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.

Variable geometry nozzles for turbomachines

Abstract: An exhaust nozzle for a gas turbine engine comprising a duct 17(c) extending along an axis and having at a dowstream end thereof a mechanism for varying the geometry and area of the nozzle. The mechanism 28 comprises an axially translatable member 28 which has a face 29 extending in a direction transverse to the axis of the duct 17(c) against which pressurized gases flowing through the duct acts to balance out the loads on the flaps. A plurality of flaps 38,43 are spaced circumferentially around the axis of the duct. The flaps 38 are pivotally attached to the axially translatable member 28 and are provided with a cam follower 40 that co-operates with a cam 37. The cams 37 are fixed relative to the duct 17(c) and thereby defines the attitude of each flap 38 relative to the member 28. Seal plates 41 and 45 cover the gaps between adjacent flaps 38 and 43 to the seal plates 45. A plurality of struts interconnect the member 28 and the second flaps of the pivotal attachment of the flaps 43 to the flap 38. A set of flaps 47 are provided to provide fairing between the downstream ends of the member 28 and the flaps 43. In operation axial movement of the member 28 moves the flaps 38 and 43 to different positions.

Method and apparatus for introducing a weft thread into a sheet of warp threads

Abstract: This invention concerns a method of introducing at least one weft thread into a sheet of warp threads so as to assist in holding the sheet together, the said method comprising employing at least one toothed wheel which is rolled transversely across the sheet periodically to raise and lower predetermined warp threads in a sequence which permits the passage of the weft thread transversely of at least a part of the sheet, and introducing the said weft thread over and under the said predetermined warp threads.

Turbine stator aerofoil blades for gas turbine engines

Abstract: A stator aerofoil blade for a gas turbine engine is manufactured in the form of a heat pipe so that during engine operation, the blade remains substantially isothermal. Localized thermal gradients within the blade are minimized thereby reducing the possibility of blade distortion or cracking. A shroud ring for a gas turbine engine is manufactured in the form of a heat pipe so that during engine operation, the ring remains substantially isothermal. Localized thermal gradients within the ring are minimized, thereby reducing the possibility of ring distortion occurring.

Optical determination of clearances

Abstract: Simplification in manufacture and use of an optical triangulation probe is achieved by providing it with a T-shaped optical path. The cross-bar of the T-shape extends between a light source comprising a laser diode 42 and a light detector comprising a photodiode array 103, whilst the stem of the T- shape contains a rod-shaped lens and prism arrangement 71. The cross-bar of the T-shape is occupied by a solid optical bar-shaped assembly 31 comprising a number of blocks cemented together and providing reflective surfaces 53,55 and 59 for directing outgoing and return light through the T-shape, The lens and prism arrangement focusses outgoing light from laser diode 42 onto the surface of an object 101 whose distance is to be measured and focusses reflected return light onto the photodiode array 103 as a light spot 111. Position of light spot 111 as monitored by the output signal of photodiode array 103 is a measure of distance D between the object 101 and the probe. The probe is for use in gas turbines for measuring clearances between rotor blade tips and turbine casings.

Gas turbine engines

Abstract: A gas turbine engine blade tip seal consists of a sealing ring which is controlled by means of two annular control members The members are arranged such that one control member has a relatively rapid thermal response rate and the other control member has a relatively slow thermal response rate, the sealing ring being controlled such that a preferred tip clearance is maintained under varying engine operating conditions