FUEL-AIR MIX COMBUSTION AND RAMJET ENGINE WITH SPIN DETONATION WAVE Russian patent published in 2016 - IPC F02K7/02 F02K7/14 

FIELD: engines and pumps.

SUBSTANCE: claimed process meant for development of jet thrust in ramjet consists in that incident high-speed airflow is decelerated to Mach number 3-4 in the supersonic two-stage air intake with the blunt-nose boss. Then, fuel is forced into the flow to swirl the produced well-mixed fuel-air flow to be decelerated to subsonic velocity axial component for said mix to be ignited and combusted in the spin detonation wave. Detonation and shock waves propagating against the flow are suppressed by incident supersonic flow of fuel-air mix. Generated combustion products are directed to creation of engine jet thrust. Claimed engine for high-speed flights comprises the supersonic two-stage air intake with blunted boss and entropy and boundary plies drain system. Fuel pylons are provided with the nozzles to feed fuel into incident airflow, nozzles outlets being configured and arranged to facilitate airflow deceleration and to swirl the produced fuel-air flow. Besides, it includes the circular screen damper of detonation and shock waves and axially symmetric ring-shape nozzle with diverging outer shell and the boss with bottom edge. Aforesaid damper comprises circular screen webs making the channels for deceleration and turning of fuel-air flow to subsonic velocity axial component at preservation of supersonic velocity in the damper channels. The circular detonation combustion chamber is arranged at the damper outlet, chamber initial inner radius smaller than that of the damper ring. The circular screen to straighten outlet flow is arranged at the combustion chamber outlet.

EFFECT: intensified chemical reactions rate of the combustion owing to the spin detonation combustion of well-mixed fuel-air mix.

4 cl, 2 dwg