United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Thomas N Slavens

Brooks E Snyder

Mark F Zelesky

Nicholas M LoRicco

James Tilsley Auxier

Thomas J Martin

Timothy J Jennings

San Quach

Carey J Clum

Alexander Staroselsky

Joel H Wagner

Dominic J Mongillo, Jr

Matthew A Devore

Steven Bruce Gautschi

Sergey Mironets

Lane Mikal Thornton

Tracy A Propheter-Hinckley

Christopher Whitfield

Gabriel L Suciu

Brian D Merry

Daniel Bernard Kupratis

Edward F Pietraszkiewicz

JinQuan Xu

Carl R Verner

John R Farris

Tania Bhatia Kashyap

Kevin Zacchera

Michael G McCaffrey

Raymond C Surace

John Joseph Marcin

Dilip M Shah

Atul Kohli

Sasha M Moore

Mosheshe Camara-Khary Blake

John McBrien

Clifford J Musto

Andrew D Burdick

Kevin L Rugg

Albert Rabinovich

John D Teixeira

Yafet Girma

Arthur W Utay

Dipanjan Saha

Weiduo Yu

Eric A Grover

Bret M Teller

Awadh B Pandey

Hoyt Y Chang

Michael F Blair

Christopher King

David A Niezelski

Lea Kennard Castle

Alex J Schneider

Charles W Haldeman

Jeremy Styborski

Rodney H Warner

Brandon S Donnell

Sean D Bradshaw

Jaime G Ghigliotty

Jason L O'Hearn

Lisa K Osborne

Charles W Halderman

James Tisley Auxier

Nicholas M Loricco

Kevin L Zacchera

Brooke E Snyder

Nicholas M Lo Ricco

Sacha M Moore

Lane Thorton

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 assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

Cupped contour for gas turbine engine blade assembly

A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.

Enhanced adhesion thermal barrier coating

Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

Airfoil having dead-end tip flag cavity

One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

Multiple piece engine component

A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component

A method for applying a coating to a substrate having a plurality of holes. The method comprises: applying a braze material to a substrate having a plurality of holes; heating the substrate to melt the braze material to form a melt; cooling the substrate to solidify the melt to form plugs in the respective holes; applying a coating to the substrate; and further heating the substrate to melt the plugs.

Method of manufacturing conductive film holes

A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.

Gas turbine engine component with film cooling hole

A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

Additive manufactured mold, a method of manufacturing the mold, and a workpiece casted from the mold

One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

Fluidic machining method and system

A heat shield for use in a combustor of a gas turbine engine including a plurality of standoff pins that extend from a cold side, the plurality of standoff pins at least partially surround an attachment stud, the cold side including at least one film cooling hole adjacent to the plurality of standoff pins and the attachment stud.

Additive manufactured combustor heat shield

In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

Centrifugal airfoil cooling modulation

A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.

Rotating turbine vane bearing cooling

Growing community of inventors

Vernon, CT, United States of America

Thomas N Slavens