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, during cranking of engine rotor, there measured is fuel pressure after the pump of engine fuel supply system; if fuel pressure after the pump is higher than the pre-determined value at which hydro-mechanical ACS elements of the engine begin operating in normal mode, there formed is process control commands for multiple laying of metering units and hydraulic cylinders from stop to stop until fuel pressure after the pump of fuel supply system is decreased during the rotor rundown to the pre-determined value at which hydro-mechanical ACS elements of the engine stop operating in normal mode.
EFFECT: improving ACS operating quality, and as a result, improving GTE reliability and aircraft safety owing to accelerated and quality preservation of elements of the executive part of fuel supply system and engine control engine.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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| 0 |
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