Hamilton Sundstrand Corporation

Motorola Corporation

Rohr, Inc.

Motorola Mobility LLC

Goodrich Corporation

Hamilton Sundstrand Space Systems International, Inc.

Debabrata Pal

John Horowy

Ashutosh Joshi

Mark W Metzler

Craig R LeGros

Mark Hamilton Severson

Eric W Karlen

Viktor Kilchyk

Frank Z Feng

Eric Alan Carter

Charles Patrick Shepard

John Huss

Tom A Utecht

Joseph Kenneth Coldwate

Daniel M Saban

Dwight D Schmitt

Laurence D Vanek

Michael James Krenz

William Louis Wentland

Mustansir Kheraluwala

Kevin J McDunn

Robert C Cooney

Glenn C Lemmers, Jr

Daniel Roman Gamota

Martin Rabindra Pais

Andreas C Koenig

Naison E Mastrocola

Kris H Campbell

Kurt A Estes

Waleed M Said

Shin Katsumata

Francis C Belisle

Robert Scott Downing

Robert Telakowski

Huazhen Chai

John M Beck

Jonathan C Dell

Aiden Coutin

Mustansir Hussainy Kheraluwala

Clifford G Thiel

Roy D Rasmussen

Minoo D Press

Gary L Galloway

Steven Schwitters

Christina W Millot

Gary L Miles

Nhia Yang

John H Paliulis

Erika M Danckers

Joshua J Krecklow

Scott R Ganong

Brian C Konopa

Scott R Bouras

Rainer Seidel

Martinho Rabindra Pais

Harry Huazhen Chai

Richard L Downing

Milan Lucic

Deron J Staas

Irina Shmagin

Darin R Driessen

Garron K Morris

Randy P Gauvin

Terry J Milroy

Irina Konstantinonva Shmagin

Markus Dantinne

Chukwunyere Ofoegbu

Kandy Elaine Spahr

Coralyn J Saxby

Aida Virginia Bennett

John Shutts

Joseph Sukkar

Dirk Derr

Rainer J Seidel

Craig R Legros

Joshua L Krecklow

Kevin Mcdunn

Joseph A Sukkar

Kurt Estes

In accordance with at least one aspect of this disclosure, a system includes an airflow line, a main compressor disposed in the airflow line configured to receive a ram air flow and supply a compressed air flow to the air flow line, and a motor operatively connected to drive the main compressor. An air cycle machine is disposed in the airflow line downstream of the main compressor configured to receive the compressed airflow and supply a cooled cabin airflow to an aircraft cabin. A cooling line tap disposed in the airflow line downstream of the air cycle machine configured to communicate a flow of cooling air to the motor from the airflow line to supply a portion of the cooled cabin airflow to one or more portions of the motor as motor cooling air via a first cooling airflow line.

Systems and methods for cooling motors

An assembly includes a rotor shaft extending in an axial direction along a center axis of the assembly and a flange extending radially outward from the rotor shaft and circumferentially around the rotor shaft. An axial flux motor extends circumferentially around the rotor shaft. The axial flux motor includes an array of magnets, a stator support structure, and a plurality of coils. The array of magnets extending circumferentially around the rotor shaft. The stator support structure extends circumferentially around the rotor shaft and faces the flange. The plurality of coils extends circumferentially around the rotor shaft and faces the array of magnets in the axial direction. Each coil of the plurality of coils includes bearing windings and torque generating windings on the stator support structure. Both the bearing windings and the torque generating windings face the array of magnets in the axial direction.

Mixed flux motor with integrated journal and thrust bearings

A ram air turbine assembly includes one or more airfoils and a ram turbine operably connected to the one or more airfoils. The ram air turbine includes: a rotor; a stator that includes windings; and a self-regulating heater coupled to the stator. The self-regulating heater configured to vary power that passes through it based on a temperature of the heater.

Smart heater for aircraft generator freeze protection

A system for cooling a cabin air compressor (CAC) motor includes a water separator which extracts water from airflow through a turbine and/or a fuel cell, and a CAC motor including cooling channels connected to an inlet and an outlet. The inlet of the CAC motor receives water from the water separator. The steam at the outlet of the CAC motor can be repurposed for warming utilities in an aircraft cabin, or for de-icing or increasing enthalpy of the turbine. The cooling water flow can be directed to the CAC motor in response to a predicted temperature of the CAC motor exceeding a threshold. The predicted temperature can be generated by feeding inputs including CAC motor input power measured by a power sensor, differential pressure measured by a pressure sensor, and a temperature at an air cooling inlet measured by a temperature sensor to a processor which generates a map model.

CAC motor auxiliary water cooling system

A liquid-cooled rectifier assembly includes first and second bus bars, each having at least one cooling channel formed therein, which are adapted and configured to carry a cooling fluid therethrough, and a first power diode array arranged between and in contact with the first and second bus bars. A third bus bar can be provided, along with a second power diode array.

Oil-cooled rectifier diode assembly

A vehicle includes a body, at least one propulsion system including an electric component, a strut extending between the body and the at least one propulsion system, and a cooling system operably coupled to the electric component of the at least one propulsion system. A portion of the cooling system is arranged within the strut.

Motor cooling system

A cooling system of a power generation system includes a generator cooling circuit having a first cooling fluid circulating therethrough. The generator cooling circuit includes a generator heat exchanger fluidly connected to a generator of the power generation system via the generator cooling circuit to cool the generator. A power converter cooling circuit has a second cooling fluid different from the first cooling fluid circulating therethrough. The power converter cooling circuit includes a power converter heat exchanger fluidly connected to a power converter of the power generation system via the power converter cooling circuit to cool the power converter.

Power generator cooling system

A rotor for an electrical machine includes a core including a plurality of rotor poles circumferentially spaced apart from one another about a hub. A winding is wound about the rotor poles. The winding passes longitudinally through a respective winding gap between each circumferentially adjacent pair of rotor poles. A cooling tube extends through at least one of the respective winding gaps.

Embedded liquid cooled rotor cooling

In accordance with at least one aspect of this disclosure, a power distribution system having integrated cooling includes a chassis defining an interior cavity, an electronics bus structure housed within the interior cavity, and an electrical contactor operatively connected to the electronics bus structure to receive a voltage therefrom. One or more heat dissipation fins can be included extending away from the chassis and configured to dissipate heat from the electronics bus structure to an ambient environment external to the chassis. In embodiments, the electronics bus structure can be sealed within the interior cavity.

Cooling for power distribution systems

A system for cooling a motor operating within an aircraft system includes an enclosure receiving ram air from a first ram air duct and discharging ram air to a second ram air duct to form a cooling path. The second ram air duct is discrete and independent from the second ram air duct. The system can discharge ram air between a heat exchanger and a fan within the second ram air duct that define a reduced or negative pressure region within the second ram air duct.

Component cooling and cooling air flow generation from remote heat exchanger

A wedge for a wound rotor includes a wedge body. The wedge body has a first layer and one or more second layers interfused with one another to provide structural support and limit resistive heating of the wedge from current flow within the wedge body by windings spaced apart by the rotor wedge. Generator rotors and methods of making generator rotors are also described.

Method of making a triangular rotor wedge with different layers having titanium

A transformer includes a housing having a base wall, a first side wall, a second side opposing wall, a third side wall joining the first side wall and the second side wall at a first end including a first cooling channel joining the first side wall and the second side wall at a first end, and a fourth side wall including joining the first side wall and the second side wall at a second end. The first, second, third, and fourth side walls collectively define an interior portion. A cover extends across each of the first side wall the second side wall, the third side wall, and the fourth side wall. A cooling system includes a first cooling channel disposed in the third side wall, a second cooling channel disposed in the fourth side wall, and a third cooling channel disposed in the cover.

Cooling system for a transformer and a method of cooling a transformer

A system comprises a stator core defining a plurality of winding slots between circumferentially spaced apart teeth. A respective cooling channel is defined within each of the circumferentially spaced apart teeth for circulation of coolant fluid through the stator core. The stator core is a laminated structure, where the teeth, winding slots, and cooling channels are part of a common laminated structure with the stator core.

Two phase cooling for electric machine

An thermal management system including, a body having a coolant passage in thermal communication with an electronic device, a first heat exchanger fluidically connected to the coolant passage configured to receive the coolant from the coolant passage, a second heat exchanger fluidically connected to the first heat exchanger, and a generator fluidically connected to the second heat exchanger.

Thermal management system and method of use

The present disclosure provides air cooling systems and methods for propulsion systems (e.g., aviation or aerospace propulsion systems). More particularly, the present disclosure provides integrated air cooling systems and methods utilizing air cycle machine cooling for hybrid-electric aircraft or aerospace propulsion systems or the like. The present disclosure provides integrated air cycle machine cooling into the hybrid propulsion system (e.g., into the wing-mounted hybrid propulsion system). As such, the air cooling systems and methods of the present disclosure can minimize weight while improving electric motor/generator cooling.

Hybrid propulsion system with integrated air-cooling system

Growing community of inventors

Hoffman Estates, IL, United States of America

Debabrata Pal