General Electric Company

Clopay Building Products Company, Inc.

Thomas Edward Agin

Steven Alan Ross

Daniel Edward Mollmann

Praveen Sharma

Richard Alan Wesling

Kudum Shinde

Kenneth E Carper

Weize Kang

Charles Stanley Orkiszewski

Milind Chandrakant Dhabade

Alan R Leist

Shivam Mittal

William Carl Anderson

Tony Y Lin

Caitlin Marie Ford

Michael William Murrish

George S Carper

Timothy McCann

A turbofan engine includes an outer bypass duct and a gas turbine engine having an outer casing. The gas turbine engine is disposed in the outer bypass duct such that a bypass airflow passage is formed between the outer casing of the gas turbine engine and the outer bypass duct. The turbofan engine includes a turbine rear frame link assembly including a set of links coupled between the outer bypass duct and the outer casing to support the gas turbine engine relative to the outer bypass duct. The links are arranged around the gas turbine engine on a plane that is perpendicular to a centerline axis of the turbofan engine. None of the links extends through the bypass airflow passage at a position that intersects a radius extending in a vertically downward direction from the centerline axis.

Turbine rear frame link assemblies for turbofan engines

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

Structure and method to mitigate rotor bow in turbine engine

Methods and systems for mitigating distortion of a shaft of a gas turbine engine are provided. One method comprises at least one step of applying intermittent rotary power to a shaft of a gas turbine engine. The step of applying intermittent power to the shaft is performed during a period where conditions of temperature differential in the engine exist capable of distorting the shaft. The methods and systems shorten the time needed to start a gas turbine engine in such a way that bowing of a shaft is not a significant problem.

Methods and systems for mitigating distortion of gas turbine shaft

A method and apparatus for reducing dynamic loading of a gas turbine engine is provided. The gas turbine engine includes a rotor shaft assembly including a rotor shaft, a bearing assembly, a mounting race, and a support frame, the mounting race including a spherical surface. The method includes supporting the rotor shaft on the gas turbine engine support frame with the bearing assembly, the rotor shaft including a yield portion configured to permit bending of the rotor shaft during an imbalance operation.

Method and apparatus for supporting rotor assemblies during unbalances

An overhead door apparatus utilizing a torsion spring counterbalancing mechanism. The counterbalancing mechanism includes a worm drive ring-shaped gear winding mechanism for setting the appropriate torque or number of winds in the spring. A counting mechanism is provided to indicate to the installer the number of winds being given to the spring. The ring-shaped gear is a spur gear which is formed integrally with the fitting or cone which attaches by way of a threaded connection with one end of the spring. Means are also provided for accommodating spring growth and contraction during winding and unwinding using the winding mechanism and during normal raising and lowering of the door. A spring clip gear retainer is disclosed for preventing rotation or creep of the worm drive gear and spur gear during normal raising and lowering of the door.

Counterbalancing mechanism for an overhead door

Growing community of inventors

Cincinnati, OH, United States of America

Thomas Edward Agin