Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Jeffrey Allen Walston

David John Thomas

Daniel Kent Vetters

Ted Joseph Freeman

Aaron D Sippel

Jun Shi

Michael J Whittle

Bruce Edward Varney

Eric Koenig

Tara Grant Schetzel

Alexandra Baucco

Simon James Jones

Sean E Landwehr

Andrew J Eifert

Steven Hillier

Jeffrey M Crutchfield

Peter Broadhead

Jeff Crutchfield

Paul Antony Davis

Benjamin John Bowin Lai

Andrew James Hurst

Andrew Joseph Lazur

Adam Lee Chamberlain

Adrian Lewis Harding

John Alan Weaver

Paulo Bazan

Shaling Starr

Steven Clarke

Roy Peter McIntyre

Sean Kroszner

Brad D Belcher

Roy Mcintyre

David Thomas

John A Weaver

Daniel Kentl Vetters

Andrew Hurst

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.

Vane assembly for a gas turbine engine

An article may include a substrate including a ceramic or a ceramic matrix composite. The substrate defines a hot side surface configured to face a heated gas environment and a cool side surface opposite the hot side surface. The article also includes a cool side coating on the cool side surface. The cool side coating comprises at least one material having a flow temperature equal to or slightly less than a temperature of the heated gas environment.

Cool side coating for ceramic or ceramic matrix composite article

A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.

Turbine shroud assembly with sealed pin mounting arrangement

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 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 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 turbine shroud assembly adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track segment includes a runner that extends circumferentially partway around a central axis and an attachment post that extends radially from the runner. The carrier is coupled with the attachment post to support the blade track segment relative to the central axis.

Multi-piece carrier assembly for mounting ceramic matrix composite seal segments

A turbine shroud adapted for use in a gas turbine engine includes a seal segment and an attachment unit. The seal segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The attachment unit includes a first carrier and a second carrier that cooperate to define a channel that receives at least a portion of the mount post.

Turbine shroud with friction mounted ceramic matrix composite 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

A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis. The carrier is coupled with the outer case for movement with the outer case in response to thermal expansion and contraction of the outer case during use of the turbine assembly.

Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring

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

In some examples, techniques of repairing and/or reinforcing oxide-oxide ceramic matrix composite (CMC) materials using a metallic material. In one example, a method including applying a metallic material at an edge of an oxide-oxide CMC substrate; and heating the metallic material to diffuse the metal material into the oxide-oxide CMC substrate at the edge. In another example, a method including applying a metallic material onto a damaged area of the oxide-oxide CMC; applying a reinforcing phase material onto the damaged area of the oxide-oxide CMC; and heating the metallic material to diffuse the metallic material into the oxide-oxide CMC and attach the reinforcing phase material to the damaged area of the oxide-oxide CMC.

Repair and/or reinforcement of oxide-oxide CMC

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.

Growing community of inventors

Indianapolis, IN, United States of America

Jeffrey Allen Walston