Honeywell International Inc.

Alliedsignal Inc.

Gary A Farnsworth

Glenn H Lane

Kellan P Geck

Douglas C Smith

Casey Hanlon

Calvin C Potter

Louie Timothy Gaines

William Lee Giesler

Larry K Ball

Todd Langston

David M Eschborn

David M Mathis

Paul S Evans

Gerhard Schroeder

Jonathan S Hager

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 passive ATS lubrication system is provided that includes a starter housing, a receptacle and two valves. The starter housing is adapted to couple to a gearbox assembly and includes a supply opening and an exhaust opening that are each configured to provide fluid communication between the gearbox assembly and the starter housing. The receptacle is coupled to the starter housing proximate the supply opening to thereby define a reservoir. The first valve is disposed within the reservoir and configured to open or close the supply opening in response to a pressure differential between the starter housing and the gearbox assembly. The second valve is coupled to the starter housing proximate to the exhaust opening and configured to open or close the exhaust opening in response to the pressure differential between the starter housing and the gearbox assembly.

Passive improved air turbine starter lubrication system

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 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.

A decoupling apparatus for disconnecting an engine starter from an engine includes a first rotatable decoupler shaft, having a first clutch jaw, coaxially mounted with respect to a second rotatable decoupler shaft having a second clutch jaw. The two shafts can translate relative to each other from a first position in which the first and second clutch jaws are engaged to a second position in which the jaws are disengaged. A torsional shear pin with a unitary shaft has a first end in contact with a resilient member and a second end attached to the first decoupler shaft, thereby urging the first and second decoupler shafts into the first position. The torsional shear pin is frangible in response to angular movement of the first decoupler shaft relative to the second decoupler shaft to release the axially compressive force, thereby permitting the first and second decoupler shafts to move into the second position.

Shaft decoupler

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 includes a radially outwardly extending slinger ring with radially open slinger ports formed therein, in combination with an axially projecting centrifuge sleeve defining an internal tapered centrifuge surface disposed in close running clearance with an axially projecting cylindrical wall segment on the end wall. During shaft rotation, the centrifuge surface pumps oil in a direction away from the end wall to the slinger ring for discharge through the slinger ports to the interior of the bearing housing. In addition, in the preferred form, the slinger rotor has an internal bore with axially extending lands for press-fit mounting onto the rotating shaft, wherein the lands are separated by ramped slots defining additional tapered centrifuge surfaces for pumping oil away from the end wall of the bearing housing.

Growing community of inventors

Mesa, AZ, United States of America

Gary A Farnsworth