Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Michael J Whittle

Anthony G Razzell

Roderick M Townes

Daniel Kent Vetters

Ted Joseph Freeman

Eric Koenig

Pascal Dunning

Ian M Edmonds

Jeffrey Allen Walston

Keith C Sadler

Stephen Harris

David J Shepherd

Andrew T Holt

Duncan Forbes

Steven Hillier

David John Thomas

Jeffrey M Crutchfield

James C Smith

Michael G Abbott

Oliver D A O'Carroll

Robert S Bainbridge

Afzal Ali

Rachel Woodfield

Emma C Steedman

Edward M Jones

Aaron D Sippel

Daniel Clark

Stephen Isaiah Harris

Alexandra Baucco

David Cameron Wright

Jeff Crutchfield

Louise J Gale

Stephan J Pattison

Carl Boettcher

Matthew D Thomason

Alexander Wong

Sungbo Shim

James Kell

Jay Edgar Lane

Andrew D Norton

Thomas Nixon

Donka Novovic

Jade Whittle

Paul Morrell

Christopher Nash

Michael J Abbott

Matthew Adams

James William Philip Montgomery

Austin R Warmuth

Laurie Bootle

Guillaume Lambertin

A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

Efficient aircraft engine

A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

Gas turbine engine

A ceramic matrix composite (CMC) component is provided that includes: a CMC body in which an environmental protection layer is completely embedded within a CMC material of the CMC body, the environmental protection layer comprising a ceramic that has a higher impact and/or environmental resistance than the CMC material. Methods for manufacturing the CMC component are also provided.

Recession resistant intermediate layer for CMC vane

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 turbine shroud assembly for a gas turbine engine includes a shroud wall extending circumferentially partway around a central reference axis to define a gas path of the gas turbine engine. An attachment feature extends radially from the shroud wall. A foam is located at least on the shroud wall.

Gas turbine engine components with metallic and ceramic foam for improved cooling

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 stator vane assembly for a gas turbine engine is disclosed. The stator vane assembly includes an inner carrier including a metallic material and an outer carrier including a metallic material. The stator vane assembly further includes a ceramic-containing airfoil that extends from the inner carrier to the outer carrier and is at least partially received by the inner carrier and the outer carrier. The stator vane assembly further includes a load transfer device disposed between the airfoil and at least one of the inner carrier and the outer carrier. The load transfer device includes a support member fixedly attached to the at least one of the inner carrier and the outer carrier, and a plurality of micropillars coupled to the support member and extending towards the airfoil. Each micropillar is deformable and engages the airfoil.

Load transfer device, stator vane assembly, turbine, and gas turbine engine including the same

A turbine vane assembly for use in a gas turbine engine includes turbine vanes, a segmented inner vane support, and an outer vane support. The turbine vanes are arranged around a central axis of the engine. The inner vane support is arranged radially inwardly of the turbine vanes. The outer vane support includes a full-hoop outer support ring located radially outward of the plurality of turbine vanes and extends entirely circumferentially about the central axis. The outer vane support further includes a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane.

Vane ring assembly with ceramic matrix composite airfoils

An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

Gas turbine engine components with foam filler for impact resistance

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.

Ceramic matrix composite turbine vane assembly having minimalistic support spars

A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly and a vane assembly. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly.

Ceramic matrix composite vane assembly

A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

Ceramic matrix composite vane assembly with shaped load transfer features

A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.

Gas turbine engine operating schedules for optimizing ceramic matrix composite component life

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London, United Kingdom

Michael J Whittle