The application discloses a
time sequence control rotating
detonation engine
system combined with a
turbojet engine, which comprises a
turbojet engine, a shell sleeved on the periphery of the
tail nozzle of the
turbojet engine, a cylindrical base coaxially arranged on the inner side of the shell, and a fan-shaped
detonation tube. A cover driven by an electromagnetic push rod is arranged at the top end of each
detonation tube. A sequential
ignition control device is arranged, and a
fuel supply unit of the sequential
ignition control device comprises an
oil pump, a fuel coil
pipe coiled in the cylindrical base, a
common rail ring outside the shell, and a plurality of fuel injectors. A
control unit adopts a mechanical
time sequence controller, and through rotating a moving contact on an outer rotor, the mechanical
time sequence controller sequentially connects static contacts on an
electrode distributor, synchronously triggers electromagnetic push rods and fuel injectors of corresponding detonation tubes, and realizes multi-tube sequential cycle detonation. The application recovers
exhaust heat energy to preheat fuel through a coaxial integrated structure, supplies air by using an ejecting effect, replaces a complex electronic
system with a simple and reliable mechanical control, and realizes efficient, compact, wide working condition
adaptation and thrust enhancement.