fluidized bed utilized as the heating source for the power plant. The fluidized bed comprises inerts and coal in which is immersed a temperature sensitive device, the signal from which is used to control the supply of coal to the bed to thereby maintain the bed at a predetermined temperature and to limit the bed temperature to a predetermined maximum value. The bed can be fluidized by the flow of compressed air from the compressor of the gas turbine engine power plant and the whole of the compressor delivery air flows through the bed in direct chemical contact with the bed materials and is then cleaned prior to delivery to the turbines of the power plant from which it is discharged to atmosphere.

Method for manufacturing bladed members from powder material

Abstract: The invention is concerned with manufacturing gas turbine engine components e.g. guide vanes and blades, in dense silicon nitride starting with silicon nitride in a powder form. Guide vanes are usually in the form of an aerofoil portion and two shroud portions and according to the invention, the aerofoil portion is made in a first mould by hot pressing a mixture of silicon nitride powder and a fluxing agent, such as magnesia. The formed aerofoil is placed in a second mould so that each end extends partly into a space which is to be filled with a further mixture of silicon nitride powder and a fluxing agent. The further mixtures are hot pressed both to form the shroud portions and to amalgamate the shroud portions with the aerofoil portion. Features, such as, flanges and webs can be formed in the shrouds during the moulding process or they can be machined into the shrouds after the vane is removed from the second mould.