| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: inventions are related to methods for protection of bypass two-shaft gas turbine engines (GTE) of airplane against ingress of foreign objects and turbulent vortex flows to the inlet of high pressure compressor (HPC). Whenever GTE operates at idle and other reduced conditions of forward thrust, air relief gate valves of both groups are in open position. Contaminating particles that are separated in fan and low pressure compressor (LPC), through open gate valves of both groups are supplied to external circuit and further exhausted from GTE without its damage. During airplane landing pilot puts engine control lever (ECL) in position "Flight idle", relief gate valves of both groups are in open position. Then pilot switches on thrust reversal, after that ECL is changed over to position of "Maximum reverse thrust". GTE control lever position detector continuously measures value Lecl, which is compared to Lthreshold ecl in unit of reversal switching signal generation. If Lecl< Lthreshold ecl, signal I2=1 (criterion of operation at reversal) is generated at the outlet of reversal switching signal generation unit, which arrives to inlet of commutator switch. If signal I2=1 is available in commutator switch, control circuits of gate valves of both groups open, and independently on rotation frequency n"" and velocity Vs, gate valves remain in open position, thus providing for reliable protection of engine against ingress of foreign objects and effect of "bound vortex" during airplane breaking. At the same time on appearance of signal I2=1 regulation program is readjusted at pickup, at that higher surplus of fuel supply DeltaGf to combustion chamber is provided compared to program of fuel supply Gf at pickup modes for forward thrust. Such method and device will make it possible to increase reliability of engine operation. ^ EFFECT: higher reliability of engine operation. ^ 3 cl 1 dwg |
