Patent ID: 11867069
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 4:
5. A method for managing airflow through a core flow path of a hybrid electric engine for an aircraft, the method comprising:
converting, using an electric generator, rotational power of a high speed spool of the hybrid electric engine or a low speed spool of the hybrid electric engine to electricity;
storing electricity generated by the electric generator using a power source electrically connected to the electric generator and a variable area turbine control system, wherein the variable area turbine control system is electrically connected to the electric generator through the power source, the power source being one of a battery; a capacitor; a supercapacitor; and an ultracapacitor;
providing power to the variable area turbine control system from the power source, the variable area turbine control system comprising: a plurality of variable turbine vanes located in a turbine section of the hybrid electric engine and a variable area turbine actuator;
rotating, using the variable area turbine actuator, each of the plurality of variable turbine vanes to adjust a cross-sectional area of the core flow path of the hybrid electric engine, wherein the variable area turbine actuator is an electromechanical actuator; and
delivering enough fuel to the hybrid electric engine during a taxi of the aircraft to maintain a minimum fuel flow requirement for the hybrid electric engine; and
rotating, using the variable area turbine actuator, each of the plurality of variable vanes to decrease the cross-sectional area of the core flow path through the turbine section of the hybrid electric engine to spoil engine thrust from the hybrid electric engine.