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 Protection of Gas Turbine Blades: A PLATINUM ALUMINIDE DIFFUSION COATING

Abstract: Turbine blades in gas turbine engines operate at elevated temperatures and in highly oxidising atmospheres that can be contaminated with fuel residues and sea water salts. These components, which are expensive to produce, are subjected to high stresses during operation but must be totally reliable during their design life. An economic way to maintain blade properties is to coat the base metal superalloy with a protective layer capable of resisting both high temperature oxidation and hot corrosion. Conventional aluminide coatings are widely used for this purpose but platinum aluminides offer improved corrosion resistance. A collaborative exercise involving Rolls‐Royce and Johnson Matthey has now resulted in the development of a platinum aluminide diffusion coating that offers some advantages over the commercial systems.

An Improved Correlation for the Broadband Noise of High-speed Fans

Abstract: Broadband noise data have been obtained from tests on a wide variety of transonic design speed fans. These fans show considerable differences in noise level at a given tip speed which are often inconsistent with trends expected from previous correlations; in particular, fan loading does not appear to be of primary importance. A new correlation has been developed using rotor blade incidence and relative Mach number as primary parameters. The use of incidence accounts for variations in noise between the fans and also for the effects of throttling at constant tip speed, resulting in a good collapse of data. However, the remaining scatter shows that some second-order effects do exist, and these are discussed.

Blade assembly for a fluid flow machine

Abstract: In a bladed rotor for a gas turbine engine the shrouds or platforms of the blades each have a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as the radial distance from the rotor axis increases, and a sealing member such as a wire is mounted in the groove to seal between the adjacent platforms or shrouds.

Fluid flow machine

Abstract: The invention concerns a fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible force-transmitting means breaking when subjected to a force exceeding a predetermined value.

Bladed rotor for a gas turbine engine

Abstract: This invention relates to a bladed rotor for a gas turbine engine which comprises a disc having blade carrying slots in its periphery. In order to seal the spaces between the blade platforms and the disc an annular array of sealing plates is provided. The plates are supported directly from the disc by a rivet, pin or the like which passes through the disc in between the blade carrying slots, in this way avoiding any additional loading on the blades themselves.