Honeywell International Inc.

Srinivas Chinthapally

Avinash Kumar

Theodore S Brockett

Milind Khare

Venkatarao Ganji

Arnab Das

Rama Sateesh Venkata Kandula

Somayaji Chittavajhula

Krishna Mohan Kumbham

A mounting system for coupling a gearbox to an engine includes a sleeve having a first sleeve end opposite a second sleeve end, an outer perimeter and a sleeve bore defined through the sleeve from the first sleeve end to the second sleeve end. The mounting system includes a damping member coupled about the outer perimeter of the sleeve at the first sleeve end. The mounting system includes a corrugated bushing coupled about the outer perimeter of the sleeve between the damping member and the second sleeve end.

Mounting system for gearbox including corrugated bushing

A turbine engine has an engine case with an inlet and an interior of the engine. A bearing is disposed on a portion of the engine case. A fan is disposed within the engine and rotates with operation of the engine. The fan includes a plurality of fan blades, and each fan blade is secured at a first end to a disk. A second end of each fan blade is disposed adjacent to the bearing. The portion is oriented relative to the fan such that a reaction force of a fan blade impacting the bearing is directed axially or away from the inlet.

Engine case for fan blade out retention

Exemplary embodiments are provided to reduce the high transient mount load in an aircraft engine mounting system under extreme loading condition. The exemplary embodiments reduce the impact of the snubbing phenomenon without adding to the weight or space claim of the engine mounting system.

Method and apparatus for reducing high transient mount load in aircraft engine mounting systems

Growing community of inventors

Andhra Pradesh, India

Srinivas Chinthapally