Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Steven Hillier

Aaron D Sippel

David John Thomas

Daniel Kent Vetters

Peter Broadhead

Michael J Whittle

Simon James Jones

Paul Antony Davis

Ted Joseph Freeman

Andrew J Eifert

Jeffrey Allen Walston

Anthony G Razzell

Bruce Edward Varney

Joseph P Lamusga

Brian J Shoemaker

Jun Shi

Sungbo Shim

Roderick M Townes

Clark Snyder

Joseph Gordon Doyle

Stephen Harris

Michael Jacquinto

William Richards

Wesley Thibault

Dennis Jong

Owen Draper

David Thomas

A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall. The second shroud segment includes a second carrier segment and a second blade track. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Turbine shroud system with ceramic matrix composite segments and dual inter-segment seals

A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.

Ceramic matrix composite airfoil with heat transfer augmentation

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 gas turbine engine assembly includes a first component, a second component, and a seal. The first component is spaced apart from the second component to form a gap between the first component and the second component. The seal is configured to block gases from flowing in the gap between the first component and the second component.

Turbine engine assembly with ceramic matrix composite components and end face seals

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 section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.

Turbine vane assembly with ceramic matrix composite vanes

This document discloses a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes one or more axial restraint features which engage with a corresponding feature of the wall segment or a supporting structure thereof.

Intercomponent seal for a gas turbine engine

The disclosure relates to a ceramic matrix composite (CMC) aerofoil. Example embodiments include an aerofoil comprising first and second tubular CMC cores () extending along a longitudinal axis of the aerofoil; and an outer CMC layer surrounding the first and second tubular CMC cores () and defining an outer shape of the aerofoil having leading and trailing edges, wherein fibres within a wall of the second tubular CMC core extend to the trailing edge of the aerofoil.

CMC aerofoil

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

Split line flow path seals

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

This disclosure describes a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts the either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes axially compressible segments which allow the seal member to bend longitudinally.

Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibers held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.

Growing community of inventors

Manchester, United Kingdom

Steven Hillier