ROCKET-RAMJET ENGINE WITH ADJUSTABLE FLOW RATE OF SOLID FUEL Russian patent published in 2017 - IPC F02K7/18 

FIELD: engines and pumps.

SUBSTANCE: rocket-ramjet engine includes an air inlet, a gas generator with a charge of solid fuel, connected to it a flow regulator, a combustion chamber with a shaped outlet nozzle. The flow regulator is adapted to regulate the two-stage combustion of solid fuel flow, comprising a housing. The housing includes a front cover in the form of a perforated grating, and a back cover mounted between annular nozzle array of holes. Inside fixed housing installed with a central insert bore and moving the adjusting member relative thereto, and a profiled sleeve. Between the liner, the fixed regulating element and the sleeve-shaped annular channel is formed with a curved variable orifice bounded by the annular nozzle grid with holes whose axes are inclined at an angle of 45÷135° to the central longitudinal axis of the engine. The combustion chamber is designed as a variable-section channel providing combustion acceleration from subsonic to supersonic speeds, and the output nozzle is shaped such that the combustion products provides acceleration to speeds of Mach M≥4.

EFFECT: increase specific impulse, increasing range and increasing the completeness of combustion of solid fuel in the air stream.

4 cl, 4 dwg