CPC H02J 3/36 (2013.01) [B64D 27/24 (2013.01); H02J 1/06 (2013.01); H02K 7/1815 (2013.01); H02M 7/537 (2013.01); H02P 27/06 (2013.01); B64D 27/026 (2024.01); B64D 2221/00 (2013.01)] | 20 Claims |
1. A hybrid power system for an aircraft, the hybrid power system comprising:
a high-voltage DC (HVDC) bus;
a generator-motor system configured to (1) selectively receive electric power from the HVDC bus to assist an engine of the aircraft in providing propulsion and (2) provide electric power to the HVDC bus during regulated power extraction from the engine, wherein the generator-motor system includes:
a low-pressure spool (LPS) generator/motor coupled with an LPS shaft of the engine;
a high-pressure spool (HPS) generator/motor coupled with an HPS shaft of the engine;
a first AC/DC converter connected to the LPS generator/motor and the HVDC bus; and
a second AC/DC converter connected to the HPS generator/motor, the first AC/DC converter, and the HVDC bus;
an electric motor connected to the HVDC bus and configured to provide one or more of propulsion and electric power;
an AC distribution system connected to the HVDC bus;
a DC distribution system connected to HVDC bus; and
a control system configured to selectively control a state of a connection to the HVDC bus of one or more of the first AC/DC converter, the second AC/DC converter, the electric motor, the AC distribution system, and the DC distribution system.
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