US 11,946,419 B2
Methods and apparatus to produce hydrogen gas turbine propulsion
David Justin Brady, Lynn, MA (US); Mirko Gernone, Bari (IT); and Nathan E Gibson, Evendale, OH (US)
Assigned to General Electric Company, Schenectady, NY (US); and GE AVIO S.R.L., Rivalta di Torino (IT)
Filed by General Electric Company, Schenectady, NY (US); and GE AVIO S.R.L, Rivalta di Torino (IT)
Filed on Feb. 23, 2022, as Appl. No. 17/678,824.
Prior Publication US 2023/0265797 A1, Aug. 24, 2023
Int. Cl. F02C 7/224 (2006.01); B64D 37/32 (2006.01); F02C 3/22 (2006.01); F02C 3/30 (2006.01)
CPC F02C 7/224 (2013.01) [B64D 37/32 (2013.01); F02C 3/22 (2013.01); F02C 3/30 (2013.01); F05D 2260/213 (2013.01); F05D 2260/607 (2013.01); F05D 2260/99 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An apparatus to produce propulsion in a gas turbine engine comprising:
a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor;
at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line; and
processor circuitry configured to:
identify a temperature of the fluid line; and
cause the inert gas to be injected into the fluid line before the hydrogen is injected into the fluid line for startup of the gas turbine engine in response to the temperature of the fluid line being greater than a freezing point temperature of the inert gas.