General Electric Company

Christopher Charles Glynn

Darek Tomasz Zatorski

Roger C Walker

Richard Ludwig Schmidt

Peeyush Pankaj

Shashank Suresh Puranik

Mark Eugene Noe

Randy M Vondrell

Bhaskar Nanda Mondal

Robert Proctor

David Edward Bulman

Wu-Yang Tseng

Harold Ray Hansel

Brandon Wayne Miller

David William Crall

Toby George Darkins, Jr

Monty Lee Shelton

John David Bibler

Rolf R Hetico

Nicholas Rowe Dinsmore

Robert Paul Czachor

Richard William Albrecht, Jr

Robert Joseph Albers

John Christopher Brauer

Martin C Hemsworth

Donald Scott Yeager

Jeffrey Douglas Rambo

Mohamed Osama

Robert Francis Manning

Victor Hugo Silva Correia

Alan Roy Stuart

Darrell Glenn Senile

Steven Douglas Johnson

Ian Francis Prentice

Corey Bourassa

Rajesh Kumar

Dean Thomas Lenahan

Thomas Kupiszewski

Michael J Epstein

Bruce Clark Busbey

Jared Peter Buhler

Robert Alan Frederick

Arnab Sen

Peter W Mueller

Thomas Tracy Wallace

Michael Ray Tuertscher

Mehdi Milani Baladi

Michael Todd Radwanski

Rafael Jose Ruiz

Julius John Montgomery

Jeffrey Donald Clements

Jan Christopher Schilling

Andrew Breeze-Stringfellow

Kurt David Murrow

Jacky S Naudet

Christian Lee Vandervort

Robert J Corsmeier

Daniel Edward Mollmann

Ronghai Qu

Craig Douglas Young

Ian David Wilson

Larry W Plemmons

Richard Alan Wesling

Melvin Bobo

Jean-Louis Charbonnel

Frank Worthoff

Wei Wu

Stephen Craig Mitchell

John Michael Kern

Emil Donald Jarczynski

Andrew J Lammas

Donald Albert Bradley

Alan Majors Walker

Donald George LaChapelle

Kenneth Edward Seitzer

Marie Ann McMasters

Ely E Halila

Curtis Walton Stover

David Lawrence Bedel

Nicholas M Daggett

Kenneth Lee Fisher

Donald Lee Gardner

Kevin Joseph Barb

Paul Stuart Wilson

Joseph T Stevenson

Ramana Reddy Kollam

Pierre Debeneix

James C Przytulski

Barry Lynn Allmon

Jeffrey Glover

John A Kastl

Daniel J Marey

Kiyoung Chung

Bala Corattiyil

Richard William Jendrix

Susan Marie Hyde

Daniel Edward Wines

David Walter Parry

Peter David Toot

Robert Harold Weisgerber

A fan assembly for a gas turbine engine includes a fan actuation system, a fan blade hub, a plurality of fan blades, and a counterweight system arranged disconnected from the plurality of fan blades. The counterweight system includes a counterweight hub, and a plurality of counterweight levers each having a counterweight trunnion rotationally connected to the counterweight hub, a cantilever arm with a counterweight connected thereto. The fan blades are rotationally connected to the fan blade hub and to the fan actuation system, and the counterweight levers are rotationally connected to the counterweight hub and to the fan actuation system. The fan actuation system is arranged to correspondingly rotate each of the plurality of fan blades about a respective fan blade pitch change axis, and each of the plurality of counterweight levers about a counterweight lever rotational axis in unison.

Fan assembly for a gas turbine engine

An electric machine is provided. The electric machine defines a centerline and includes: a stator assembly; a rotor assembly rotatable relative to the stator assembly about the centerline; and an actuator coupled to the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both along the centerline between a first position and a second position, the rotor assembly positioned closer to the stator assembly when in the first position than when in the second position.

Electric machine

A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flowto a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

Monolithic tube-in matrix heat exchanger

An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

Turbine engine with annular cavity

The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.

Lube system for geared turbine section

The present application relates to a frictional damper, a frictional damper assembly and method for installing the frictional damper. The frictional damper comprises a split ring; and a disk spring positioned against the split ring and tensioned by the split ring in an installed state.

Frictional damper and method for installing the frictional damper

An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.

Assembly for particle removal

A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.

Embedded electric machine

A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Turbomachine with alternatingly spaced turbine rotor blades

A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.

Ceramic matrix composite nozzle mounted with a strut and concepts thereof

A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.

Growing community of inventors

Hamilton, OH, United States of America

Christopher Charles Glynn