General Electric Company

David Vickery Parker

Byron Andrew Pritchard, Jr

Robert Francis Manning

Victor Hugo Silva Correia

John Alan Manteiga

Corey Bourassa

William Collins Vining

Michael Macrorie

Wilhelm Ramon Hernandez

Paul Trimby

Christopher David King

Matthew Brian Surprenant

Megan Lynn Williams

Awot Michael Berhe

Jesse Jacob Ollove

Basuki Srivastava

Brandon Wayne Miller

Daniel Alan Niergarth

Steven Douglas Johnson

Christian Xavier Stevenson

Nathan Evan McCurdy Gibson

Jonathan Russell Ratzlaff

Ethan Patrick O'Connor

Erich Alois Krammer

Jared Peter Buhler

Giridhar Jothiprasad

Robert Carl Murray

Gregory Michael Laskowski

Stephen Joseph Waymeyer

Sean Christopher Binion

Peter Allen Andrews, Jr

David Paul Miller

Ya-tien Chiu

Caitlin Jeanne Smythe

A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.

Core air leakage redirection structures for aircraft engines

An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Axi-centrifugal compressor with variable outlet guide vanes

An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

Fuel oxygen conversion unit

A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Diffuser-deswirler for a gas turbine engine

A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.

Fluid bearing assembly

A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

A diffuser for a centrifugal compressor including an annular diffuser housing having a plurality of diffuser flow passages therethrough the housing. Each passage including a throat portion and a diffusing section with upstream and downstream diffusing portions. A diffusing passage centerline includes a linear portion extending downstream through the throat portion and the upstream diffusing portion and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion. The diffuser flow passages may have an equivalent cone angle varying non-linearly or more particularly curvilinearly downstream along curved portion. The downstream diffusing portion may be flared.

Centrifugal compressor curved diffusing passage portion

A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk carrying an array of impeller blades around its periphery; a diffuser disposed downstream of the impeller, configured to diffuse and turn airflow discharged from the impeller; an extraction scoop disposed in fluid communication with the impeller and with a plenum disposed adjacent the impeller, and a dirt collector disposed in fluid communication with the plenum and configured to trap dirt therein.

Dirt extraction apparatus for a gas turbine engine

An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles.

Engine component for a turbine engine

A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream.

Separator assembly for a gas turbine engine

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Middleton, MA, United States of America

David Vickery Parker