Patent ID: 11927132
Assignee: RTX CORPORATION
Field: Chemical engineering (Chemistry)
Classification: CPC F  B | IPC F

Claim 0:
1. A propulsion system for an aircraft comprising:
a core engine including a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen based fuel and ignited to generate a core gas flow that is expanded through a turbine section;
a hydrogen fuel system configured to supply the hydrogen based fuel to the combustor section through a fuel flow path;
a condenser arranged along the core flow path and configured to condense water within the core gas flow; and
a water separator including an inlet, a primary water outlet and an exit including a plurality of exit guide vanes for straightening the core gas flow proceeding through the exit, wherein each one of the plurality of exit guide vanes include a secondary water outlet for removing condensed water in the core gas flow proceeding through the exit.