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.

The Importance of Circumferential Non-uniformities in a Passage-Averaged Quasi-Three-Dimensional Turbomachinery Design System

Abstract: The purpose of this paper is to show, for both rotating and non-rotating blade rows, the importance of including circumferential non-uniform flow effects in a quasi-three-dimensional blade design system. The paper follows on from previous publications on the system in which the mathematical analysis and computerised system are detailed. Results are presented for a different stack of the nozzle guide vane presented previously and for a turbine rotor. In the former case it is again found that the blade force represents a major contribution to the radial pressure gradient, while for the rotor the radial pressure gradient it is dominated by centrifugal effects. In both examples the effects of circumferential non-uniformities are detailed and discussed.Copyright © 1985 by ASME

Variable area nozzle for a gas turbine engine

Abstract: A variable area nozzle for a gas turbine engine comprises an annular array of primary flap members pivoted at their upstream ends for movement of their downstream ends towards or away from the axis of the array. The primary flap members are provided with roller tracks which co-operate with roller tracks of adjacent primary flap members to define tapered roller trackways. Rollers are positioned in the roller trackways such that relative axial movement between the rollers and roller trackways urges the downstream ends of the primary flap members towards or away from the axis of the array.

Blade for a gas turbine engine

Abstract: A stator blade for a gas turbine engine comprises a stack of laminar sections and means adapted to resiliently hold the sections together in compression to allow for differential expansion between the stack and supporting structure.

Sealing of vaned assemblies

Abstract: A nozzle guide vane assembly for a gas turbine engine includes one or more vanes, each provided with a radially inner and a radially outer shroud member. The assembly is adapted to be supported between radially inner and radially outer support members. One or more of the shroud members are provided with a chordally extending straight sealing edge adapted to sealingly contact one of the radially inner and outer support members.

Seal between relatively moving components of a fluid flow machine

Abstract: A seal at the downstream end of a compressor of a gas turbine engine is formed between a rotor element of the compressor and a stationary element carried by the combustion chamber inner casing, the combustion chamber inner casing is mounted at its downstream end rigidly to the engine casing so that the upstream end is free to move under the influence of both pressure and temperature changes within the engine the seal being adapted to compensate for relative movement between the compressor rotor and the combustion chamber inner casing.