METHOD AND SYSTEM FOR TURBOJET ROTOR ANGULAR POSITION DETERMINATION Russian patent published in 2013 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to determination of turbojet first rotor angular position whereat at least one oscillation is generated in first rotor rotation. Note here that every oscillation is generated when said first rotor passes one and the same check angular position to detect generated oscillations. At the moment, turbojet second rotor angular position is obtained relative to angular position the rotor stayed at during check moment representing detection of one of oscillations. Note here that said second rotor is coupled in rotation with first rotor and runs at speed that differs from rpm of the first rotor. On the basis of second rotor angular position, that of the first rotor is defined at the given moment.

EFFECT: simplified procedure without rpm transducer equipped with gear wheel at hardly accessible rotor.

12 cl, 4 dwg