General Electric Company

Air Products and Chemicals, Inc.

Thermodyn

Nextstream Co2, LLC

Douglas Carl Hofer

Zachary William Nagel

Norman Douglas Lathrop

Narendra Digamber Joshi

Bugra Han Ertas

Nicholas William Rathay

Chiranjeev Kalra

Vitali Victor Lissianski

Vittorio Michelassi

Gregory Alexander Natsui

Edward John Sharrow

Thomas Michael Lavertu

Timothy John Sommerer

Brian Magann Rush

Corey Bourassa

Brian Gene Brzek

Andrew Maxwell Peter

Kevin Joseph Barb

Roger Allen Shisler

Daniel Mark Brown

William Dwight Gerstler

Stephen Francis Rutkowski

Ahmed Elasser

Juan Antonio Sabate

David Allan Torrey

Venkat Eswarlu Tangirala

Andrew Lee Trimmer

Adam Rasheed

Ruxi Wang

Azam Mihir Thatte

Ramanujam Ramabhadran

Anthony Holmes Furman

Michael Solomon Idelchik

Younkoo Jeong

Matthew Alexander Lehar

Thomas Frank Fric

Shashi Kiran

John Aibangbee Osaheni

Karthik Kumar Bodla

Nicholas Francis Martin

Yash Veer Singh

Adegboyega Masud Makinde

William Thomas Parry

Hongbo Cao

Gary Dwayne Mandrusiak

Ching-Jen Tang

Stephen Duane Sanborn

Edip Sevincer

Jalal Hunain Zia

Dhananjayarao Gottapu

David Graham Holmes

Amir Mujezinovic

Kenneth James Robertson

Joseph Philip DiPietro

Raymond Kenneth Overbaugh, Jr

Alison Carol Farrell

Paolo Graziosi

Ramani Mani

Richard Edwin Warren, Jr

William John Bonneau

Shishir Tiwari

Michael Joseph Boss

Rajesh Kumar Venkata Gadamsetty

Zheyu Zhang

Krishna Mainali

Alan Donn Maddaus

John Malott Cottrill

Jessica Lynn Plummer

Shridhar Shrikant Kulkarni

Nicholas Joseph Mollo

Robert James Sherwood

Chaitanya Venkata Rama Krishna Ongole

Sylvain Guillemin

Christen A Vitrone

Leonid Yulyevich Ginessin

Scott William Blackwell

Rajkeshar Singh

Ganesh Krishnamoorthy

Fuhua Ma

Rajiv Sampath

Anthony Herbert Neumayer

John Keeling

Kristin Segreto

Andrew Paul Mann

Anna Lis Laursen

Francisco J Moraga

Nikolett Sipoecz

Xianyun Bi

Martin Vysohlid

Paul Brian Wickersham

Chiranjeev Singh Kalra

Mehmet Arik

Dhananjaya Rao Gottapu

Ravindra Gopaldas Devi

Methods and systems of electrochemically machining a component are provided. The method may include applying two or more potentials to a tool electrode comprising an array of two or more individual electrodes to generate two or more electric fields in between the tool electrode and a workpiece opposite of the tool electrode, wherein each of the two or more electric fields is generated by one of the array of two or more individual electrodes.

Methods and systems of electrochemical machining

A carbon dioxide capture system includes a first heat exchanger configured to exchange heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a first turboexpander including a first compressor driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor. The carbon dioxide membrane unit is configured to separate the exhaust stream into the lean carbon dioxide effluent stream and a rich carbon dioxide effluent stream. The carbon dioxide membrane unit is further configured to channel the lean carbon dioxide effluent stream to the first heat exchanger.

System and method of recovering carbon dioxide from an exhaust gas stream

A counter-flow heat exchanger including a core region and a plenum region. The core region including a first set of heat exchanging passageways and a second set of heat exchanging passageways disposed at least partially therein. A plenum region is disposed adjacent opposed distal ends of the core region. Each of the plenum regions including a fluid inlet plenum, a fluid outlet plenum and a tube plate disposed therebetween. The first set of heat exchanging passageways is truncated and defines a first tube-side fluid flow path in a first direction. The second set of heat exchanging passageways defines a second tube-side fluid flow path in a second opposing direction. Each of the heat exchanging passageways extending from a fluid inlet plenum to a fluid outlet plenum. The tube plates and the core region include one of a cast metal formed thereabout each of the heat exchanging passageways or a braze bond formed between each of the heat exchanging passageways.

Counter-flow heat exchanger

A customizable power conversion system () is configured to operate with multiple alternating current (AC) and direct current (DC) power sources () and supplies multiple AC and DC loads (). The customizable power conversion system is also configured to be assembled from a plurality of customizable power converters (), each of which is configured to function as a building block of the customizable power conversion system. More particularly, each customizable power converter may be configured as any DC/DC, DC/AC, AC/DC, or AC/AC converter, such as any of i) an inverter, ii) a DC/DC converter for use with a photovoltaic (PV) array (or string of PV arrays), and iii) a DC/DC converter for use with an energy storage element (e.g., a battery or battery string).

Customizable power converter and customizable power conversion system

A system includes a first working fluid compressor configured to pressurize a working fluid, and a prime mover coupled to the first working fluid compressor and configured to provide a mechanical input into the first working fluid compressor. An exhaust assembly is coupled to the prime mover and is configured to receive exhaust heat from the prime mover, the exhaust assembly including a generator configured to generate electric current based on the exhaust heat received by the exhaust assembly. A second working fluid compressor includes an electric motor electrically and synchronously coupled to the generator and configured to pressurize the working fluid.

Compressor system with heat recovery

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

System and method for cooling a leading edge of a high speed vehicle

A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

Heat engines employing fluid bearing assemblies hermetically sealed with a closed flowpath for a working fluid are generally disclosed. For example, the heat engine includes a rotating drivetrain and a fluid bearing assembly. The rotating drivetrain includes a compressor section, an expander section, and a heat exchanger. The compressor section and expander section together define at least in part a closed flowpath for the flow of a working fluid. The heat exchanger is thermally coupled to the closed flowpath for adding heat to the working fluid. The fluid bearing assembly is configured to utilize the working fluid to support the rotating drivetrain. Further, the fluid bearing assembly is hermetically sealed with the closed flowpath.

Closed cycle heat engine

An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.

Axial load management system

A carbon dioxide capture system includes a first heat exchanger that exchanges heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a second heat exchanger in flow communication with the first heat exchanger. The second heat exchanger is configured to cool the exhaust stream such that a condensate is formed, and the second heat exchanger is configured to channel a condensate stream for injection into the lean carbon dioxide effluent stream. A first turboexpander including a first compressor is driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor.

At least one thermal module in fluidic communication with the one or more electronic components. The thermal module including a hydraulic motor operable to rotate a motor output shaft. The module further including a fan coupled to the motor output shaft, at least one heat exchanger in fluidic communication with the fan to provide passage therethrough of an air stream in response to rotational movement of the fan, and a conduit carrying a pressurized liquid stream through the hydraulic motor and each of the at least one heat exchanger. The pressurized liquid stream causing the motor output shaft to rotate and wherein heat in one of the air stream or the pressurized liquid stream is passed through each of the at least one heat exchanger and rejected into the other of the air stream or the pressurized liquid stream. A thermal management system including the at least one thermal module is disclosed.

Liquid driven thermal module and thermal management system

A compressor system includes a first compressor assembly including at least one first impeller. The first compressor assembly defines at least one first volute configured to receive a first working fluid from the at least one first impeller at a first pressure and a first temperature. The compressor system also includes a second compressor assembly rotatably coupled to the first compressor assembly. The second compressor assembly includes at least one second impeller rotatably coupled to the at least one first impeller. The second compressor assembly defines at least one second volute configured to receive a second working fluid from the at least one second impeller at a second pressure. Further, at least one of the following conditions exist, i.e., the first pressure is different from the second pressure and the first temperature is different from the second temperature.

Apparatus for pressurizing a fluid within a turbomachine and method of operating the same

Thermoelectric energy storage system and an associated method are disclosed. The thermoelectric energy storage system includes a first refrigeration system, a power system, a first thermal storage unit, and a second thermal storage unit. The first refrigeration system includes a first heat exchanger, a first compressor, a second heat exchanger, and a first expander. The first heat exchanger is disposed upstream relative to the first compressor. The power system includes a third heat exchanger, a second compressor, a fourth heat exchanger, a fifth heat exchanger, and a second expander. The third heat exchanger is disposed upstream relative to the fourth heat exchanger. The fifth heat exchanger is disposed downstream relative to the second expander. The first thermal storage unit is coupled to the first heat exchanger and the fifth heat exchanger. The second thermal storage unit is coupled to the first refrigeration system and the power system.

Thermoelectric energy storage system and an associated method thereof

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Clifton Park, NY, United States of America

Douglas Carl Hofer