General Electric Company

Carl Lawrence MacMahon

Praveen Sharma

James Eugene Dingle

Narayanan Payyoor

Kudum Shinde

Tod Robert Steen

Shuvajyoti Ghosh

Mark Joseph Mielke

Charles Stanley Orkiszewski

Shivam Mittal

Shashank Suresh Puranik

Anthony Michael Metz

Drew Michael Capps

Yoon Seok Choi

Brian Drummond

Julie Ann Duselis

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

An apparatus for transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

Engine transportation apparatus

Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal circuit at the second manifold assembly.

Thermal gradient attenuation structure to mitigate rotor bow in turbine engine

An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

Active airfoil vibration control

An apparatus and method of transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

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Cincinnati, OH, United States of America

Carl Lawrence MacMahon