Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

Abstract: A turbine engine with a turbine core that includes a compressor section having a compressor coupled to a high speed shaft, a combustion section, a turbine section having a high pressure turbine coupled to the high speed shaft and a low pressure turbine coupled to a low speed shaft, and a nozzle section. The turbine engine also includes an electric machine that can operate in a first starting mode and a second generating mode.

Abstract: A turbine engine with a turbine core that includes a compressor section having a compressor coupled to a high speed shaft, a combustion section, a turbine section having a high pressure turbine coupled to the high speed shaft and a low pressure turbine coupled to a low speed shaft, and a nozzle section. The turbine engine also includes an electric machine that can operate in a first starting mode and a second generating mode.

Abstract: A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine. The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft.