General Electric Company

Siemens Energy, Inc.

U.S. Department of Energy

Unison Industries, Inc.

John Carl Glessner

Brandon Wayne Miller

Ethan Patrick O'Connor

Mark Edward Linz

Arthur William Sibbach

William Dwight Gerstler

Hendrik Pieter Jacobus De Bock

Robert Proctor

Ian Francis Prentice

Ravindra Shankar Ganiger

Daniel Alan Niergarth

Jeffrey Douglas Rambo

David Raju Yamarthi

Daniel Jason Erno

Byron Andrew Pritchard, Jr

Scott Alan Schimmels

Steven Douglas Johnson

David James Wiebe

Robert James Bland

Biao Fang

Shiloh Montegomery Meyers

Timothy A Fox

Craig Alan Gonyou

Bernd Prade

Kevin Samuel Klasing

Brian Christopher Kemp

David Justin Brady

Michael Robert Millhaem

Michael Joseph Murray

Sheo Narain Giri

Neil Richard Garrigan

Ivan H Peterson

Andrew Hudecki

Samer P Wasif

Christopher Jon Potokar

Jeffrey Lee Mason

David M Ritland

Daniel Fusinato

Anil Gulati

Stefan Dahlke

Lawrence William Nurre

Efren Souza Chavez

Nagendra Baddam

Bradley Willis Fintel

Udo Schmitz

Norman Stanton Baylis

Karsten Jordan

Eric Barre

Stephanie Glynn Cotten

Saurya Ranjan Ray

Mark F Rubio

Daniel John Oehrle

Jarrod Paul Sands

Daniel Alexander Sieg

Mustapha Ismail

John Robert Holland

Jeffrey Scott Ksander

Jeffrey Scott Laubenthal

Dan Nicholas Mirkovich

David Kargetta

Robert O Nicosia

Charles Steve Lawless

Carlos Eduardo Gutierrez

Gabriel Walker-Santiago

James Darrell Bradley

David William Morris

Stephen A Raimer

Scott J Markovitz

A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

Gas turbine engine

A turbine engine having an inner cowl that circumscribes at least a portion of an engine core, where the inner cowl is radially spaced from the engine core. An outer cowl circumscribes at least a portion of the inner cowl where the outer cowl includes a radially outer surface spaced from a radially inner surface to define an outer cowl space. A fire box is located within a portion of the outer cowl space. An accessory device is located in the fire box.

Turbine engine having a fire box

A turbine engine having an engine core having a compression section, combustion section, a turbine section, and an engine drive shaft. The turbine engine includes an air turbine starter having a housing defining an air flow passage. The air turbine starter can operate in a start-up mode and a shut-down mode. The turbine engine further includes a gearbox and a drive unit.

Turbine engine including an air turbine starter

A turbine engine having an engine core that includes a compressor section, a combustion section, and a turbine section. An inner cowl circumscribes the engine core and an outer cowl radially spaced from the inner cowl, circumscribes at least a portion of the inner cowl. A transfer gearbox, at least partially located within an inner cowl space between the engine core and the inner cowl, operably couples to a first accessory device. An accessory gearbox located in the outer cowl operably couples to the transfer gearbox and a second accessory device.

Turbine engine including transfer gearbox and accessory gearbox

A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Accessory gearbox for a turbine engine

A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.

Compressor bleed for gas turbine engine

Example split valves for regulating a first flowrate and a second flowrate of a fluid within a closed loop systems are disclosed herein. An example split valve includes an electrohydraulic servo valve coupled to a first piston via a first hydraulic flowline and a second hydraulic flowline, the first piston to include a piston shaft, a first head, and a second head; one or more bellows fixed to at least one of the first head or the second head, the one or more bellows to hermetically seal the fluid from a hydraulic fluid; and a control system connected to the electrohydraulic servo valve, the control system to adjust the first flowrate and the second flowrate of the fluid through a first fluid chamber, the first piston to be located in the first fluid chamber.

Split valves for regulating fluid flow in closed loop systems

A turbine engine including an engine core, a nacelle, and a cowl door. The engine core including in serial, axial flow arrangement a compressor section, a combustor section, and a turbine section and defining a first airflow axially through the engine core. The nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface and an internal passage located between the exterior surface and the engine core and defining a third airflow. The cowl door located along the nacelle.

Turbine engine with a cowl door

An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.

Unducted fan turbine engine with a cowl door

An inverted heat exchanger device includes an exterior conduit elongated and extending around a center axis between a first end and second end. The exterior conduit including a body having an exterior surface, an interior surface, a center core elongated along the center axis, and plural walls extending between the center core and the interior surface. A first conduit is disposed inside the exterior conduit that includes an inlet, plural core passages, an outlet, and internal manifolds. A first fluid is configured to flow along the first conduit. A second conduit is also disposed inside the exterior conduit. The second conduit includes an inlet, plural core passages, an outlet, and internal manifolds. A second fluid is configured to flow along the second conduit. The plural walls are configured to define the first conduit and the second conduit within the body of the exterior conduit.

Inverted heat exchanger device

A turbine engine includes: a core cowl, a core within the core cowl, the core including a compressor having a bleed port; an undercowl space; a cooling duct at least partially in the undercowl space and having an inlet and an outlet, the inlet communicating with a source of cooling air, the outlet communicating with the compressor bleed port; a valve assembly in the cooling duct; and a cooling blower operable to move air flow from the inlet of the cooling duct towards the outlet of the cooling duct and into the compressor bleed port. A method of cooling an engine having a core cowl and a compressor, combustor and turbine includes: operating the engine; shutting the engine down; after or during engine shutdown, operating a cooling blower internal to the engine cowl, to force air through the compressor by way of a compressor bleed port.

Gas turbine engine reverse bleed for coking abatement

A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow.

High pressure exhaust muffling device with multiple sources

Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.

Active clearance control manifold system

A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.

Combustor apparatus in a gas turbine engine

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Kings Mills, OH, United States of America

John Carl Glessner