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.
Aircraft propulsion system with turbine engine and exhaust condenser
2024-09-10
Patent
Electronic Resource
English
AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER
European Patent Office | 2024
|Aircraft propulsion system with turbine engine and exhaust condenser
European Patent Office | 2024
|Aircraft propulsion system with turbine engine and exhaust condenser
European Patent Office | 2024
|AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER
European Patent Office | 2024
|AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER
European Patent Office | 2024
|