SCRAMJET WITH PULSE DETONATION COMBUSTION CHAMBER AND HYPERSONIC JET FLOW COMBINED WITH SUPERSONIC DIRECT FLOW IN "ONE-IN-ONE" MANNER Russian patent published in 2014 - IPC F02K7/20 

FIELD: engines and pumps.

SUBSTANCE: invention aims at perfection of application of rarefaction formed after reflection of impact wave from working surface of hemispherical resonator (known Hartmann-Sprenger effect). Working rarefaction volume is increased for its filling with water-steam or other gas fuel mix at inflammable concentration. Several explosive volumes are produced with their overlap in aircraft lengthwise direction (in direction of sole degree of freedom). This is done for implementation of self-ignition of fuel mix in closed volume of said explosive volumes which ensures an increase in flame propagation rate in direction of infinite increase. Scramjet incorporates pulsating-detonation conical-circular combustion chamber enveloping the uniflow jet working channel. This combines hypersonic jet flow of said conical-circular combustion chamber with supersonic jet flow of direct-flow channel in the "one-in-one" manner. Said conical-circular combustion chamber has air-steam inflammable fuel mix feed circular nozzle, increased rarefaction volume formation and first explosive intake section that makes second explosive section, section of ahead shock wave braking at the outlet of said combustion chamber, its outer conical surface being aligned with inlet nozzle section of first Laval nozzle tightly connected with second one. Hypersonic and supersonic jet flows get as if combined in the mixing chamber at the joint between said two Laval nozzles. Ignition means ignites explosive fuel mix at engine initial starting period. Thermal change is used to heat and purge the combustion chamber, direct-flow channel and to produce ejection air draft. Detonation starting charge serves to form triple shock wave with necessary interval for engine starting.

EFFECT: perfected design, higher efficiency of scramjet operation.

2 cl, 2 dwg