US 9,810,155 B2
Method for starting aircraft engines
Hao Huang, Vandalia, OH (US)
Assigned to GE AVIATION SYSTEMS LLC, Grand Rapids, MI (US)
Appl. No. 14/915,066
Filed by GE Aviation Systems LLC, Grand Rapids, MI (US)
PCT Filed Sep. 6, 2013, PCT No. PCT/US2013/058461
§ 371(c)(1), (2) Date Feb. 26, 2016,
PCT Pub. No. WO2015/034517, PCT Pub. Date Mar. 12, 2015.
Prior Publication US 2016/0208709 A1, Jul. 21, 2016
Int. Cl. F02N 11/04 (2006.01); H02K 23/52 (2006.01); H02P 9/04 (2006.01); F02C 7/26 (2006.01); F02C 7/268 (2006.01); F02N 11/00 (2006.01); F02N 11/08 (2006.01); H02P 9/08 (2006.01); H02M 7/68 (2006.01); H02P 101/30 (2015.01)
CPC F02C 7/26 (2013.01) [F02C 7/268 (2013.01); F02N 11/006 (2013.01); F02N 11/04 (2013.01); F02N 11/08 (2013.01); H02M 7/68 (2013.01); H02P 9/08 (2013.01); F02N 11/087 (2013.01); F02N 2011/0896 (2013.01); H02P 2101/30 (2015.01); Y02T 50/671 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A method of starting an aircraft having at least a first turbine engine having a first starter/generator (S/G) and a second turbine engine having a second S/G using at least one inverter/converter and at least one of an AC power source having an AC power output and a first DC power source having a DC power output, the method comprising:
selectively starting at least one of the first S/G or second S/G in an AC start mode, where the AC power output is supplied to a first inverter/converter, which converts the AC power output to a second DC power output supplied to a second inverter/converter, which inverts the second DC power output to a second AC power output, which is supplied to the at least one of the first S/G or second S/G, and in a DC start mode, where the DC power output is supplied to the inverter/converter, which inverts the DC power output to a second AC power output, which is then supplied to the at least one of the first S/G or second S/G.