General Electric Company

David Alexander Hiett

Stefan Joseph Cafaro

David Marion Ostdiek

Robert Jon McQuiston

Robert Charles Hon

Thomas Charles Swager

Jeffrey S Spruill

John Thomas Lammers

Nicholas Adam Descamps

A control system and schemes for controlling a three-stream gas turbine engine are disclosed. In one aspect, a three-stream engine is architecturally arranged so as to define a primary bypass flowpath, a secondary bypass flowpath, and a core flowpath that may each output propulsive thrust. The three-stream engine includes one or more effectors that can be controlled to adjust a thrust contribution provided by the secondary bypass flowpath to the net propulsive thrust as well as a thermal contribution provided by the secondary bypass flowpath to an associated thermal management system. Competing demands, limits, and priorities can be considered in controlling the effector. In some embodiments, a secondary effector can be ganged or controlled in conjunction with the effector to assist with adjustment of the contributions provided by the secondary bypass flowpath.

Three-stream gas turbine engine control

A method is provided for operating a hybrid-electric propulsion system having a first engine, a second engine, a first electric machine coupled to the first engine, and a second electric machine coupled to one of the first engine or the second engine. The method includes: receiving data indicative of a first engine operating parameter, a second engine operating parameter, or both; determining a first engine operating parameter margin, a second parameter operating margin, or both; determining a load share for the first engine, the second engine, or both, or between the first engine and the second engine based on the first engine operating parameter margin, the second engine operating parameter margin, or both; and transferring a first amount of power to or from the first electric machine and a second amount of power to or from the second electric machine in response to the determined load share.

Hybrid electric propulsion system load share

A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power source. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device is operable with the compressor section, combustion section, turbine section, or a combination thereof. The actuator is operationally coupled to the actuation device and includes an electric actuator configured to convert electrical current into mechanical power. The power source is configured to supply electrical current to the actuator, alone or in tandem with a hydraulic actuator.

Gas turbine engine actuation device

Systems and methods for shutting down a gas turbine engine in response to a severe mechanical failure include determining a rate of change of one or more process conditions. If the rate of change of the one or more process conditions exceeds a respective predetermined failure threshold, a potential severe mechanical failure of the gas turbine engine may be determined. Steps may be taken to confirm the potential severe mechanical failure of the gas turbine engine. In response, an engine restart is prevented.

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Cincinnati, OH, United States of America

David Alexander Hiett