Cryogenically assisted exhaust condensation
US11603798B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 11, 2022 |
| Grant date | Mar 14, 2023 |
| Priority date | — |
| Expiry date | Feb 11, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/606
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Aircraft engines include a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section. A condenser assembly is arranged downstream of the turbine section along the core flow path. A cryogenic fuel source is configured to supply fuel to the burner section along a fuel line passing through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.