US 12,334,859 B2
Gas-turbine electrical start system
Peter Schenk, Indianapolis, IN (US); Erik A. Munevar, Indianapolis, IN (US); and Rigoberto J. Rodriguez, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Aug. 12, 2022, as Appl. No. 17/819,527.
Prior Publication US 2024/0056007 A1, Feb. 15, 2024
Int. Cl. H02P 9/08 (2006.01); F02C 7/268 (2006.01); H02P 101/25 (2016.01); H02P 101/30 (2015.01)
CPC H02P 9/08 (2013.01) [F02C 7/268 (2013.01); H02P 2101/25 (2015.01); H02P 2101/30 (2015.01)] 20 Claims
OG exemplary drawing
 
1. A system comprising:
a power electronics system;
a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft;
an alternating current (AC) electrical bus connected to the power electronics system, the AC electrical bus being supplied power by one or more power sources of the aircraft; and
an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system,
wherein the power electronics system is configured to deliver AC electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from the AC electrical bus of the aircraft.