Rolls-Royce Limited

About: Rolls-Royce Limited is a based out in . It is known for research contribution in the topics: Gas compressor & Rotor (electric). The organization has 624 authors who have published 623 publications receiving 10751 citations. The organization is also known as: Rolls Royce Limited.

Gas turbine engine power plant

Abstract: A V.S.T.O.L. gas turbine power plant includes a main gas turbine engine having an exhaust gas propulsion nozzle and a fan arranged within a fan duct, which duct terminates in two nozzles such that a portion of the fan air may be directed vertically downwards or horizontally, the remaining portion of the fan air acts as a working fluid in one or more further auxiliary gas turbine engines each engine including a vectorable exhaust nozzle.

Monitoring distance variations

Abstract: An optical device for monitoring variations in the distance between an object and a datum is particularly useful for monitoring running clearances in the demanding environment of a gas turbine engine. The device depends upon the principle that an image focussed by an astigmatic lens system changes shape as it passes through the focus. To monitor variations, e.g., in the working clearance between a turbine blade tip and a turbine casing, light from a light source is projected through an astigmatic lens system, onto the blade tip. Reflected light from the astigmatic image on the blade tip is passed back through the lens system and re-projected onto an image shape monitor which includes photo-cells. The photo-cells may be mounted in the main optical assembly or probe, or they may be distant from the probe and fed by light guides. Signals from the cells are combined to produce a monitor signal, the magnitude of which is a measure of the shape of the image on the blade tip, and hence of the clearance.

Rotor blade for a gas turbine engine

Abstract: A rotor blade for a gas turbine engine comprises an aerofoil, shank portion and a root by which the remainder of the blade may be supported from a rotor disc. Cooling for the aerofoil is provided by passages in the leading portion of the aerofoil which are fed with cooling air from an entry aperture and a sealed liquid cooling circuit which contains a cooling liquid. This circuit comprises a liquid feed passage adjacent the trailing edge of the aerofoil and connected adjacent the tip of the aerofoil with a vapor return passage, both passages communicating with a sealed cavity within the shank of the blade. In operation the cooling fluid (e.g. metallic sodium) flows under the influence of centrifugal and other forces along the feed passage, is vaporized and returns to the cavity via the return passage. The cavity acts as a condenser for the fluid.

Compressor rotor stage

Abstract: A rotor blade stage for a gas turbine engine comprises an annular array of aerofoil blades. Each blade is provided with circumferentially extending platforms which are arranged so as to circumferentially spaced apart from the platforms of adjacent blades. Elastomeric dampers are interposed between adjacent blades and are so adapted that upon rotation of the array of blades, each of the elastomeric dampers is centrifugally urged into engagement with the radially inner faces of adjacent platforms of adjacent blades.

Aerofoil for a gas turbine engine

Abstract: An aerofoil, particularly a nozzle guide vane, for a gas turbine engine comprises a hollow interior with an air guide tube located therein. The air guide tube has apertures therein, and in order to cause the free edges of the apertures to seal against internal ribs of the aerofoil, springs are provided to force the open edges apart. Conveniently the springs comprise straps between the apertures which are formed with a corrugated shape.