Honeywell International Inc.

Honeywell Power Systems, Inc.

Mike Medhi Masoudipour

Steven Robert Eccles

Filip Reinis

Allen Hansen

Roger P Murry

Edward Mark Down

Robert A Nims

Wayne Schindler

Carol A Oximberg

Jeff A Lotterman

Chris Speights

Phung K Duong

Amanda L Anthony

Zeng Qian

Long K Duong

Michael S Yang

Thomas K Yim

A ducted ram air turbine may be used to drive a generator to provide power to an aircraft. The ducted ram air turbine may be used in a pod attached to the aircraft, where the pod is fully powered, cooled and lubricated by devices attached to the ram air turbine. A gearbox may be deployed to control the speed of the turbine for driving various pumps and the like. The speed of the turbine may be controlled by inlet and exit actuators driving inlet and exit doors.

Ducted ram air generator assembly

An apparatus for determining the fluid level of a container, such as an accumulator, may include both a remote quantity indicator and a direct quantity indicator. The remote quantity indicator may include a remote dial at the end of a flexible cable or an electrical signal receiver receiving an electrical signal from a rotary variable differential transformer (RVDT), such as a potentiometer. The RVDT type of indicator may include an electrical connector on the accumulator to attach an electrical cable to carry the quantity level signal. The direct quantity indicator may include a dial directly mounted on the accumulator. The remote/direct quantity indicators may include, for example, one of the following three combinations: 1) a dial directly on the accumulator and a remote dial at the end of a flexible cable; 2) an RVDT output and a dial directly on the accumulator; and 3) an RVDT output on an accumulator, a remote dial at the end of a flexible cable and a dial directly on the accumulator.

Accumulator with both direct and remote quantity level indication

A two-stage vapor cycle compressor includes a first stage impeller, a second stage impeller situated adjacent to the first stage impeller, an electric motor running on a pair of foil bearings, a thrust disk including two foil bearings and being positioned between the second stage impeller and the electric motor, and a compressor housing enclosing the first and second stage impeller and the electric motor. A refrigerant vapor compressed by the first stage and second stage impeller flows through an internal passageway formed by the compressor housing and cools the foil bearings and the electric motor. The compressor may be a gravity insensitive, small, and lightweight machine that may be easily assembled at low manufacturing costs. The two-stage vapor cycle compressor may be suitable for, but not limited to, applications in vapor compression refrigeration systems, such as air-conditioning systems, for example, in the aircraft and aerospace industries.

Two-stage vapor cycle compressor

A cooling jacket of an electric motor or generator includes a cylindrical inner sleeve, a cylindrical outer sleeve coaxially surrounding the inner sleeve and forming a circular space between the outer sleeve and the inner sleeve, and a passageway extending within the circular space between the outer sleeve and the inner sleeve. The passageway may be a continuous winding path that may extend axially back and forth along the circumference of said inner sleeve. An embodiment of the present invention provides a cooling jacket that is suitable for, but not limited to, applications in the aircraft and aerospace industries, for example in air-conditioning systems. The cooling jacket as in one embodiment of the present invention may be leak proof and water tight, has a compact design, and may be easily assembled and integrated into an electrically driven machine, such as an electrically driven compressor.

Electric motor cooling jacket

A cooling system for an electrical motor or generator includes a first cooling loop, a second cooling loop, and a heat exchange system. The first cooling loop may extract heat from an iron stack and winding of the electrical motor or generator. The second cooling loop may extract heat from end turns of the stator winding, the rotor, and the bearings independently from and simultaneously to the first cooling loop. At least the first cooling loop may pass through the heat exchange system. A liquid coolant may circulate in the first cooling loop and a compressed gas, such as compressed air or compressed refrigerant in vapor form, may circulate in the second cooling loop. The cooling system and method for an electrical motor or generator may be suitable for, but not limited to, applications in the aircraft and aerospace industries, such as driving a cabin air compressor of an aircraft.

Thermal and secondary flow management of electrically driven compressors

A cooling jacket resistor includes a passageway incorporated into a wall and across the entire inside length of a cooling jacket from an inside of the cooling jacket. The passageway may include at least one sump and may have a depth that inclines from a first to a second end. The cooling jacket resistor may be positioned at the lowest point of the cooling jacket when installed in an electrical motor/generator. The cooling jacket resistor may collect condensed refrigerant in liquid form and may transport the condensed refrigerant towards a drain port by gravity. The condensed refrigerant may then be drained from the cooling jacket resistor through the drain port. The cooling jacket resistor may be suitable for, but not limited to, applications in electric motors or generators that uses vapor as a coolant, for example, two-stage refrigerant cooled vapor cycle compressors.

Electric motor cooling jacket resistor

A gas turbine engine having a housing and an axially extending shaft journaled to the housing by two axially spaced apart bearings. The bearings are located along the shaft so as to define an overhung shaft portion. A rotating component such as a turbine wheel or compressor wheel is mounted on the overhung shaft portion and is concentric about the centerline ( ) of the engine. An annular shroud ( ) that is part of the housing is disposed about the rotating component, the annular shroud ( ) being concentric about a centerline ( ) radially offset from the engine ( ).

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Torrance, CA, United States of America

Mike Medhi Masoudipour