METHOD TO CONTROL GAS TURBINE ENGINE FUEL SYSTEM Russian patent published in 2010 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine production and can be used in gas turbine engine ACS. In compliance with the proposed invention, additionally measured are engine rotor rpm, actual fuel flow rate in KC, gas pressure in KC and fuel pressure at fuel filter inlet. Fuel pressure in engine KC manifold is compared with gas pressure in KC. If difference falls beyond preset range selected for every type of engine by experiments and computation, signal "Faulty fuel system" is generated. Engine rotor rpm is used to define from known relationship, the designed fuel pressure ahead of fuel filter. If measure pressure exceeds designed one by preset value, signal "Fuel filter fault" is generated. If measured fuel pressure is smaller than preset one at filter inlet, signal "Faulty 1^st fuel pump" is generated. Gas turbine engine rotor run-out conditions are used to set fuel metering unit into position that allows maximum fuel consumption. If measured fuel pressure at fuel filter inlet is smaller than preset one, signal "Faulty 2^nd fuel pump" is generated.

EFFECT: improved control, hence, engine higher efficiency and reliability.

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