United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

San Quach

Steven Bruce Gautschi

Tracy A Propheter-Hinckley

Jeffrey T Morton

Matthew A Devore

Matthew D Parekh

Thomas N Slavens

Christopher King

Dominic J Mongillo, Jr

Bryan P Dube

Adam P Generale

Alberto A Mateo

Lucas Dvorozniak

Raymond C Surace

Timothy J Jennings

Nicholas M LoRicco

John S Tu

Robert M Sonntag

Tyler G Vincent

John J Rup, Jr

Sasha M Moore

John McBrien

Carey J Clum

Donald William Peters

Christopher Whitfield

Lane Mikal Thornton

Michael G McCaffrey

Christopher Corcoran

Brandon W Spangler

Mark F Zelesky

Steven D Porter

Eric A Hudson

Howard J Liles

Scott D Lewis

Robert A White, Iii

Atul Kohli

Stephen G Pixton

Alex J Schneider

Brian T Hazel

James B Hoke

Zhongtao Dai

Jason Shenny

Gregory Anselmi

Clifford J Musto

Robert Selinsky, Jr

Brandon S Donnell

Anthony Van

Winston Gregory Smiddy

David J Candelori

Russell Deibel

Steven Taffet

Daniel C Nadeau

David Donald Chapdelaine

Fred NguyenLoc

Erik R Granstand

Matthew S Gleiner

Matthew Andrew Hough

Jeffrey S Beattie

Allan N Arisi

Ryan Alan Waite

Monica Pacheco-Tougas

Andreas Sadil

Jeffrey Leon

Frank J Trzcinski

Anita L Tracy

William F Werkheiser

Joseph James Sedor

Aaron S Butler

Cheng Gao

Jeremy Styborski

Jessica L Serra

John R Battye

Scott A Elliott

Caroline Karanian

Neil B Ridgeway

Yafet Girma

Andrew Cervoni

Jaime G Ghigliotty

Christina E Botnick

Gerard V Cadieux

Kaitlin M Tomeo

Richard G Ullrich

Eva Wong

Kristy Rose Riley

Joanne V Rampersad

Lisa A Jenkins

Lisa Tse

Tracy A Propheter-hinckley

Lauryn M Curtis

Michael G Mccaffrey

Scott A Elliot

Joseph J Sedor

Robert Selinsky

John J Rup

In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

CMC stepped combustor liner

A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.

Ceramic wall seal interface cooling for an airfoil vane arc segment

An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

Flowpath assembly for gas turbine engine

In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

CMC component flow discourager flanges

A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.

Airfoil tip pocket with augmentation features

An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.

Ceramic component with support structure

Ceramic wall seal interface cooling

A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.

Engine with cooling passage circuit for air prior to ceramic component

A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.

Vane arc segment with conformal thermal insulation blanket

An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

Ceramic airfoil with cooling air turn

In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.

An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil. The second zone includes a second plurality of cooling holes that provide a second cooling density that is lower than the first cooling density such that the high temperature area and the low temperature area are balanced to lower a thermal gradient across the first and second zones of the vane airfoil. An vane airfoil and a method of assembling a ceramic matrix composite vane airfoil are also disclosed.

Baffle with impingement holes

A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

Mateface for blade outer air seals in a gas turbine engine

A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

Cooling arrangement including overlapping diffusers

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East Hartford, CT, United States of America

San Quach