Honeywell International Inc.

Glenn H Lane

Gary A Farnsworth

Louie Timothy Gaines

Paul T Wingett

Calvin C Potter

Todd Langston

David M Eschborn

David M Mathis

Douglas C Smith

James A Wissinger

Casey Hanlon

Kellan P Geck

Jimmy Wiggins

William F Ryan

Paul S Evans

Dori Marshall

John Thurston

Cal Potter

Gerhard Schroeder

Michael J Burns

Peter J Auer

Michael Kolic

A valve actuator is provided for use in conjunction with a drive motor and a valve. In one embodiment, the valve actuator includes a housing assembly, a first power screw rotatably mounted in the housing assembly and configured to be rotated by the drive motor, a first rack translatably mounted in the housing assembly, and a pinion rotatably mounted in the housing assembly and mechanically linked to the valve. The first rack is threadably coupled to the first power screw and is configured to move linearly as the first power screw rotates. The pinion engages the first rack and is configured to rotate as the first rack moves linearly to move the valve to a desired position.

Low profile valve actuator having high torque output

An actuator assembly includes a motor assembly, a harmonic drive gearbox, an actuator, and an electromagnet brake device. The actuator assembly is fairly compact in size and the electromagnetic brake device is a non-contact type of devices, making it less prone to wear as compared to many other brake devices.

Compact, electromagnetically braked actuator assembly

A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.

More electric aircraft starter-generator multi-speed transmission system

An electric motor system includes a motor brake control circuit that uses current induced in the motor stator from generated back EMF to keep the motor brake energized and in its disengaged position, should electric power be lost to the motor system. When the motor has slowed sufficiently that the induced current is no longer sufficient to keep the motor brake energized, the motor brake will move to its engaged position, and prevent further motor rotation. The motor rotational speed at which the motor brake is no longer energized is sufficiently low that any potential degradation or other deleterious effects from motor brake engagement are minimized.

Electric motor brake engagement holdup system

An aircraft engine starter assembly provides for liquid cooling of the clutch assembly and overrunning engine by integrating a pitot pump in the system. The system includes a starter motor, a torque transfer connection, a clutch assembly and the pitot pump. The torque transfer connection is adapted to be coupled to the aircraft engine. The clutch assembly is coupled to one of the starter motor or the torque transfer connection. The pitot pump is coupled to one or both of the torque transfer or the clutch assembly via a first oil line and a second oil line. The pitot pump comprises a pitot tube in fluidic communication with an oil reservoir for the delivery of oil under pressure to lubricate one or both of the torque transfer or the clutch assembly.

Air turbine starter assembly

A compressor system that is configured to compress the fluid from low pressure source to a higher pressure magnitude is powered from the same low pressure fluid source. The compressor system includes two piston assemblies that are coaxially coupled to one another, and that are of differing cross sectional areas. The low pressure fluid is used to move the larger piston assembly, which is in turn used to move the smaller piston assembly. Low pressure fluid is selectively admitted to the smaller piston assembly, and movement thereof is used to compress the low pressure fluid to a higher pressure magnitude. The compressor system uses a fluidic bistable amplifier, which also coupled to the low pressure fluid source, to control low pressure fluid flow to the larger piston assembly, to thereby control its movement.

Fluidic compressor

Methods and apparatus are provided for monitoring an aircraft accessory. The apparatus comprises a processor associated with said aircraft accessory, a transducer coupled to said processor and operable to produce parametric data relating to said aircraft accessory and a memory coupled to said processor having baseline parametric data residing therein, wherein said baseline parametric data comprises the parametric data obtained during an acceptance test procedure. The method comprises installing a transducer configured to produce parametric data relating to said aircraft accessory, coupling said transducer to a processor associated with said aircraft accessory, coupling said processor to a memory associated with said aircraft accessory, recording baseline parametric data relating to said aircraft accessory in said memory during an acceptance test procedure for said aircraft accessory.

Aircraft accessory monitor

One or more particle arrestors are mounted in a curved radial flow portion of a gas turbine starter annular flow passage, between a fluid inlet and a fluid outlet. The one or more arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the one or more arrestor rings substantially inhibit relatively high energy particles from exiting the turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

High energy particle arrestor for air turbine starters

An air turbine starter valve able to open despite being frozen shut. Dual actuators apply sufficient torque upon an air turbine starter valve to overcome obstructions presented by frozen moisture. By applying separate and generally-aligned torques, the actuators are able to provide sufficient force to overcome the adhesion provided by frozen moisture between the valve plate and adjacent structures.

Dual actuator air turbine starter valve

An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Air turbine starter with fluid flow control

One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the arrestor rings substantially inhibit relatively high energy particles from exiting the gas turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

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Chandler, AZ, United States of America

Glenn H Lane