Honeywell International Inc.

Alliedsignal Inc.

David M Mathis

Kellan P Geck

Louie Timothy Gaines

William Lee Giesler

Todd Langston

Brent Bristol

Glenn H Lane

Jennifer L Zonneveld

Casey Hanlon

Calvin C Potter

James Hall

Kevin K Chakkera

David M Eschborn

William F Ryan

Paul S Evans

William Facinelli

Gary A Farnsworth

David P Gentile

John Thurston

Remo Neri

Scott C Meyers

Ronald A Peck

James A Wissinger

Marvin K Collins

Cynthia S Byers

Eugene A Zanelli

Jonathan S Hager

Paulynn Dong

Robert Bons

Steven W Trimble

James A Hall

Jennifer L Zonnerveld

A torque limiter for use on an aircraft comprises a drive shaft having a toothed outer portion, an output shaft, and a spline having an aperture therethrough for receiving the toothed portion. The spline is configured to rotationally couple the drive shaft to the output shaft and to rotationally disengage from the output shaft when the torque at the drive shaft exceeds a predetermined torque threshold. The spline comprises an outer annular portion and an inner annular portion configured to receive a lubricant. The inner annular portion comprises a plurality of circumferentially-spaced tooth structures and root structures. At least one of the root structures has at least one slot therein for receiving and retaining the lubricant.

Spline with lubricant retention feature for use in torque limiter

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

A lubrication system for supplying lubricants between two environments is provided. The first environment is disposed within a first housing and the second environment is disposed within a second housing having a supply opening and an exhaust opening. The system includes a lubricant supply tube disposed within the supply opening and configured to supply lubricant from the first environment to the second environment. The system also includes a receptacle disposed within the second housing and configured to receive lubricant supplied from the supply tube and to hold a predetermined volume of the lubricant. A check valve is disposed within the second housing and is in fluid communication with the exhaust opening. The check valve is configured to receive overflow lubricant from the receptacle, if the lubricant exceeds the predetermined volume and to provide a seal between the first and second environments in response to a pressure differential therebetween.

Accessory lubrication system for a turbine plant

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

A shroud is provided for separating an air turbine starter housing from a turbine wheel. The shroud comprises a ring and a bumper. The ring is configured to be disposed between the turbine wheel and the housing and has an outer peripheral surface and an inner peripheral surface that defines a flow channel. The bumper is coupled to and extends radially inwardly from the ring inner peripheral surface and defines a bumper section of the ring flow channel. At least a portion of the bumper section has a cross-sectional flow area that is less than another cross sectional flow area of the ring flow channel.

Shroud for an air turbine starter

An air turbine starter (ATS) configured to couple to a gearbox, the ATS including an output shaft having an outer peripheral surface, a gearbox section, and an ATS section, the gearbox section configured to be disposed within, and coupled to, the gearbox and the ATS section configured to be disposed within the ATS, and a shield plate extending radially from the outer peripheral surface and coupled to the ATS section of the output shaft.

Air turbine starter enhancement for clearance seal utilization

An air turbine starter is provided that includes a check valve assembly for placement between a first environment, at least a portion of which is at a first pressure (P), and a second environment, at least a portion of which is at a second pressure (P), wherein the difference between the first and second pressures generate a pressure force (F). The check valve assembly comprises a valve element disposed between the valve seat and the valve body, the valve element capable of being acted upon by a gravitational force (F), a viscous force of the fluid to be communicated between the gearbox assembly and the starter housing (F), a buoyancy force of the valve element (F), and the pressure force on the valve element (F), the valve element further configured to translate axially to a closed position when P&#x3c;Pand F&#x3c;F+F+F.

Air turbine starter having a force balanced, pressure energized, weighted check valve

An improved oil seal is provided for sealing passage of rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a slinger rotor mounted on the shaft for rotation therewith. The slinger rotor has an inner surface with an annular cavity and axially extending lands separated from each other by axially extending slots. The cavity and slots define a low velocity zone in which oil is centrifuged out. The slots and cavity so the centrifuged oil flows away from the end wall of the bearing housing. A labyrinth, air seal is disposed between the shaft and end wall.

Oil seal for a high speed rotating shaft

An underwater vehicle such as a torpedo has a jet pump propulsion system. A high speed pump is located inside a rigid cylindrical housing of the torpedo near an end thereof. A water inlet communicates with the pump as does a water outlet provided at the aft end of the rigid housing via a water passage. A high speed electrical motor, on the order of 10,000 rpm, is provided inside an inner cylindrical housing disposed within the outer cylindrical housing. The electric motor is provided aft of the pump and the electric motor shaft is directly coupled to the pump rotor. Only one bearing and one water seal is provided between the electric motor and pump rotor. A water exit passage is provided between the inner cylindrical housing containing the high speed motor and the rigid outer cylindrical housing. Water passing through the exit passage cools the electric motor by dissipating heat therefrom. Motor control electronics can be provided immediately aft of the high speed electric motor, in which case water passing through the exit passage also serves to cool the motor electronics by dissipating heat therefrom.

Underwater vehicle with improved jet pump propulsion configuration

A process for operating a closed Brayton-cycle engine (14) at two substantially differrent levels of output power by selectively changing the molecular weight of the working fluid, and an engine adapted for use with the process.

Method for operating a closed Brayton engine and engine adapted for use

Growing community of inventors

Phoenix, AZ, United States of America

David M Mathis