Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce High Temperature Composites Inc.

Peter Broadhead

Daniel Kent Vetters

Aaron D Sippel

David John Thomas

Steven Hillier

Andrew J Eifert

Simon James Jones

Paul Antony Davis

Jun Shi

Jeffrey Allen Walston

Bruce Edward Varney

Thomas Wunderlich

John Hoptroff

Ted Joseph Freeman

Roderick M Townes

Joseph P Lamusga

Joseph Gordon Doyle

Harald Schiebold

Stuart Lee

Michael Jacquinto

Michael Leslie Burns

Wesley Thibault

Peter Avery

Tim Hopp

David Thomas

Steven Hiller

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Keystoned blade track

A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

Brazed blade track for a gas turbine engine

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Impingement tubes for gas turbine engine assemblies with ceramic matrix composite components

A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.

Segmented turbine shroud with sealing features

A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

Full hoop blade track with flanged segments

Composite keystoned blade track

Impingement tubes for CMC seal segment cooling

A method of forming a blade assembly for a gas turbine engine, the method comprising mounting turbine blades on a rotor in a number of radial stages. Sacrificial supports are placed on the blades, and nozzle guide vanes are located on the supports. The rotor is introduced into a casing, and the guide vanes are mounted to the casing.

Method of forming a rotating blade assembly

A passive internal control system for rotor blade tip clearance of a high-pressure turbine is based on inner rings that expand in a radial direction under the influence of heat and radially adjust the clearance delimited by liner segments () on the casing side. It comprises a radially expandable U-shaped downstream inner ring () mounted to inner platforms () of guide vanes () on a side where the rotor does not have a static bearing, said ring providing expansion compensation in the axial and peripheral directions and forming a torsion box () with struts () that absorbs rolling and tilting moments.

Arrangement for internal passive turbine blade tip clearance control in a high pressure turbine

On a two or multi-stage turbine, expansion rings are provided in all stages at the sides of the rotors for passive, continuous running gap control whose thermal expansion and contraction behavior corresponds to that of the rotors and which are connected to radially moveable upstream and downstream stator vanes (). The downstream stator vanes are assembled to the upstream stator vanes via a bridge () which is axially and circumferentially fixed and located flexibly in the radial direction on the outer casing () of the turbine. The stator vanes () arranged between the rotor disks are integrally connected to the bridge or, as separate components, held axially and circumferentially on the bridge to take up rolling and tilting moments.

Arrangement for the automatic running gap control on a two or multi-stage turbine

A retaining arrangement for joining together two components such as a rim coverplateand a rotor discin a gas turbine engine. The arrangement comprising a channelformed by respective formationson the discand coverplate, which channellocates one or more annular ring memberwhich prevents relative axial movement therebetween. Engageable abutment formationsare provided respectively on the discand coverplate, to prevent relative pivotal movement.

Retaining arrangement

This invention relate to a retaining arrangement for rotor blades of axial-flow turbomachinery which features blade roots slots on a rotor disk for the accommodation and radial fixation of roter blades and which further features a continues, circumferential retaining ring for the axial fixation of the rotor blades in the blade root slots and a locking arrangement for the axial retention of the retaining ring. The retaining arrangement is characterized in that the retaining ring has recesses which correspond with sections of the blade root slots and projecting sections on its outer circumference. The present invention provides a cost-effective retaining arrangements for blade of axial-flow turbomachinery which provides for better control of the leakage flows in the blade root area, generally improved flow conditions in the inter-stage area, lower centrifugal forces and ease of assembly. The separation of the retaining function from the sealing function according to the present invention provide for a considerable saving in mass

Retaining arrangement for rotor blades of axial-flow turbomachinery

A gas turbine engine rotor disc (20) is provided with a plurality of cooling air supply passages (32) which are generally radially extending but are inclined in the downstream direction. Each passage (32) has a cross-sectional configuration which renders the ends (34) of the passages (32) less likely than normal to act as the site of hoop-stress induced cracks.

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Derby, United Kingdom

Peter Broadhead