| 摘要 |
FIELD: aircraft industry. ^ SUBSTANCE: invention can be used as engine of gas-jet electric generator or flying vehicles with subsonic flying speeds, particularly, helicopters. Proposed detonation combustion pulsejet engine has body with combustion chamber with input, circular channel with input and output, converter of working medium internal energy into mechanical work of thrust in form of gas-dynamic resonator, engine nozzle, detonation initiating mechanism and annular nozzle to feed fuel mixture. Combustion chamber is made in form of semispherical gas-dynamic resonator and nozzle of engine. Mechanism initiating detonation is made in form of tube stopped from one side, free output of which is connected with center of gas-dynamic resonator, ratio of detonation products velocity to fuel mixture delivery speed should be greater than or equal to ratio of two lengths of detonation initiating mechanism to radius of resonator. ^ EFFECT: decreased mass and overall dimensions at considerable centrifugal forces, improved efficiency and reliability of engine under said conditions. ^ 8 cl
|
