General Electric Company

Steven Alan Ross

Thomas Ory Moniz

Bhaskar Nanda Mondal

Scott Hunter

John Joseph Rahaim

Daniel Fusinato

Daniel Edward Mollmann

Robert Charles Hon

Robert Joseph Albers

Tod Robert Steen

Kevin Richard Graziano

Michael Scott McCambridge

Joel Francis Kirk

Mark Edward Linz

Amid Ansari

Thomas Charles Swager

Jeffrey Lee Mason

Thomas Earl Gillingham

Andrew Todd Lehmann

Edward P Brill

Thomas Edward Agin

Daniel Roy Kiracofe

Kenneth Kirchmayer

Charles Thomas McMillan

Joseph Roger Broda

Joseph Daniel Garrett, Iii

Benjamin Lee Walter

Bradley Frank Anastasia

Michael John Vukelich

Byron Andrew Pritchard, Jr

Robert Proctor

Robert Paul Czachor

Richard William Albrecht, Jr

Richard Alan Wesling

Larry W Plemmons

Dean Thomas Lenahan

Gulcharan Singh Brainch

Charles William Carrier

John Christopher Brauer

Charles Stanley Orkiszewski

David A Di Salle

Michael Howard Fisher

Andrew David Kemp

Raymond Gust Holm

Michael Charles Eckert

Jeffrey Scott Allen

Keith Louis Gehring

Enzo Luigi Morabito

George Gould Cunningham, Iii

Paul Alfred Pezzi

Andrew Joseph Kundrot

John Absi

Chris League

Robert R Kursmark

Stephen Wade Faw

Michael Scott Mccambridge

Joseph Daniel Garrett

Kevin Richard Gaziano

Joseph Daniel Garrett Iii

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

Passive control of gas turbine clearances using ceramic matrix composites inserts

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.

Method of starting a gas turbine engine including a bowed-rotor cooling phase

A method of starting a gas turbine engine having a rotor comprising at least a shaft-mounted compressor and turbine, with a casing surrounding the rotor includes an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine.

Method of starting a gas turbine engine including a cooling phase

A gas turbine engine variable bleed apparatus includes a variable bleed valve door disposed in a bleed inlet in a transition duct, rotatable about two or more separate pivot points, operable to open and close an aft bleed slot extending outwardly from transition duct, and operable to open and close a forward bleed slot extending inwardly into transition duct. Door is operable to transition between a first position with aft bleed slot open and forward bleed slot closed to a second position with aft bleed slot closed and forward bleed slot open without fully closing door. Door is rotatable about an axis translatable between the two or more separate pivot points. Transition duct having a transition duct conical angle at least about 10 degrees greater than a booster conical angle of a booster outer shroud upstream of transition duct.

Gas turbine engine two degree of freedom variable bleed valve for ice extraction

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

A method facilitates assembling a gas turbine engine assembly including at least a first member and a second member. The method comprises inserting a threaded fastener through an opening formed in a flange, and providing at least one shank nut including a flanged mating end, an opposite non-mating end, and a body extending therebetween. The body includes an internal surface, an external surface, and a centerline extending between the body ends. The flanged mating end includes a substantially planar exterior surface that is aligned perpendicularly to the centerline and an annular groove that extends from the exterior surface at least partially towards the non-mating end. The method also comprises securing the assembly together such that the mating end is positioned flush against the flange and such that the threaded fastener extends at least partially into a bore extending through the shank nut and defined by the shank nut internal surface.

Methods and apparatus for coupling gas turbine engine components

Methods and systems of balancing a rotatable member are provided. A method includes separately balancing a first portion and a second portion of the rotatable member wherein the second portion mateable to said first portion, coupling the first and second portions to each other, measuring a physical dimension of the coupled first and second portions, and determining a balance weight magnitude and position based on the measured physical dimension.

Methods and systems for balancing a rotatable member

Stapler with digital display

An annular air baffle disposed in a cavity of a rotatable gas turbine engine part includes an annular split ring supporting a plurality of circumferentially spaced apart fins. The cavity is closed at a radially outer diameter and open at a radially inner diameter of the part. The ring and the fins may be integrally formed in one piece. The fins may have common surfaces with the ring and the common surfaces may be circular cross-sectional surfaces of the ring and radially outer rounded corners of the fins. The fins may have triangular cross-sectional shapes with first, second, and third sides, rounded first radially inner corners between the first and second sides, rounded second radially inner corners between the second and third sides, and the radially outer rounded corners between the first and third sides. The fins may extend radially inwardly from the annular split ring.

Gas turbine engine air baffle for a rotating cavity

A damper for reducing vibration in a least a portion of a component during inertia welding. The damper includes a generally annular body having a spiral slot formed therein.

Method and apparatus for reducing component vibration during inertia welding

A web-based system standardizes data from a plurality of different programs to facilitate design review comparisons in a cost-effective and reliable manner. The system includes a client system including a browser, a data storage device for storing information, and a server system coupled to the client system and the database. The server system is configured to store data in the data storage device in a standardized format, generate characteristics unique to the data input using pre-determined calculations, compare the characteristics to pre-determined target values, quantify shifts of the characteristics from respective target values, and generate standardized graphical representations of the data using based on the generated characteristics.

System and methods for standardizing data for design review comparisons

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Cincinnati, OH, United States of America

Steven Alan Ross