Patent ID: 11912423
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 0:
1. A propulsion system for an aircraft, the propulsion system comprising:
a first shaft, a second shaft, and a third shaft;
a fan and a low pressure turbine operably coupled to the first shaft;
a low pressure compressor and an intermediate pressure turbine operably coupled to the second shaft;
a high pressure compressor and a high pressure turbine operably coupled to the third shaft;
a burner arranged between the high pressure compressor and the high pressure turbine, wherein a main flow path is defined through the fan, the low pressure compressor, the high pressure compressor, the burner, the high pressure turbine, the intermediate pressure turbine, and the low pressure turbine;
a hydrogen fuel system configured to supply hydrogen fuel from a liquid hydrogen tank to the burner through a hydrogen flow path;
a main flow bypass arranged to direct a portion of air from the high pressure compressor to bypass the burner and be directed to the high pressure turbine, wherein a heat exchanger is arranged along the main flow bypass to receive the portion of air as a first fluid and the hydrogen as a second fluid, wherein the hydrogen is heated within the heat exchanger prior to being supplied into the burner;
a condenser arranged along the main flow path and configured to extract water from exhaust from the burner and supply said extracted water to a water storage tank; and
an evaporator arranged upstream from the condenser along the main flow path and configured to receive a portion of the water from the water storage tank to generate steam, wherein said steam is injected into the main flow path upstream from the evaporator.