General Electric Company

Carl Grant

Chellappa Balan

Peter John Wood

Donald George LaChapelle

Mark Joseph Mielke

Stephen Rex Payling

Ruby Lasandra Zenon

Kendra Lyn Anderson

David Curr Douglas

James Vota

Philip John Gosinski

Christopher H Lenhardt

Mark Stephen Krautheim

A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.

Turbofan gas turbine engine with variable fan outlet guide vanes

A multiple pass machining method for removing excess flash from a formed part to approximate a desired, curved profile on the formed part includes moving the part relative to a grinder in p straight passes, wherein a first pass removes a portion of flash is at an angle E relative to a stack axis of the part and each remaining straight pass is at an incremental angle F. A portion of the flash is thereby removed to approximate a master profile on an abraded edge of the part.

Methods and apparatus for machining formed parts to obtain a desired profile

A stator vane assembly for a compressor of a gas turbine engine, including a stator vane having an inner portion and an outer portion, a platform attached to the outer portion of the stator vane, a casing for the gas turbine engine, wherein the outer platform of the stator vane is attached to the casing in a manner so that an open area is defined therebetween, and a member positioned within the defined open area for damping vibrations transmitted from the casing to the outer platform.

Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine

A rotor includes a disc having a plurality of blades extending therefrom. The blades include tip shrouds, each having first and second axial ends, and first and second circumferential faces. The first and second faces of adjacent tip shrouds are spaced from each other to define gaps therebetween. The first and second ends each include U-shaped slots, each having an arcuate damper wire disposed therein. The slots are aligned generally parallel to an axial centerline axis of the rotor for allowing ease of manufacture and assembly while providing effective frictional damping by the damper wires urged by centrifugal force against the slots.

Rotor tip shroud damper including damper wires

Growing community of inventors

Cincinnati, OH, United States of America

Carl Grant