General Electric Company

Andrew J Lammas

Nicholas Joseph Kray

William Terence Dingwell

Harry McFarland Jarrett, Jr

Daniel Edward Wines

Wayne Ray Bowen

Richard J Fallon

Jayakrishna Velampati

Christopher Charles Glynn

Thomas Joseph Farineau

Craig William Higgins

Roger C Walker

Charles William Carrier

David Lawrence Bedel

Richard G Menzies

Siddharth Navinchandra Ashar

James Edwin Rhoda

Mark Dean Pezzutti

Herbert Halila

William F McGreehan

Jason Winfred Jewett

Philip W Dietz

Bradley Willis Fintel

Steven Mark Ballman

Michael Jason Bishop

Aaron Henry King

Paul Richard Stukenborg

Barbara Ann Link

Terrence Owen Dyer

Chad Duncan Munkres

Laurie Ann Cribley

John D Connelly

Mateusz Wojciech Golebiowski

Eric Lorin Letterman

Saurabh Deshmukh

Anthony E Hungler

Michael Christopher Howard

Doug A Finkhousen

Eric Paul Knopf

Randy Joseph Ketterer

Charles Chris England

Joeseph Charles Kulesa

Sean Patrick McGowan

A clutch system configured to transmit torque between an input shaft and an output shaft. The clutch system may include a clutch and a lubrication supply system. The clutch may include: an input portion disposed at an end of the input shaft; an output portion disposed at an end of the output shaft; and a sliding component that slides axially between the input and output portions to engage the clutch. The lubrication supply system may include: one or more lubricant feeds for delivering a lubricant to the clutch; and one or more lubricant drains for draining the lubricant from the clutch. The one or more lubricant feeds may include one or more respective valves. The one or more valves each may be configurable between settings that vary an amount of the lubricant delivered to the clutch via the respective one of the one or more lubricant feeds.

Clutch with variable lubrication supply

A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.

Lock link mechanism for turbine vanes

A variable vane assembly for a compressor having a plurality of vanes is disclosed. The variable vane assembly may generally include a synchronizing ring and a plurality of attachment studs secured to the synchronizing ring. The variable vane assembly may also include a plurality of lever arms, with each lever arm having a first end and a second end. The first end of each lever arm may be attached to one of the vanes. Additionally, a plurality of rotational attachment devices may be configured to rotatably couple the second end of each lever arm to one of the attachment studs so as to define a rotational interface therebetween. Further, each of the attachments studs may be rigidly attached to one of the rotational attachment devices at the rotational interface such that there is substantially no relative radial and circumferential sliding motion between the synchronizing ring and the plurality of lever arms during rotation of the synchronizing ring.

Variable vane assembly for a turbine compressor

An attachment stud for a variable vane assembly is disclosed. The attachment stud may generally include a bottom segment, a middle segment, a top segment and a shoulder segment. The bottom segment may generally have a shape and configuration adapted to be secured to a synchronizing ring of the variable vane assembly. The middle segment may generally have a shape and configuration adapted to receive a rotational attachment device of the variable vane assembly. The shoulder segment may be disposed between the bottom segment and the middle segment. The top segment may generally have a shape and configuration adapted to receive a retaining device configured to rigidly attach the rotational attachment device to the attachment stud.

Attachment stud for a variable vane assembly of a turbine compressor

A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Rotary machine components and methods of fabricating such components

A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.

High pressure turbine disk hub with reduced axial stress and method

A method of assembling a gas turbine engine that includes providing a rotor assembly including a rotor shaft, an air duct, and a rotor disk that includes a mounting arm, wherein the mounting arm extends radially inward from the rotor disk towards the rotor shaft and coupling a rotor impeller assembly to the mounting arm, wherein the rotor impeller assembly includes a carrier and a plurality of bleed tubes that each extend outwardly from the carrier and are configured to receive bleed air.

Methods and apparatus for operating gas turbine engines

A compressor rotor includes coaxially adjoining disks having corresponding rows of rotor blades. A forward shaft is affixed to a forward disk and includes an annular seat for being mounted in a bearing to support the rotor at its forward end. A blisk coaxially surrounds the shaft axially between the seat and forward disk, and is removably fixedly joined piggyback to the shaft. In a repair method, the blisk may be removed from the compressor rotor without requiring teardown of the compressor rotor itself.

Piggyback rotor blisk

A rotor blade for a turbine engine including a blade root section and an airfoil section which extends radially outward along a radial line R,from the blade root section, is described. The radial line R,extends at an angle relative to a plane extending across a top surface of the platform, rather than normal, or perpendicular, to such plane. As a result, and during a blade out event, an over turning moment is generated in a root of the airfoil section. The overturning moment facilitates bending the airfoil section reducing damage to the stator.

Rotor blade

An article and a method for improving an article that results in a reduction or elimination of damage due to fretting from contact of similar metals. The invention specifically reduces wear-related fretting between titanium alloy parts by lowering the stresses between mating parts. An aluminum bronze coating is applied to one of the parts. The aluminum bronze coating provides an improvement over prior art coatings in reducing coefficient of friction between the parts. Additionally, the cumulative stresses at the surface of the parts is reduced by a dual intensity peening treatment. This involves a first peening operation using large peening media that provides a compressive stress to the required depth. This first peening operation is followed by a second peening operation that provides additional compressive stresses closer to the dovetail surface. The combined metallurgical and mechanical improvement results in a system with less susceptibility to fretting damage and corresponding improved fatigue resistance.

Dual intensity peening and aluminum-bronze wear coating surface enhancement

A dovetail of a rotor blade is mounted in a complementary slot in a rotor disk. Life of the dovetail is simulated by providing a specimen dovetail mounted in a complementary slot in a fixture. Relative stiffness of the specimen dovetail and fixture are tailored to simulate the loading profile between the blade dovetail and rotor disk. Load is cycled between the specimen dovetail and fixture for determining life of the dovetail.

Simulated dovetail testing

A method and fixture assembly for assisting in the matching and assembly of components of a variable stator vane assembly of a gas turbine engine. The method generally entails a stator vane configured to be assembled to a casing with a spacer. The vane has a surface at a perimeter thereof and a seat offset from the surface. The spacer to which the vane is to be assembled has first and second surfaces offset relative to each other, the first surface being adapted to engage the seat of the vane and the second surface adapted to face the surface of the vane. The vane is installed within an opening in the casing so that a first sealing member is between the casing and the vane, the casing is between the first sealing member and a second sealing member, and the seat extends through the opening. A fixture is then mounted to the vane so that the casing and the first and second sealing members are clamped between the fixture and the vane under a load. The position of the seat of the vane is then detected, and a spacer is selected having an offset dimension between its first and second surfaces based on the position of the seat.

Method of assembling a variable stator vane assembly

A shaft assembly for movement of an array of adjustable members comprises a hollow shaft body including a shaft body wall with a wall outer surface. A plurality of spaced apart clevises, secured with the shaft body wall on the wall outer surface, each includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the adjustable members.

Movable shaft assembly

A seal and a washer for a variable vane assembly in a turbine engine are described. The seal includes a first portion and a second portion that are substantially perpendicular. The seal is positioned between a variable vane and a casing. The washer is substantially flat and is located between the casing and a spacer.

Variable vane seal and washer

A bushing assembly as a means to enable guided movement of a shaft in an opening of a housing comprises a stationary bushing support carried by a housing internal wall. The bushing support has a support internal wall defining a bushing support opening through the bushing support to receive a movable shaft. Carried by the shaft is a removable wear sleeve having a wear sleeve outer wall in juxtaposition with and spaced apart from the support internal wall to permit relative axial movement of the wear sleeve with the shaft within the bushing support opening. Disposed between and for contact with the support internal wall and with the wear sleeve outer wall is an anti-friction layer.

Growing community of inventors

Maineville, OH, United States of America

Andrew J Lammas