Patent ID: 11946419
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 0:
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.