FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production and can be incorporated with electronic hydro mechanical automatic gas turbine engine control systems. To identify the compressor surge state, this invention proposes to calculate additionally the surge criterion and compare it with the cut-in/cut-out settings selected for every gas turbine type experimentally. In case the said criterion exceeds the cut-in setting, the "SURGE" signal is generated. If the said criterion is smaller than the cutting-in setting, it is compared with cutting-off setting. Is the criterion exceeds the cutting-off setting, the "SURGE" signal is preserved. Is the criterion is smaller than the cutting-off setting, the "SURGE" signal is removed, cooling chamber is cut out and fuel feed to combustion chamber of gas turbine is resumed.
EFFECT: higher engine reliability and aircraft safety.
1 dwg
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|
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|
RU2329388C1 |
