Hutchinson Aerospace & Industry Limited

Barry Controls Corp.

Ivan Roson

Iman Shahosseini

John Nall

Luigi Max Maggi

A vibration isolation device comprises a frame for mounting on an engine casing, an axis to be mounted to an external component to isolate, a resilient member located between the frame and the axis, and a fuse mechanism ensuring that the vibration isolation device presents a first stiffness when loads applied to said vibration isolation device are below a predetermined threshold load, and a second stiffness, lower than the first stiffness, when loads applied to the vibration isolation device are at least equal to the predetermined threshold load. The fuse mechanism constrains the resilient member within a predetermined space when loads applied to the vibration isolation device are below the predetermined threshold load and to release the resilient member so that this latter is capable of deforming beyond said predetermined space when loads applied to the vibration isolation device are at least equal to the predetermined threshold load.

Vibration isolation device, especially for aircraft applications

A hydraulic torque compensation device comprises a pair of housings, a first housing including a first high pressure liquid chamber and a second low pressure liquid chambers, a second housing having a third high pressure liquid chamber, a fourth accumulator chamber, and a fifth low pressure chamber that is defined by a wall and an end of the second housing. A first main duct links the first chamber of the first housing to the third chamber of the second housing. A second main duct links the second chamber of the first housing to the fifth chamber of the second housing. Each housing also include a piston, the first chamber between a first piston body and an end of the first housing and the third chamber between a second piston body and the wall. The device ensures a counter action to engine loads when a positive torque is applied.

Hydraulic torque compensation device

The invention proposes to address the vibration transfer function transmitted by a turbo-fan engine or equivalent to the aircraft structure, with two types of isolators mounted on a unique assembly but with a different physical response to the transfer function, an absorbing one and a resonating one. The difference in nature of such responses induces a non-interaction effect between the two isolators. The invention concerns more specifically a two-tone isolator assembly adapted to be mounted on an aircraft or equivalent comprising in particular a head, a cabin yoke and a power engine structure having a longitudinal axis crossed by a radial plan. The two-tone isolator assembly comprises, located at the head side of the aircraft, at least one support for, at least, one fluid mount isolator and two dynamic absorbers, and mechanical means to couple said support to the power engine structure and to the cabin yoke. Said assembly is designed to link the fluid mount isolator at once to the power engine structure and to the cabin yoke, whereas the dynamic absorber is only linked to the cabin structure. Furthermore, the dynamic absorbers are supported to move in the radial plan of the power engine structure.

Growing community of inventors

Long Beach, CA, United States of America

Ivan Roson