Honeywell International Inc.

Steven Hadden

Timothy Hindle

Toren S Davis

Jack Howard Jacobs

Dennis Wayne Smith

Paul Buchele

Dale Thomas Ruebsamen

Tim Daniel Barber

Ryan Goold

Mark Alan Villela

Torey Davis

Ronald E Strong

Jim Boyd

John Douglas Gilreath

Thom Krieder

Embodiments of a three parameter, multi-axis isolator configured to limit the transmission of vibrations between a mass and a base are provided. In one embodiment, the three parameter, multi-axis isolator includes an isolator housing configured to be mounted to the base, opposing bellows sealingly mounted within the isolator housing, and a damper piston movably suspended within the isolator housing between the opposing bellows. The damper piston is configured to be coupled to the mass. The opposing bellows deflect with movement of the damper piston along multiple axes to limit the transmission of vibrations between the mass and the base.

Three parameter, multi-axis isolators, isolation systems employing the same, and methods for producing the same

Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.

Gas turbine engines including broadband damping systems and methods for producing the same

Embodiments of a thermally-conductive vibration isolator are provided, as are embodiments of a spacecraft isolation employing a plurality of thermally-conductive vibration isolators. In one embodiment, the thermally-conductive vibration isolator includes a first end portion, a second end portion substantially opposite the first end portion, and first and second load transfer paths from the first end portion to the second end portion. The first and second load transfer paths comprise a main spring and a damper in parallel with the main spring, respectively. An elongated thermal conduit, which has a thermal conductivity exceeding that of first load transfer path and the second load transfer path, extends from the first end portion to the second end portion.

Thermally-conductive vibration isolators and spacecraft isolation systems employing the same

Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

Resilient aircraft engine mounts and aircraft engine mounting systems including the same

Systems are provided for damping vibrations from a payload. In an embodiment, and by way of example only, the system includes an isolation strut and a gas line. The isolation strut includes a bellows and a piston. The bellows has a first end and a second end, the first end being enclosed, and the second end attached to the piston to define a chamber. The piston includes a damping annulus therethrough having a gas inlet and a gas outlet. The gas inlet provides flow communication to the chamber of the bellows. The gas line is coupled to the isolation strut and is in fluid communication with the gas outlet thereof. The system is hermetically sealed to contain a gas therein.

Systems for damping vibrations from a payload

A spacecraft payload, suspended by an isolator, is locked down during launch by using a compliant member to pull on a pin, clamping the payload against the launch lock. The payload is unlocked, after launch, by heating a shape memory alloy to move the pin to overcome the compliant member, releasing the payload from launch lock. The payload may be re-locked for reentry by heating another shape memory alloy to push the pin against the other shaped memory alloy.

Growing community of inventors

Peoria, AZ, United States of America

Steven Hadden