Hamilton Sundstrand Corporation

United Technologies Corporation

Scott F Kaslusky

Louis J Bruno

Thomas M Zywiak

Brian St Rock

Louis J Spadaccini

Daniel R Sabatino

Vincent C Nardone

John H Whiton

Robert A McLaughlin

Foster Philip Lamm

Jeffrey T Wavering

He Huang

Michael K Sahm

Thomas Gregory Tillman

Hayden M Reeve

Young Kyu Park

Louis Chiappetta, Jr

Luca Bertuccioli

Adam M Finney

Timothy D DeValve

Yirong Jiang

Massoud Vaziri

Jaeseon Lee

David R Sobel

Robert L Bayt

Brandon M Grell

Charles Beecroft

Jeffrey David Ernst

Eric Stephen Surawski

An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Heat transfer device with fins defining air flow channels

A heat exchanger includes a plurality of channels and one or more active flow disruption members disposed at an entrance to the plurality of channels. The active flow disruption members are configured to induce unsteadiness in a flow through the plurality of channels to increase thermal energy transfer in the plurality of channels. A method for transferring thermal energy from a heat exchanger includes locating one or more active flow disruption members at an entrance to a plurality of channels of the heat exchanger. A flow is directed across the one or more active flow disruption members into the plurality of channels and an unsteadiness is produced in the flow via the one or more active flow disruption members. The unsteadiness in the flow increases the transfer of thermal energy between the heat exchanger and the flow.

Active structures for heat exchanger

A thermoelectric device () includes a plurality of conductor portions (-) including a first angled side portion () and a second angled side portion (). The thermoelectric device () also includes a plurality of conductor members (-) including a first angled side section () and a second angled side section (). A plurality of P-type thermoelectric members (-) interconnect corresponding ones of the first angled side portions () with the first angled side sections (). A plurality of N-type thermoelectric members (-) interconnect corresponding ones of the second angled side portions () with the second angled side sections (). Electric flow through the plurality of conductor portions (-) and the plurality of conductor members (-) passes along a first predefined curvilinear path and a heat flux passes along a second predefined curvilinear path.

Thermoelectric device architecture

According to one aspect of the invention, an electronics package includes an enclosure and one or more thermal energy generating components disposed in the enclosure. A radial heat sink is disposed in the enclosure including a blower disposed in the radial heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the radial heat sink. The plurality of fins define a plurality of channels having a plurality of channel exits at the perimeter of the radial heat sink. The radial heat sink configured to dissipate thermal energy from the one or more components which are arranged around the heat sink according to heat flux requirements of each component. An air inlet extends through the enclosure and is connected to the blower to direct air to the blower in a direction substantially perpendicular to the first longitudinal face and/or the second longitudinal face.

Electronics package with radial heat sink and integrated blower

A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

Transcritical fluid cooling for aerospace applications

A heat sink includes a blower located in the heat sink and a plurality of fins extending from a periphery of the blower toward a perimeter of the heat sink. The plurality of fins define a plurality of channels each having a channel inlet located at the blower and a channel exit located at the perimeter of the heat sink. The plurality of channels vary in length around the perimeter of the heat sink A velocity of an air flow from the blower at each channel inlet is substantially equal for each channel of the plurality of channels, and a total pressure drop from the channel inlet to the channel exit is substantially equal for each channel of the plurality of channels.

Non-circular radial heat sink

A heat exchanger includes one or more passages and one or more metal foam sections adjacent the passage to promote an exchange of heat relative to the passage. The metal foam section includes a nominal thermal conductivity gradient there though to provide a desirable balance of heat exchange properties within the metal foam section.

Metal foam heat exchanger

A fuel based thermal management system includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. High temperature components are arranged along the fuel flow path such that even at the higher operating temperatures the fuel operates as a heat sink to transfer heat from high temperature components to the fuel. An optimal high temperature ester-based oil permits an oil-loop to exceed current oil temperature limits and achieve a high temperature to permit efficient rejection of heat to the fuel late in the fuel flow path.

Thermal management system for an aircraft

A fuel delivery system for a gas turbine engine includes a main fuel pump supplying fuel to a fuel-metering device. The operational flow range of the fuel system is dependent on a minimum net positive suction pressure at the main pump inlet required to prevent pump cavitation. A mixture of fuel and dissolved gases increases the minimum net positive suction pressure required to prevent cavitation. A fuel de-aerator including a permeable membrane removes dissolved gases from the fuel to eliminate formation of dissolved gases. The elimination of dissolved gases from within the liquid fuel reduces the required net positive suction pressure, enabling a greater operational flow range.

Extended operability aircraft fuel delivery system

A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide the fuel to the engine, and a heat exchanger in thermal communication with the fuel to transfer heat from the heat generating sub-system to the fuel. A method of managing thermal transfer in an aircraft includes removing oxygen from a stream of a fuel fed to an engine used to drive the aircraft, transferring heat from a heat generating sub-system of the aircraft to the fuel, and combusting the fuel. A system for the thermal management of an aircraft provides for powering the aircraft, supplying a fuel deoxygenating the fuel, and transferring heat between a heat generating sub-system of the aircraft and the fuel.

System and method for thermal management

Growing community of inventors

West Hartford, CT, United States of America

Scott F Kaslusky