General Electric Company

Unison Industries, Inc.

Ge Aviation Systems Limited

U.S. Department of Energy

Gelcore, LLC

William Dwight Gerstler

Daniel Jason Erno

Hendrik Pieter Jacobus De Bock

Mehmet Arik

Michael Thomas Kenworthy

Jeffrey Douglas Rambo

Brian Magann Rush

Bryan Patrick Whalen

Ri Li

Corey Bourassa

Carlos Enrique Diaz

Xiaochun Shen

Brandon Wayne Miller

Daniel Alan Niergarth

Benjamin Jon Vander Ploeg

Manoj Ramprasad Shah

James Pellegrino Alexander

Christopher Anthony Kaminski

Ayman Mohamed Fawzi EL-Refaie

Todd Garrett Wetzel

Nicholas William Rathay

Thomas Kupiszewski

Emil Donald Jarczynski

Murtuza Lokhandwalla

Michael Ralph Storage

Chiranjeev Kalra

Nicolas Kristopher Sabo

Bugra Han Ertas

Lembit Salasoo

James William Bray

Yogen Vishwas Utturkar

Konrad Roman Weeber

Biao Fang

Eric Richard Westervelt

Stefano Angelo Mario Lassini

John Carl Glessner

Naveenan Thiagarajan

Lana Maria Osusky

Neil Richard Garrigan

Florian Stefan Hoefler

Nicholas Taylor Moore

Jeffrey Russell Bult

Evangelos Trifon Laskaris

Jie Jerry Liu

Anil Raj Duggal

Narendra Digamber Joshi

Anant Achyut Setlur

Christopher Edward Wolfe

Stanton Earl Weaver, Jr

Trevor Howard Wood

Kishore Ramakrishnan

Douglas Carl Hofer

Stephen Francis Rutkowski

Pazhayannur Ramanathan Subramanian

David Allan Torrey

Cherik T Bulkes

John Russell Yagielski

Warren F Bessler

James Michael Fogarty

Ronghai Qu

Jeremy Daniel Van Dam

Changjie Sun

Weijun Yin

Brian Gene Brzek

Bruce P Biederman

Joseph Lucian Smolenski

Ralph James Carl, Jr

Michael John Bowman

Mark Steven Honkomp

Robert Michael Zirin

Richard Alfred Beaupre

James Albert Tallman

Bulent Aksel

Kevin Robert Feldmann

Michael J Epstein

Mustafa Tekin Dokucu

Laura Cerully Dial

Patel Bhageerath Reddy

Eyitayo James Owoeye

Kiruba Sivasubramaniam Haran

Brian Lewis Devendorf

Charles Adrian Becker

James Claude Carnahan

Karthik Kumar Bodla

David Justin Brady

James Michael Kostka

Matthew Robert Cerny

Adegboyega Masud Makinde

Michael Joseph Murray

Blake Weldon Wilson

Steven Joseph Brzozowski

Daniel P Smith

Kevin Edward Hinderliter

Gary Dwayne Mandrusiak

Tsarafidy Raminosoa

Ken Ivcar Salas Nobrega

Jeremy Daniel VanDam

Voramon Supatarawanich Dheeradhada

Ching-Jen Tang

Vaibhav Bahadur

A heat exchanger includes a core defining a first passageway for a first fluid flow and a second passageway for a second fluid flow. The core includes an assembly of a plurality of unit cells coupled together. Each unit cell defines a first passageway portion within an interior volume and a second passageway portion at an exterior surface. Each unit cell includes a plurality of first openings into the interior volume and forms the second passageway in volumes between the plurality of unit cells. The assembly is shaped to combine and divide the first fluid in the first passageway portion and combine and divide the second fluid in the second passageway portion during exchange of heat between the first fluid and the second fluid. Each second passageway portion receives the second fluid from three other second passageway portions. The heat exchanger further includes at least one baffle in at least one of the first passageway or the second passageway to route the first fluid flow independently from the second fluid flow.

Multifurcating heat exchanger with independent baffles

A heat exchanger for a gas turbine engine includes an outer shell extending between a first end and a second end opposite the first end. The outer shell defines a first fluid chamber, a first fluid inlet adjacent the first end, and a first fluid outlet adjacent the second end. The outer shell also defines a first plurality of second fluid inlet openings located between the first end and the second end and a second fluid outlet adjacent the second end. The heat exchanger includes a manifold disposed within the outer shell. The manifold defines a second fluid chamber and a second plurality of second fluid inlet openings. The heat exchanger defines a first fluid pathway and a second fluid pathway.

Heat exchangers for gas turbine engines

Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.

Airfoils for turbofan engines

A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.

Heat exchanger including furcating unit cells

According to one embodiment, a thermal management system for electronic devices, including a heat frame, a conformal slot portion, chassis frame, and heat fins wherein the heat frame, conformal slot, chassis frame, and heat fins are integrally formed as a unitary structure by additive manufacturing. In another example, there is a modular vapor assembly for electronic components having a vapor chamber comprising a component surface and a top surface with a vapor channel formed therebetween with at least one liquid receptacle and having a wick structure on at least some of an interior of the component surface. In operation, there is a circuit card with at least some of the electronic components coupled to the vapor chamber component surface and the wick structures transfer at least some of the liquid from the receptacle towards the electronic components, wherein the liquid turns to a vapor that moves towards the receptacle.

Systems and methods for using additive manufacturing for thermal management

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 cooling system includes a conduit extending from an upstream end to a downstream end and retains a gas. A heat exchanger is fluidly coupled with and disposed within a surface of the conduit. A portion of the gas is directed into the heat exchanger via one or more passages extending between the conduit and the heat exchanger, and a portion of the gas is directed out of the heat exchanger via the one or more passages. The heat exchanger directs cooling fluid in one or more directions within the heat exchanger along one or more passageways of plural passageways. The heat exchanger directs the portion of the gas in one or more directions within the heat exchanger along one or more other passageways of the plural passageways. The heat exchanger cools the gas by exchanging heat from the gas to the cooling fluid within the heat exchanger.

Cooling system for an engine assembly

A thermal structure for management of thermal energy, the thermal structure including: a first wall structure defining a first cavity; a second wall structure defining a second cavity, the second cavity in fluid communication with the first cavity; and a barrier cavity defined at least in-part by the first wall structure and the second wall structure, wherein the barrier cavity is disposed between the first cavity and the second cavity and includes a pressurized barrier fluid therein or is configured to receive the pressurized barrier fluid during operation of the thermal structure.

Pressure equilibrated thermal insulation gap

A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Heat exchanger and leak detection system

The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.

Electric motor having an integrated cooling system and methods of cooling an electric motor

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

An aerospace vehicle including: a body, wherein the body is configured to generate heat during operation; a coating disposed over at least a portion of the body, the coating being configured to shift a frequency of at least one wavelength of the heat generated by the body from a first frequency to a second frequency having higher transmissivity relative to a neighboring medium surrounding the body as compared to the first frequency.

Aerospace vehicles with coatings for heat radiation and associated methods

A heat exchanger is provided. The heat exchanger provides a first plurality of tubes and a second plurality of flow passages which furcate near one of the first and second manifolds into two or more furcated flow passages and subsequently converge to exit the heat exchanger. The plurality of furcated flow passages are intertwined, reducing the distance between flow passages containing each fluid therebetween to improve thermal transfer. Further, the furcations create changes of direction of the fluid to re-establish new thermal boundary layers within the flow passages to further reduce resistance to thermal transfer.

Multi-branch furcating flow heat exchanger

A powered system that has an electric power system with a stator having plural poles with each pole having a conductive winding that may surround the corresponding pole and may be configured to generate a magnetic field, and a rotor that may be configured to rotate in response to the magnetic field generated by the stator. The at least one of the conductive windings may be insulated with an insulation material configured to conduct heat from the at least one conductive winding while operating at a temperature above 600&#xb0; C.

Electric power system for hypersonic speed operation

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Niskayuna, NY, United States of America

William Dwight Gerstler