HYPERSONIC PULSE DETONATING ENGINE AND METHOD OF ITS FUNCTIONING Russian patent published in 2009 - IPC F02K7/02 

FIELD: engines and pumps.

SUBSTANCE: hypersonic pulse detonating engine comprises casing, air intake, half-closed detonating combustion chamber, nozzle block, fuel system and control system. Air intake is arranged as annular. Central body is casing with fuel tank, heat exchanger and active thermal shielding. Half-closed detonating combustion chamber is formed by end wall of central body and internal wall of nozzle block. Air intake channel is connected to half-closed detonating combustion engine by adjusted annular slotted nozzle. Method of hypersonic pulse detonating engine functioning consists in preparation of fuel mixture, its supply to half-closed detonating combustion chamber, detonation of fuel mixture in pulse mode and generation of impulse. Prepared fuel mixture with coefficient of oxygen excess below 0.1 is supplied to half-closed detonating combustion chamber via end perforated wall. Fuel mixture with coefficient of oxygen excess more than 0.85 is sent to half-closed detonating combustion chamber via adjusted annular slotted nozzle periodically in pulse mode, and fuel mixture gas detonation is carried out in the range of frequencies from 200 to 27,000 Herz.

EFFECT: higher reliability of engine operation in hypersonic flight modes, and also thermal efficiency factor and specific impulse increase.

6 cl, 1 dwg