METHOD FOR PROTECTION OF DUAL-FROW TURBOJET ENGINE AGAINST LOW PRESSURE TURBINE SPIN-UP Russian patent published in 2016 - IPC F02C9/46 

FIELD: engines.

SUBSTANCE: invention relates to gas turbine engine building, namely to systems for automatic protection of gas turbine engine against turbine spin-up at its disconnection from the compressor shaft. For determining technical state of engine is additionally determined initial S_beg and current S_cur values of rotor sliding using formulas: and . Note here that n_{re beg} - frequency of turbocompressor rotation before change of sliding, rev/min; n_{r beg} - frequency of rotation of low pressure turbine before change of sliding, rev/min; n_{re cur} - frequency of turbocompressor rotation through a time interval Δt, rev/min; n_{r cur} - frequency of low pressure turbine through a time interval Δt, rev/min. Calculate value ΔS = S_cur-S_beg and compared it with preset initially value A₁. Calculate value Δn_r= n_{r beg}-n_{r cur} and compared it with preset initially value A₂. In case if at the same time satisfied the condition under which ΔS > A₁ and Δn_r> A₂, then carry out decrease or the complete cessation of supply of fuel in the engine and giving of a signal on opening of valves of restart-up of air in the compressor.

EFFECT: declared invention will allow to increase reliability of determination of faults and reliability of protection system of bypass turbojet engine low-pressure turbine spin-up.

1 cl, 1 dwg