Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Other

Anthony G Razzell

Michael J Whittle

Ted Joseph Freeman

Roderick M Townes

David J Shepherd

Duncan Forbes

John J A Cullen

Ian M Edmonds

Aaron D Sippel

Jeffrey M Crutchfield

John Richard Webster

Steven Hillier

Stephen Isaiah Harris

Alexandra Baucco

Edwin G Butler

Paul A Doleman

Robert J Mitchell

Michael G Abbott

Louise J Gale

Diane Holland

John Dominy

Alexander Wong

Stephan J Pattison

Daniel Kent Vetters

Ian C D Care

Jay Edgar Lane

Andrew Martin Rolt

Leo Vivian Lewis

Adrian Lewis Harding

Mark David Taylor

Robert John Miller

Geraint Wun Jewell

Alan J Mitcham

Ludovic Edmond Molliex

Lee Mansfield

Samuel Alexander Mason

Paul Morrell

Matthew Adams

Fabrice Rossignol

Dennis Jong

Magnus Holmquist

Robert Lundberg

Olivier Sudre

Julien Parmentier

Michel Parlier

Philip D Brown

Ihsan A H Al-Dawery

Ihsan Ai-i Al-Dawery

Stephen Pattison

Owen Draper

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Gas turbine engine with pre-conditioned ceramic matrix composite components

A component for use in a gas turbine engine is made from ceramic materials. The component is made from a core preform containing ceramic reinforcement fibers. A plurality of preform tows are applied on at least a portion of the core preform and extend along at least a portion of the core preform to provide an outermost surface. The core preform and the plurality of preform tows are infiltrated with ceramic matrix material to form a ceramic matrix composite component.

Ceramic matrix composite vane with hybrid construction

A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.

Hybrid vane segment with ceramic matrix composite airfoils

An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.

Ceramic matrix composite vane with cooling holes and methods of making the same

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.

Turbine shroud assembly with dovetail retention system

A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.

Turbine section assembly with ceramic matrix composite vane

A component for use in a gas turbine engine includes a component body, and a damage-indicative coating. The damage-indicative coating is configured to change from an intact state in which the damage-indicative coating has a first appearance to a damaged state in which the damage-indicative coating has a second appearance.

Turbine engine component with overstress indicator

A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The turbine outer case is arranged around an axis. The blade track segment is configured to define a portion of a gas path of the gas turbine engine. The carrier assembly is coupled to the turbine outer case and supports the blade track segment.

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 blade for a gas turbine engine includes a root and an aerofoil. The root is configured to be coupled with a disc of the gas turbine engine and rotate with the disc about an axis during operation of the gas turbine engine. The aerofoil is coupled with the root of the turbine blade for movement with the root.

Turbine blade with ceramic matrix composite aerofoil and metallic root

A turbine shroud assembly of a gas turbine engine includes seal segments made from ceramic matrix composite materials. The mounting assembly used to support the seal segments has heat shields adapted to resist radiant heating from the seal segments, especially portions of the seal adjacent to a primary gas path along the turbine shroud assembly.

Ceramic matrix composite hanger heat shield

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Derby, United Kingdom

Anthony G Razzell