Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Joseph P Lamusga

Ted Joseph Freeman

David John Thomas

Aaron D Sippel

Daniel Kent Vetters

Richard Christopher Uskert

Andrew Joseph Lazur

Brian J Shoemaker

Rick Uskert

Jun Shi

Douglas David Dierksmeier

Sean E Landwehr

Steven Hillier

Todd Engel

Matt Brandt

Simon James Jones

Adam Lee Chamberlain

Bruce Edward Varney

Peter Broadhead

Alexandra Baucco

Larry Allen Junod

Christopher Barrett

Chris Barrett

David Thomas

John A Weaver

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

A method for fabricating a ceramic matrix composite component having a deltoid region is provided. The method includes providing a porous ceramic preform. The porous ceramic preform includes a layer-to-layer weave of ceramic fibers that forms a modified layer-to-layer woven core and at least one 2-dimensional layer of ceramic fibers that is disposed adjacent to the modified layer-to-layer woven core. The porous ceramic preform is formed into a ceramic matrix composite body having the deltoid region such that the modified layer-to-layer woven core extends through the deltoid region.

Ceramic matrix composite components having a deltoid region and methods for fabricating the same

A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

Ceramic matrix composite seal segment for a gas turbine engine

A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.

Segmented turbine shroud with sealing features

A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.

Compliant rail hanger

A turbine shroud adapted for use in a gas turbine engine includes an attachment feature and a body. The attachment feature and the body are constructed of ceramic matrix composite materials. In an illustrative embodiment, the ceramic matrix composite materials form a blade track segment.

Ceramic matrix composite blade track segments

A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.

Seal segment for a gas turbine engine

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

An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between 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 anti-rotation features

Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.

Seal segment retention ring with chordal seal feature

An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.

Pressure activated seals for a gas turbine engine

A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Blade track assembly with turbine tip clearance control

The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.

Ceramic matrix composite gas turbine engine blade

A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.

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Indianapolis, IN, United States of America

Joseph P Lamusga