General Electric Company

Edge Prototype LLC

Donald Scott Yeager

Brandon Wayne Miller

Darek Tomasz Zatorski

Christopher Charles Glynn

Nicholas Rowe Dinsmore

Donald Michael Corsmeier

Jeffrey Raymond Menard

Martin Carlos Todd

Arthur William Sibbach

Andrew Breeze-Stringfellow

Randy M Vondrell

Kurt David Murrow

James Thompson

Craig Douglas Young

Mark Willard Marusko

Donald Albert Bradley

Donald Lee Gardner

Daniel Dale Brown

David Bruce Patterson

Glenn Edward Wiehe

Craig Miller Kuhne

John C Schilling

Ryan T Roehm

Samuel Jacob Martin

Brian Paul Overbeck

Michael Joseph Zerbe

Robert Eugene Dyson

Darek T Zatorski

Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.

Fluid-filled thrust link apparatus and associated method

A structure for damping at a fluid manifold assembly for an engine is generally provided. The fluid manifold assembly includes a first walled conduit defining a first fluid passage therewithin. A flow of fluid defining a first frequency is permitted through the first fluid passage. A second walled conduit includes a pair of first portions each coupled to the first walled conduit. A second portion is coupled to the pair of first portions. A second fluid passage is defined through the first portion and the second portion in fluid communication with the first fluid passage. The flow of fluid is permitted through the second fluid passage at a second frequency approximately 180 degrees out of phase from the first frequency.

Gas turbine fluid manifold assembly having an adjustable length bypass conduit to attenuate dynamics

Fluid manifold assembly for gas turbine engine

The present disclosure is directed to a sealing system for a turbine engine including an engine component, the engine component defining an oblique sealing surface defining an annular shape. The oblique sealing surface defines an oblique angle with a centerline of the engine component. The sealing system includes a seal housing and a seal ring. The seal housing is annular and includes a groove that is defined by a first sidewall, a second sidewall, and an end wall connecting the first sidewall and the second sidewall. The seal ring is positioned at least partially within the groove in the seal housing. The seal ring defines a seal contact surface for forming a seal with the oblique sealing surface of the engine component.

Sealing system for sealing against a non-cylindrical surface

Provided is an exercise lifting bar having at least two hand grips, an integral loading surface for holding optional plate weights coupled to each hand grip, the paired or coupled grips and loading surfaces thereby defining a member; the members further being substantially cylindrical, collinear, and operable to translate relative to one another. Also included is a translation limiter to limit the motion between the members. Methods of assembly of the exercise lifting bar are also provided.

Exercise lifting bar with translating hand grips

A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.

Engine architecture with reverse rotation integral drive and vaneless turbine

The problems of efficiency and safety when exercising the pectoral muscles are solved in at least one aspect while maintaining low-complexity and portability by a free weight barbell with translating hand grips, with the grips having an integral weight application loading surface that moves with the grip. Provided is an exercise lifting bar having at least two hand grips, an integral loading surface for holding optional plate weights coupled to each hand grip, the paired or coupled grips and loading surfaces thereby defining a member; the members further being substantially cylindrical, collinear, and operable to translate relative to one another. Also included is a translation limiter to limit the motion between the members.

A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.

Combustion system and method of assembling the same

Spaced apart counter-rotatable forward and aft rows of forward and aft propellers are mounted on forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators on the frames are operable for controlling pitch of the propellers. A hydraulic fluid supply outboard of the frames is connected to forward and aft rotary unions which are operable for transferring hydraulic fluid between forward and aft union stators to forward and aft union rotors mounted within the forward and aft rotary unions. The forward union rotor is operable to transfer the hydraulic fluid from the forward rotary union to the aft pitch change actuators and the aft union rotor is operable to transfer the hydraulic fluid from the aft rotary unions to the forward pitch change actuators. The forward and aft rotatable frames counter-rotatably mounted on a structural frame located forward or aft of the propellers.

Hydraulic system for fan pitch change actuation of counter-rotating propellers

Axially spaced apart counter-rotatable forward and aft rows of forward and aft propellers mounted on forward and aft rotatable frames includes a flowpath passing through the forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators mounted on the aft rotatable frames are connected to and operable for controlling and setting pitch of the aft propellers. The pitch change actuators are mounted radially inwardly of the flowpath in a one to one ratio with forward and aft rotatable struts extending radially across the flowpath. One or more rotatable shafts extend through one or more of the rotatable struts and connect one or more of the pitch change actuators to one or more of the propellers. The pitch change actuators may be ganged together by unison rings having ring teeth engaging gear teeth on gears connected to the pitch change actuators or connected to the rotatable shafts.

Pitch change apparatus for counter-rotating propellers

Growing community of inventors

Loveland, OH, United States of America

Donald Scott Yeager