Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce High Temperature Composites Inc.

Rolls-royce American Technologies, Inc.

Rolls-roye Corporation

Aaron D Sippel

Ted Joseph Freeman

David John Thomas

Daniel Kent Vetters

Jeffrey Allen Walston

Joseph P Lamusga

Clark Snyder

Alexandra Baucco

Jun Shi

Sean E Landwehr

Bruce Edward Varney

Steven Hillier

Peter Broadhead

Richard Christopher Uskert

Andrew J Eifert

Thomas Nixon

Simon James Jones

Jeffrey M Crutchfield

Paulo Bazan

Donald W Reinhart

Adam Lee Chamberlain

Anthony G Razzell

Robert J Shinavski

Brian J Shoemaker

Paul Antony Davis

Shaling Starr

Loic Fabries

Michael J Whittle

Andrew Joseph Lazur

Jack Dwane Petty, Sr

Gregory W Zeaton

Jeffrey A Stone

Grant Cook

Zacheriah A Cole

Sungbo Shim

Roderick M Townes

Jay Edgar Lane

Stephen Isaiah Harris

Taylor K Blair

Todd Engel

Adrian Lewis Harding

Keith C Sadler

John Alan Weaver

Robert F Proctor

Joseph Gordon Doyle

Tara Grant Schetzel

James Sellhorn

Emil R Dejulio

William Westphal

Christopher Barrett

Chris Barrett

Peter J Loftus

Michael Jacquinto

Wesley Thibault

Andrew Glucklich

Brad D Belcher

Christopher Downie

Keith Sadler

David Thomas

Joseph Pan Lamusga

John A Weaver

Jeffrey A Walston

Ted J Freeman

David J Thomas

Bruce E Varney

An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.

Pin mounted ceramic matrix composite heat shields with impingement cooling

An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.

Turbine shroud assembly with angled cooling holes

A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Turbine shroud assemblies with strip seals

A turbine shroud assembly for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system is arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Turbine shroud assemblies with air activated pistons for biasing buffer cavity seals

In some examples, article used as a component for a turbine engine that operates in a high temperature environment. The article may include: a ceramic or ceramic matrix composite (CMC) substrate; and a coating on the ceramic or the CMC substrate, wherein the coating defines an outer surface of the article. The coating includes a plurality of surface features defining channels on the outer surface of the article. The channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article.

Article with surface structures for CMAS resistance

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Turbine shroud assemblies with channels for buffer cavity seal thermal management

A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Turbine shroud assemblies with rod seal and strip seals

A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.

Locating plate for use with turbine shroud assemblies

A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.

Turbine assembly with confronting vane and turbine shroud segment

Turbine shroud assemblies with inter-segment strip seal

A turbine assembly includes a turbine case, a turbine shroud assembly including a carrier segment, and a locating plate. The locating plate is coupled with the turbine case axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the carrier segment from the turbine case. The locating plate includes a main wall, a raised portion extending upwardly a first radial distance, and two circumferentially spaced apart extensions extending upwardly a second radial distance. The second radial distance is greater than the first radial distance such that, in a first arrangement, only the extensions contact the turbine case and such that, in a second arrangement, the raised portion is pulled toward the turbine case via a fastener so as to contact the turbine case in addition to the extensions.

A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall. The second shroud segment includes a second carrier segment and a second blade track. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Turbine shroud system with ceramic matrix composite segments and dual inter-segment seals

A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Turbine shroud assembly with inter-segment damping

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Turbine shroud assembly with pinned shroud attachment

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Method and apparatus for ceramic matrix composite turbine shroud assembly

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Zionsville, IN, United States of America

Aaron D Sippel