General Electric Company

Safran Aircraft Engines

Jonathan Edward Coleman

Timothy Leo Schelfaut

Anthony Michael Metz

Thomas P Joseph

Kudum Shinde

Mahesh Shenvi Khandeparker

Brian Michael Dixon

Ravindra Shankar Ganiger

Francois Gallet

Daniel Edward Mollmann

Craig William Higgins

Donald Lee Gardner

Guillaume Glemarec

Mark Edward Linz

Michael Riehle

Nicolas Maurice Hervé Aussedat

Illya Emmanuel Arcos Perez

Anil Soni

Lawrence Jerome Meyer

Stefan K Fox

Michael Cline

Srinivas Addagatla

Sharad Tiwari

Michael C Borner

Daniel E Mollman

Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Methods and apparatus for mounting a gas turbine engine

Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

Engine backbone bending reduction

A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.

Control system and methods of controlling an engine-mounting link system

Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle θ of at least one of the plurality of engine-mounting links.

Engine-mounting links that have an adjustable inclination angle

Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

Dual function links for gas turbine engine mounts

Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

Methods and apparatus for gas turbine bending isolation

Damper engine mount links are disclosed. An example engine assembly includes a core including a fore portion and an aft portion, the fore portion of the core to couple to a fan hub frame, the aft portion of the core to couple to a turbine rear frame or a turbine center frame. The engine assembly further includes a forward mount to couple the fan hub frame to an aircraft, and a damper link to couple the turbine rear frame or the turbine center frame to an aircraft mount.

Damper engine mount links

Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.

Bearings with visually distinct wear indicators

An aircraft and propulsion system are provided. The aircraft includes an airframe including one or more of a fuselage, a wing, or an empennage. The aircraft includes an aircraft propulsion system including a front frame and an aft frame. A front mount link is connected to the airframe and the front frame, and the aft frame is selectively connected to the airframe by an aft mount link.

Aircraft and propulsion engine mount system

A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

Growing community of inventors

Mason, OH, United States of America

Jonathan Edward Coleman