Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Allison Advanced Development Company

Daniel Kent Vetters

Ted Joseph Freeman

David John Thomas

Aaron D Sippel

Jeffrey Allen Walston

Michael J Whittle

Jun Shi

Douglas David Dierksmeier

Mark O'Leary

Eric Koenig

Todd Engel

Peter Broadhead

Bruce Edward Varney

Matthew R Brandt

Joseph P Lamusga

Steven Hillier

Andrew J Eifert

Michael Karam

Jack Dwane Petty, Sr

Simon James Jones

Robert J Shinavski

Jeffrey M Crutchfield

Paul Antony Davis

Edward Claude Rice

Sean E Landwehr

Alexandra Baucco

Robert Wayne Cedoz

Eugene Clemens

Rick Uskert

Matt Brandt

Roy David Fulayter

Bronwyn Power

Joseph Gordon Doyle

Jeff Crutchfield

Michael Jacquinto

Wesley Thibault

Andrew Joseph Lazur

Anthony G Razzell

Scott Nelson

Raymond Ruiwen Xu

Mark Jon Blackwelder

Roderick M Townes

Eric Sean Donovan

Wayne S Steffier

Steven Arlen Klusman

Steven Gagne

Michael Stephen Krautheim

Mark Stephen Henry

John Timothy Alt

Michael John Agg

Christopher Nash

Donald G Chouinard

Timothy Hoffmann

Roy Peter McIntyre

Simon Mizzi

Andrew Barlow

David Eames

Samantha Tatar

James Glen Schwefel

Phil Bastnagel

The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.

Turbine vane assembly with reinforced end wall joints

An airfoil assembly for a gas turbine engine includes a vane, a support strut, and an inner carrier. The vane is adapted to interact with hot gases flowing around the airfoil assembly during use of the airfoil assembly. The support strut is located in an interior cavity formed in the vane and configured to receive force loads applied to the ceramic matrix composite vane by the hot gases. The inner carrier is coupled with the support strut and adapted to block the hot gases from flowing radially inward toward an axis of the gas turbine engine.

Turbine vane assembly with ceramic matrix composite parts and platform sealing features

An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.

Airfoil assembly with ceramic matrix composite parts and load-transfer features

A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.

Turbine shroud segment having a seal segment perimeter seal with separated buffer cavities

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. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Turbine shroud segment with flange-facing perimeter seal

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

An assembly adapted for use in a gas turbine engine. The assembly includes a support component comprising metallic materials, a supported component comprising ceramic matrix composite materials, and an attachment pin configured to couple the supported component to the support component. The attachment pin includes compliant features to distributes loads applied to the supported component.

Ceramic matrix composite assembly with compliant pin attachment features

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a supported component, illustratively used as a heat shield. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

Turbine shroud assembly with hangers for ceramic matrix composite material seal segments

A turbine section for use in gas turbine engine includes a turbine case, turbine shroud rings, a turbine vane assembly, and a vane mount ring. The vane mount ring couples the turbine vane assembly to the turbine case.

Turbine section of a gas turbine engine with ceramic matrix composite vanes

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

Turbine shroud assembly with multi-piece support for ceramic matrix composite material seal segments

An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform.

An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gases from passing over turbine blades included in the gas turbine engine.

Ceramic matrix composite blade track with mounting system having axial reaction load distribution features

An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.

Ceramic matrix composite joints

An airfoil assembly includes a roller joint formed between a ceramic airfoil portion and a carrier allowing sliding (rolling) radial movement therebetween to accommodate thermal growth disparity.

Ceramic matrix composite load transfer roller joint

A turbine shroud assembly of a gas turbine engine includes a carrier, a blade track segment and a mounting assembly. The carrier is made from metallic materials. The blade track segment is made from ceramic matrix composite materials. The mounting assembly is configured to couple the blade track segment to the carrier.

Turbine shroud with ceramic matrix composite seal segments mounted to metallic carriers

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Indianapolis, IN, United States of America

Daniel Kent Vetters