METHOD OF THE NON-CONTACT EARLY BURNOUT DIAGNOSTICS OF THE ROCKET CHAMBER ON THE SELF-MAGNETIC FIELD INTENSITY OF COMBUSTION PRODUCTS Russian patent published in 2018 - IPC F23N5/24 G01R29/08 G01R33/02 

FIELD: motors and pumps.

SUBSTANCE: invention relates to the field of aerospace engineering, in particular aerospace engine technology. One of the most common failure causes of liquid-fuel rocket engines is the burnout of the chamber, the beginning of which is associated with the appearance of a multitude of charged solid particles in the combustion products. Changes in vibration frequencies of electromagnetic parameters of a gas-dynamic motion of high-temperature combustion products flowing through a combustion chamber and a nozzle, is recorded by a highly sensitive magnetic field sensor susceptible to the appearance of solid particles in a gas stream preceding a fracture, spectral density in the power spectrum of the realization of this signal is determined and compared with the reference value of the spectral density, and in the case of exceeding the determined parameter of a given reference value, the frequency at which the excess occurred is determined, this frequency is compared with the frequency values of the burnout start for the given chamber and a signal to the engine's emergency protection system about the start of the burnout is generated.

EFFECT: ensuring a reliable detection of the beginning of the process of destruction of the combustion chamber and the nozzle to prevent burnout of said heat-stressed elements of the flow duct of the rocket engine.

1 cl, 2 dwg