| 摘要 |
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 Sand current Svalues of rotor sliding using formulas:and. Note here that n- frequency of turbocompressor rotation before change of sliding, rev/min; n- frequency of rotation of low pressure turbine before change of sliding, rev/min; n- frequency of turbocompressor rotation through a time interval Δt, rev/min; n- frequency of low pressure turbine through a time interval Δt, rev/min. Calculate value ΔS = S-Sand compared it with preset initially value A. Calculate value Δn= n-nand compared it with preset initially value A. In case if at the same time satisfied the condition under which ΔS > Aand Δn> A, 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 |
