HYBRID AEROSPACE ROCKET RAMJET Russian patent published in 2015 - IPC F02K7/18 B81C99/00 

FIELD: engines and pumps.

SUBSTANCE: claimed engine comprises rocket engine running on fuel composed of aluminium nanopowder sized to not over 25 nm in liquid aqueous phase and ramjet combined therewith and running on molecular hydrogen formed at combustion of aluminium nanopowder. Claimed engine comprises cylindrical shell ring, central axially symmetric or wedge-like body fitted in said shell ring, combustion chamber to combust aluminium nanopowder in water vapours. One end of said cylindrical shell ring has inlet for atmospheric airflow and discharge nozzle at opposite end. System of shock waves is developed at edges of said central axially symmetric or wedge-like body. Said combustion chamber to combust aluminium nanopowder in water vapours doubles as the chemical reactor for production of hydrogen and is located in wedge-like body and coupled therewith at outlet and with nozzle suitable for formation of combustion zone at interaction of hydrogen efflux with incoming airflow. Molecular hydrogen and oxidizer in combustion zone exist in stoichiometric relationship (fuel-to-oxidizer ratio ϕ=1), or form lean mix (with ratio ϕ<1).

EFFECT: higher efficiency of fuel chemical energy conversion into thermal power, expanded range of flying conditions.

3 cl, 1 dwg