United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Coproration

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

San Quach

Allan N Arisi

Matthew A Devore

Steven Bruce Gautschi

Benjamin T Fisk

Mark F Zelesky

Raymond C Surace

Timothy J Jennings

Anita L Tracy

Michael G McCaffrey

Carey J Clum

Eric A Hudson

Joel H Wagner

Brandon W Spangler

Joseph W Bridges, Jr

Gregory M Dolansky

Amanda Jean Learned

Edward F Pietraszkiewicz

James Tilsley Auxier

Anthony P Cherolis

Shawn J Gregg

David P Houston

Justin D Piggush

Michael F Blair

Young H Chon

Amarnath Ramlogan

Eric P Letizia

Yongxiang D Xue

Thomas N Slavens

Jonas S Banhos

Adam P Generale

Dustin Wayne Davis

Kyle C Lana

Ron I Prihar

Rafael A Perez

Benjamin Bellows

Scott A Kovach

Jun Shi

James B Hoke

Dennis M Moura

Stephen Karl Kramer

Atul Kohli

Stanislav Kostka, Jr

John P Rizzo, Jr

Ricardo Trindade

Gordon Miller Reed

Daniel A Snyder

Alan C Barron

Anton G Banks

Craig R McGarrah

Jonathan Ortiz

Michael Parkin

Renee J Jurek

Guolin Oo

Steven Taffet

Paul M Lutjen

Timothy S Snyder

Bryan P Dube

JinQuan Xu

Steven J Bullied

John Joseph Marcin

Wendell V Twelves

Carl R Verner

Jose R Paulino

Howard J Liles

John R Farris

Matthew S Gleiner

William Arthur Sowa

Edwin Otero

Robert Russell Mayer

Jeffrey S Beattie

Matthew Andrew Hough

Christopher Whitfield

Lane Mikal Thornton

Jeffrey J DeGray

Emma J Place

Christopher King

Dave J Hyland

Mark A Boeke

David Richard Griffin

Alberto A Mateo

Mark Borja

Peter F Gero

Agnes Klucha

Jeremy B Fredette

Eric L Couch

Sarah Riley

Douglas C Jenne

Charles C Wu

Justin M Aniello

Lucas Dvorozniak

Roger Gates

Loi Cheng

Brandon S Donnell

Sergio Martins Loureiro

Garrett Kernozicky

David J Hyland

Robert L Hazzard

An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

Accessible debris separator for high pressure turbine outside diameter fed static components

A turbine blade for a gas turbine engine, including: an airfoil, the having a leading edge, a pressure side, a suction side and a trailing edge; a plurality of internal cooling cavities including a leading edge cavity, a leading edge feed passage, pressure side cooling passages, suction side cooling passages and main body cavities; the leading edge cavity extending towards the suction side; a first crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage; and a second crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage, a centerline of the first crossover row of cooling passages is located closer to the pressure side than a centerline of the second crossover row of cooling passages and the centerline of the second crossover row of cooling passages is located closer to the suction side than the centerline of the first crossover row of cooling passages, and wherein the second crossover row of cooling passages are radially staggered relative to the first crossover row of cooling passages.

Air foil with staggered cooling hole configuration

A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.

Airfoil tip cleaning and assessment systems and methods

An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.

Airfoil with axial cooling slot having diverging ramp

An inspection device is disclosed herein. In various embodiments, the inspection system device comprises: a support structure; a motor, a shaft operably coupled to the motor, the shaft extending from a first side of the support structure to a second side of the support structure, the shaft configured to couple to a bladed rotor; and a scanner moveably coupled to the support structure, the scanner configured to generate a three-dimensional model for the bladed rotor.

Airfoil tool mount

Disclosed herein is a system for slurry coating leveling. The system includes a guide frame and a scrapper apparatus coupled to the guide frame. The scrapper apparatus includes a plurality of scrapper fingers aligned substantially parallel to each other. The system also includes a contour guide coupled to the scrapper fingers. The contour guide is configured to guide movement of the scrapper fingers across a surface of a component having a slurry coating. The scrapper fingers conform to a contour profile of the surface to level the slurry coating on the surface of the component.

Slurry coating leveling

An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

Airfoil with cooling passage network having arced leading edge

A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material. A casting article is also disclosed.

Additively manufactured core

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

Airfoil with arced pedestal row

A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.

Component with feather seal slots for a gas turbine engine

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Method of forming gas turbine engine components

A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

Cooled cooling air for blade air seal through outer chamber

An airfoil section has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.

Airfoil with wall that tapers in thickness

Growing community of inventors

Manchester, CT, United States of America

Tracy A Propheter-Hinckley