METHOD OF HELICOPTER POWER PLANT CONTROL Russian patent published in 2013 - IPC B64C27/04 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering and may be used in helicopter turboprop ACSs. Proposed invention consists in measuring and comparing of rotor rpm of turbo compressors of own and adjacent engines in takeoff mode. In case mismatch between said rpm exceeds preset magnitude, pilot uses "Emergency mode" to up the setting of turbo compressor rotor rpm limiter by preset value defined depending upon engine intake air pressure and temperature. Second electronic controller is used to measure gas temperature in the area of turbo compressor turbine distributors and to compare it with maximum tolerable value. In case gas temperature exceeds tolerable value control action for fuel dispenser is generated to decrease fuel flow rate until measured gas temperature drops below said tolerable value. Electric pressure controller and two independent transducers are used to measure free turbine rotor rpm to compare every measured rpm with maximum tolerable value. In case, at least, one measured rpm exceeds maximum tolerable value, the pilot is warned by signal "engine rotor rpm overshoot" while when two measured rpm exceeds said tolerable value shutdown signal is generated and engine is cut off.

EFFECT: higher reliability of power plant.

1 dwg