Rolls-royce Corporation

Rolls-royce Power Engineering Plc

Sean Alan Walters

Guy David Snowsill

Julian Glyn Balsdon

Brian G Cooper

Kevin Paul Self

Mark Timothy Mitchell

Neal Carter

Michael J Jago

Simon Bather

Andrew Thomas Napper

Benjamin Thomas Littley

Daniel P Moss

Ivor Saltman

John Irving

Nomesh P Kandaswamy

Jessica Kennedy

Kali Charan Nayak

Benjamin Littley

Nomesh Kandaswamy

Brian Guy Cooper

Daniel Paul Moss

A bladed disc system for a turbine engine having a disk portion and a plurality of blade portions which are associated with a stator section and an intercavity sealing portion, disc portion shaped such that blade portions are able to fit within firtree slot in disc portion, blade portion having aerofoil section and root section, aerofoil section having portion shaped such that they extend proximate to intercavity sealing portion, disc portion extending from portion that connects with drum to outer edge at which blade portions are connected with disc portion having width transition region in which thickness of disc increases from point at which disc connects to drum to outer edge at which it holds blade portions, and wherein width transition region has curved width transition region with radius r, and an overhanging portion which extends into the intercavity spacing between the width transition region and the intercavity sealing portion.

Bladed disc

An assembly for receiving in a radially extending bucket groove () of a turbine disc (), the assembly including a turbine blade having an elongate body () of aerofoil cross-section, a root portion () at one end of the elongate body () and a tip at the other. The root portion () configured to be retained in the bucket groove (). A heat shield () configured to be received between an end of the root portion () and a radially inner surface of the bucket groove () and to interlock with the root portion () in a manner which deters separation in a radial direction.

Thermal shielding in a gas turbine

An air-cooled component such as a turbine stator vane, has a row of cooling passages extending from the interior of the vane to the exterior. The passages are inclined to a plane perpendicular to the row. The angle of inclination of each passage varies with the position of the passage along the row. The arrangement assists in avoiding local overheating of the vane surface.

Air-cooled component

A core, for use in a casting mould to form a cavity in a cast component such as a blade or vane of a gas turbine engine. The core has a relatively fragile thin-walled region. A bead is formed along a lateral edge of the thin-walled portion in order to reduce cracking or other damage in the thin-walled portion.

Core for use in a casting mould

A pressure actuated tip clearance system for a shroud structure of a gas turbine engine rotary stage includes an annular plenum chamber formed between an annular arrangement of a plurality of shroud liners on the inner circumference of the chamber and a generally cylindrical casing on the radially outer side, and, in use, a hot gas stream radially inwards of the shroud liners. Each shroud liner comprises a hollow box section comprising upstream and downstream walls, radially inner and outer walls, and side walls, the downstream and radially inner and outer walls being closed, the upstream wall having an air inlet aperture, and at least one of the side walls having at least one outlet aperture. The inlet aperture is in flow communication with a source of high pressure air at a pressure higher than that of the gas stream.

Blade tip clearance system

An aerofoil made from a sheet metal blank which is bent in the shape of an aerofoil such that it has a leading edge, a trailing edge, a pressure side and a suction side, and the blank is joined at the trailing edge. The regions of the sheet metal blank that form the leading edge, trailing edge and pressure side of the aerofoil comprise a plurality of perforations. The suction side region of the sheet metal blank is imperforate.

Aerofoil

The present invention provides an airfoil for a first stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Airfoil for a first stage nozzle guide vane

A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling passage intersections when air is passed through the cooling passages. The spacing of the passages in at least one of the arrays is chosen to provide a predetermined range of intersection density in a selected region or regions of the component.

Component comprising a multiplicity of cooling passages

An air cooled component with an internal air cooling system comprising an internal cavity which is divided into at least two compartments. The compartments are arranged in flow sequence by communication through side wall chambers formed in the wall of the component. At least one of the side wall chambers is sub-divided into a plurality of cells in flow parallel and each of the cells has at least one air entry aperture and at least one air exit aperture.

Growing community of inventors

Bristol, United Kingdom

Sean Alan Walters