FIELD: engines and pumps.
SUBSTANCE: invention relates to aviation engine engineering and can be used in electronic-hydro mechanical systems of automatic control (ACS) of gas turbine engines (GTE). Essence of invention consists in the fact that in addition, depending on fuel flow supplied to the collector, there formed is design value of fuel pressure in combustion chamber collector, design collector fuel pressure value is compared to the measured one; if the latter is higher than the design one by the specified value determined experimentally for each type of engine, there formed is signal to stop the fuel supply to combustion chamber and to stop the engine start.
EFFECT: improving operating quality of ACS, and as a result, improving GTE reliability and aircraft safety owing to observing the balance between air flow through the engine compressor and fuel flow to combustion chamber.
1 dwg
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