Carrier Corporation

Hamilton Sundstrand Corporation

Other

Delphi Technologies, Inc.

Jules Ricardo Munoz

Luca Bertuccioli

Parmesh Verma

Charles E Lents

Michael F Taras

Abbas A Alahyari

Jay Fletcher

Yirong Jiang

Tobias H Sienel

Thomas D Radcliff

Joseph J Sangiovanni

Michael K Sahm

Richard C Welch

Young Kyu Park

Arthur Curtis Becker

Steve Squier

Jack Leon Esformes

Frederick James Cogswell

Vladimir Blasko

Arindom Joardar

John H Whiton

Henry E Beamer

Mikhail B Gorbounov

Bruce J Poplawski

Alexander Chen

Steven E Squier

David E Samuelson

Mohsen Farzad

Jeffrey T Benoit

Miad Yazdani

Robert Michael Runk

Mel Woldesemayat

Roger W Radomsky, Jr

Arthur Chris Becker

Salvatore Macri

Jinsang Ryu

Vivek Halwan

Sunghan Jung

Veena Sharmila Sologar Thompson

Seshadri Sivakumar

Michael D Ford

Thomas McGreevy

Salvatore MacRi

Tiziano Conti

Jifeng Zhang

Seshardi Sivakumar

Young K Park

Douglas C Wintersteen

Bruce Dittly

A refrigerant system includes a first, substantially outdoor, two phase heat transfer fluid vapor compression circulation loop including a compressor, a heat exchanger condenser, an expansion device, and the heat absorption side of a heat exchanger evaporator condenser, connected by conduit in a closed loop and having disposed therein a first heat transfer fluid having a critical temperature of greater than or equal to 31.2&#xb0; C. The system also includes a second, at least partially indoor, two phase heat transfer fluid circulation loop that transfers heat to the first loop through the heat exchanger evaporator condenser. The second loop includes the heat rejection side of the heat exchanger evaporator condenser, a liquid pump, and a heat exchanger evaporator, connected by conduit in a closed loop and having disposed therein a second heat transfer fluid that has an ASHRAE Class A toxicity rating and an ASHRAE Class 1 or 2L flammability rating.

High efficiency refrigeration system

An air-cooled chiller system includes a heat exchanger including a first tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship; a second tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship, the second tube bank disposed behind the first tube bank with a leading edge of the second tube bank spaced from a trailing edge of the first tube bank; a fan creating an airflow across the first heat exchanger, the airflow flowing over the first tube bank prior to flowing over the second tube bank, wherein refrigerant flows in the heat exchanger in a cross-counterflow direction opposite that of the airflow direction.

Heat exchanger for air-cooled chiller

A multi-pass heat exchanger having a return manifold with a partition, a front wall, and a rear wall is provided. The partition separates the return manifold into a collection chamber and a distribution chamber. The front and rear walls define a fluid channel. The front wall has a plurality of perforations placing the fluid channel in separate fluid communication with the collection chamber and the distribution chamber.

Multi-pass heat exchangers having return manifolds with distributing inserts

An inlet header of a microchannel heat exchanger is provided with a first insert disposed within the inlet header and extending substantially the length thereof, and having a plurality of openings for the flow of refrigerant into the internal confines of the inlet header and then to the channels. A second insert, disposed within the first insert, extends substantially the length of the first insert and is of increasing cross sectional area toward its downstream end such that annular cavity is formed between the first and second insert. The annular cavity of decreasing cross sectional area provides for the maintenance of a substantially constant mass flux of the refrigerant along the length of the annulus so as to thereby maintain an annular flow regime of the liquid and thereby promote uniform flow distribution to the channels.

Minichannel heat exchanger header insert for distribution

An absorption chiller assembly () includes a low-stage generator () that utilizes heat from vapor resulting from operation of a high-stage generator () and heat from another hot liquid such as coolant fluid associated with a prime mover (). An example low-stage generator () includes an arrangement of conduits for directing flow of the two heat sources through the low-stage generator in a manner that both sources simultaneously interact with a refrigerant solution within the low-stage generator. A disclosed example includes an integrated diverter valve that is preassembled and packaged within an absorption chiller assembly. A disclosed heating mode in one example includes using an absorber () and a condenser () for heating fluid useful for heating operations.

Dual gas and hot liquid absorption chiller assembly

The present invention relates to A reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

Reduced bleed vapor compression cycle environmental control system for aircraft

The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Integrated system for providing aircraft environmental control

The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

Integrated air turbine driven system for providing aircraft environmental control

The present invention relates to a vapor compression cycle environmental control system for use on aircraft. The system includes an environmental control subsystem which supplies pressurized ram air at a desired temperature to the aircraft's flight deck and/or cabin. The environmental control subsystem uses a vapor compression cycle subsystem to provide the ram air at the desired temperature. The system further includes an air turbine driven by engine bleed air to provide power to an aircraft mounted accessory drive and to provide heated air to an anti-ice system. The aircraft mounted accessory drive provides power to an air compressor which forms part of the environmental control subsystem and to a working fluid compressor which forms part of the vapor compression cycle subsystem.

Vapor compression cycle environmental control system

Growing community of inventors

South Windsor, CT, United States of America

Jules Ricardo Munoz