General Electric Company

Airbus Operations (s.a.s.)

Airbus Operations Sl

Tod Robert Steen

Amid Ansari

Paul Robert Gemin

Robert Charles Hon

Thomas Lee Becker, Jr

Michael Scott McCambridge

Thomas Earl Gillingham

Daniel Roy Kiracofe

Kenneth Kirchmayer

Richard Ludwig Schmidt

Narayanan Payyoor

Kevin Richard Graziano

Thomas Charles Swager

Andrew Todd Lehmann

Joseph Roger Broda

Richard Alan Wesling

Weize Kang

Steven Alan Ross

Shuvajyoti Ghosh

Mark Edward Linz

Joseph Daniel Garrett, Iii

Michael Scott Mccambridge

Ravindra Shankar Ganiger

David Raju Yamarthi

Daniel Edward Mollmann

Praveen Sharma

Kudum Shinde

Thomas Tracy Wallace

Charles Stanley Orkiszewski

Patrick Zaccaria

Carlos Casado-Montero

Leslie L Langenbrunner

Anthony Paul Greenwood

Ankita Sinha

Surender Reddy Bhavanam

Philippe Chareyre

Carl Lawrence MacMahon

Pio Fernandez-Lopez

Venkata Subramanya Sarma Devarakonda

Thomas Lee Becker

William Joseph Simpson

Rajesh Kumar Undipalli

Himanshu Gupta

John Howard List

Jason Jianxin Tao

Hrishi Ragesh

Aman Srivastava

Dinesh Rakwal

Joseph Daniel Garrett

Kevin Richard Gaziano

Joseph Daniel Garrett Iii

The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.

Torsional damping for gas turbine engines

A gas turbine engine includes a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine, an airflow passage having a core passage and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.

Gas turbine engine having a sensor assembly to detect torsional vibration

A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

Power transmission system and gas turbine engine comprising the same

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 is generally provided. The engine includes a rotor assembly including a compressor rotor and a turbine rotor each coupled to a shaft. The rotor assembly is coupled to a bearing assembly within a casing enabling rotation of the rotor assembly. The method includes determining, based on a lubricant parameter, a period of time within which a rotational speed of the rotor assembly is maintained within a bowed rotor mitigation speed range; rotating the rotor assembly for the period of time within the bowed rotor mitigation speed range; and accelerating the rotor assembly to the combustion speed to ignite a fuel-oxidizer mixture for combustion.

Method of starting a gas turbine engine

A controllable magneto-rheological device includes an annular cylinder formed by inner and outer walls connected at first and second opposing ends and forming an inner shaft configured to receive an operational component of an engine, generator or other device including one or more rotating structures. A magneto-rheological fluid is provided to fill a volume between the inner and outer walls of the annular cylinder. A plurality of electro-magnetic coils are positioned around the outer wall of the annular cylinder. One or more current controllers are coupled to the plurality of electro-magnetic coils for introducing a current through each of the electro-magnetic coils and corresponding magnetic flux through the magneto-rheological fluid. A level of current provided to each of the plurality of electro-magnetic coils directly affects the viscosity of the magneto-rheological fluid and thus the stiffness and damping levels of the controllable magneto-rheological device.

Controllable magneto-rheological device for gas turbine engine

The present disclosure provides a turbine engine, comprising a core turbine engine comprising a turbine and a compressor adapted to be driven by the turbine via a rotor; as accessory gearbox connected with the rotor; and a flexible shaft having a first end connected with the accessory gearbox and a second end extending toward outside for being coupled to an external power source.

Turbine engine for reducing rotor bow and method thereof

A turbomachine assembly includes annular stator surrounding rotor circumscribed and rotatable about centerline axis. One or more non-axisymmetric partial arc annular circular stiffeners are disposed around and on stator and may be helical. Non-axisymmetric partial arc annular circular stiffeners may extend about one third to one half of a circumference, be hollow, and located over one or more blade stages of rotor. One or more annular mid-span flanges may be attached to stator and axially positioned within the hollow partial arc annular circular stiffeners. One or more masses or externals may be attached to the stator or to at least one of the one or more annular mid-span flanges between ends of partial arc annular circular stiffeners. Annular stator and rotor may have matching frequencies causing rotating stator waves rotating with rotor. The stator may be fan casing surrounding fan rotor or labyrinth seal land surrounding labyrinth seal teeth.

Turbomachine stator travelling wave inhibitor

A damper assembly includes a bearing assembly including a radially outer surface. A housing surrounds the bearing assembly and includes a radially inner surface facing the radially outer surface. The radially outer and inner surfaces define a plurality of annuli therebetween. The damper assembly further includes a plurality of fluid supplies coupled in flow communication with the plurality of annuli and configured to deliver a fluid to each annulus of the plurality of annuli. Each fluid supply of the plurality of fluid supplies independently controls the fluid within the respective annulus.

System and method for a variable squeeze film damper

A method of operating a turbine engine that includes actuating a starter motor of the turbine engine such that a motoring speed of the turbine engine increases, and actuating a plurality of variable stator vanes of the turbine engine such that the plurality of variable stator vanes are at least partially open to control the motoring speed of the turbine engine.

Turbine engine and method of operating

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

An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.

Method and system for bowed rotor start mitigation using rotor cooling

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West Chester, OH, United States of America

Tod Robert Steen