Aircraft propulsion system with turbine engine and exhaust condenser
US12085043B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 16, 2023 |
| Grant date | Sep 10, 2024 |
| Priority date | — |
| Expiry date | Jun 16, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/081
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The exhaust gas condenser includes a housing, a nozzle, a plurality of air scoops, and a plurality of exhaust gas conduit banks. The housing has an interior cavity, a bottom side, and first and second lateral sides. The exhaust gas conduit banks are disposed in the interior cavity of the housing and are configured to form an interior bypass air chamber. Each exhaust gas conduit bank includes alternating exhaust gas conduits and bypass air passages. The exhaust gas conduits extend axially between the forward and aft ends, and are configured to conduct exhaust gases to the nozzle. The bypass air passages are configured to receive bypass air from the air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.