OPERATING METHOD OF PULSE-DETONATION ENGINE IN CENTRIFUGAL FORCE FIELD AND DEVICE FOR IMPLEMENTATION THEREOF IN JET HELICOPTER Russian patent published in 2020 - IPC B64C27/18 F02K7/04 F02K7/06 

FIELD: machine building.

SUBSTANCE: invention relates to air-jet engines installed at ends of rotor blade blades of a helicopter. Disclosed is method of working process arrangement in pulse-detonation traction module for jet helicopter, arranged on rotor blade end, including fuel supply, mixing fuel with air, filling combustion chamber with combustible mixture, occurrence of detonation wave, expansion of detonation products in burner circuit and outflow of detonation products through nozzle for creation of reactive thrust, in which liquid fuel is supplied to cylindrical hot inner walls cyclically in form of jets, wherein the jets are oriented so that the hot combustion chamber inner walls are wetted with liquid fuel evenly taking into account the centrifugal forces action direction, and as a result of the liquid fuel jets with the combustion walls inner combustion walls thermomechanical interaction the jets fragmentation takes place to form droplets and liquid fuel films, as well as fuel vapors providing formation of detonation-capable two-phase combustible mixture filling the burner path, and forced ignition of combustible mixture leads to formation in burner channel of accelerating turbulent flame and to fast transition of combustion to detonation, so that all remaining in burner path two-phase combustible mixture is burnt in detonation wave, running towards nozzle, and after its outlet from the nozzle, the detonation products flow through the nozzle, accompanied by the pressure decrease in the burner circuit to the braking pressure level in the incoming air flow, thereby providing conditions for the burner circuit blowdown and its repeated filling with the detonation-capable two-phase fuel and air mixture, and detonation products flowing from nozzle create reactive thrust. Proposed method is implemented in device including air intake with check valve, combustion chamber with ignition source, output device (nozzle) and control system, in which burner path is connected to air intake, which includes combustion chamber with fuel metering device and ignition source, as well as detonation pipe with obstacles-turbulence promoters and nozzle installed in outlet section of detonation pipe.

EFFECT: proposed device provides positive thrust in flight conditions at cruise speed (corresponds to incoming air flow rate of about 70 m/s).

6 cl, 5 dwg