General Electric Company

General Electric Deutschland Holding Gmbh

Steven Douglas Johnson

Rahul Anil Bidkar

Scott Alan Schimmels

Prateek Jalan

Ravindra Shankar Ganiger

Craig Alan Gonyou

Jonathan Russell Ratzlaff

Grant Robert Portune

Jeffrey Douglas Rambo

David Raju Yamarthi

Nathan Evan McCurdy Gibson

Narendra Anand Hardikar

Brandon Wayne Miller

Robert Proctor

Neelesh Nandkumar Sarawate

Nicholas M Daggett

Nicholas Rowe Dinsmore

Antonio Guijarro Valencia

Uttara Vijay Kumar

Anand Roday

Daniel Tyler Jarboe

Christopher Charles Glynn

Deepak Trivedi

Paul Hadley Vitt

Rajesh Kumar

Rodrigo Rodriguez Erdmenger

Thomas Kupiszewski

Michael J Epstein

Mehdi Milani Baladi

Julius John Montgomery

Chandrashekhar Kandukuri

John Andrew Kemme

Kevin Randall McManus

Daniel Alan Niergarth

Christopher Edward Wolfe

Bhaskar Nanda Mondal

Richard Alan Wesling

Vidyashankar Ramasastry Buravalla

Kudum Shinde

John Carl Glessner

Mark Leonard Hopper

Arnab Sen

Mohan Kannaiah Raju

David Vickery Parker

Andrew Hudecki

Sean Christopher Binion

Stephen Joseph Waymeyer

Nageswar Rao Ganji

Quang Tue Nguyen Tran

Alok Kumar

Amit Goyal

Shalini Thimmegowda

Brian Gregg Feie

Randy Thomas Antelo

Srinivasan Swaminathan

Sanjay Vijayaraghavan

Pratish Patil

Bradley Willis Fintel

Paul Joseph Kreitzer

Efren Souza Chavez

Eric Barre

Christopher Michael Thompson

Tajinder Singh

Jose Maria Rey Villazon

Guru Venkata Dattu Jonnalagadda

Bryan Jung Woo Hong

Ton Thu Lang Giang

Himanshu Gupta

Ajith Jogi

Mallikarjun Metri

Shalabh Saxena

Chirag Kataria

Hrishi Ragesh

Kevin Randall Mcmanus

Lucas Parisot

Keith William Gary

Yu-Liang Lin

Michael Jay Epstein

A turbomachine comprises a nozzle segment including an inner shroud defining a bottom surface and a nozzle flange defining a forward side surface and an aft side surface. A floating rotor seal is coupled to the nozzle flange via a carrier flange. The carrier flange includes a forward wall and an aft wall. The nozzle flange is positioned between the forward and aft walls and a flowpath is defined therebetween. A seal pocket is defined in one of the forward wall or the aft wall and is in fluid communication with the flowpath. At least one linear seal segment is partially disposed within the seal pocket. The linear seal segment is configured to form a seal against the nozzle flange or the bottom surface in response to pressurization of the seal pocket via a working fluid in the flowpath.

Sealing system for a turbomachine

A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A seal assembly defines a primary seal at an interface of the rotor and the stator and separates an inlet plenum from an outlet plenum. The seal assembly includes one or more aspiration conduits fluidly connected to the primary seal. One or more flingers are positioned at least partially between the seal assembly and the inlet plenum that define one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits. The flingers are positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.

Seal assembly for a gas turbine engine

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 gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A floating seal assembly is disposed at an interface of the rotor and the stator to seals at least portions of the rotor and the stator relative to each other. The floating seal assembly includes one or more inertial damping elements tuned to one or more frequencies.

Gas turbine engine with inertially damped seals

A turbine engine having a stator, a rotor, and a seal assembly. The rotor being rotatable about a rotational axis. The seal assembly having a carriage assembly, a seal body and a biasing element. The carriage assembly being carried by the stator. The carriage assembly defining a seal cavity. The seal body being provided within the seal cavity.

Turbine engine with a rotor seal assembly

A compressor assembly includes a compressor casing, a blade row inside the compressor casing, first and second bleed cavities defined at first and second axial locations in the compressor casing with the second axial location at least partially overlapping the first axial location in an axial direction, and first and second bleed scoops defining first and second inlets to first and second bleed cavities, respectively. The first bleed scoop extends from a first compressor stage to the first bleed cavity to direct compressed air from the first compressor stage through the first inlet and into the first bleed cavity. The second bleed scoop defines a second inlet to the second bleed cavity. The second bleed scoop extends from a second compressor stage to the second bleed cavity to direct compressed air from the second compressor stage through the second inlet and into the second bleed cavity.

Compressor assembly for a gas turbine engine having multi-stage bleed extraction

A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by a rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face and a primary seal body of the seal slider. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor apart from the primary seal body.

Seal assembly for a rotary machine having a flexible joint

A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.

Thermal management system for a gas turbine engine

A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

Turbine engine having a compressor with an inducer

A thermal management system for a gas turbine engine includes an oil tank, a pump in fluid communication with the oil tank configured to generate a flow of oil from the oil tank, at least one heat exchanger downstream of the oil tank, and one or more thermal loads downstream of the at least one heat exchanger. The oil tank is formed from a solid-solid phase change material.

Thermal management systems having an oil tank comprising solid-solid phase change material for gas turbine engines

A variable area turbine nozzle assembly includes a guide vane including an outer centering pin defining a tab. An inner support ring is spaced radially outward from the guide vane and defines an opening and a protrusion. The protrusion is configured to engage with the tab of the outer centering pin. An outer support ring extends circumferentially around the inner support ring and defines an aperture. The outer support ring has a second coefficient of thermal expansion that is greater than or less than the first coefficient of thermal expansion. At least one linkage joins the inner support ring to the outer support ring and is configured to rotate the inner support ring circumferentially about an axial centerline of the variable area turbine nozzle assembly in response to a change in operational temperature of a combustion gas thus causing the guide vane to rotate.

Variable area turbine nozzle assembly

A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.

Multi-fluid heat exchanger

A turbine engine comprising an engine core having a rotor and a stator, and a floating seal assembly sealing at least portions of the rotor and the stator relative to a higher-pressure area and a lower-pressure area. The floating seal assembly can comprise a carriage assembly at least partially defining a seal cavity and a seal body floating within the seal cavity. The floating seal assembly can further include at least one of a seal located between the seal body and the carriage assembly, and a seal face located between the seal body and the carriage assembly.

Turbine engine with a floating seal assembly

A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.

Seal assembly for a rotor shaft of a gas turbine

A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Seal support assembly for a turbine engine

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Milford, OH, United States of America

Steven Douglas Johnson