GAS TURBINE ENGINE CONTROL METHOD AND DEVICE Russian patent published in 2011 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: first, for zero-operating hours engine, T_t=f(n) ratio is generated wherein T_t is gas temperature behind the turbine and n is compressor rotor rpm. In control over afterburner conditions, rotor actual rpm (n_act) is compared with rotor rpm at zero-operating hours and actual temperature. In case Δn exists there between, signal proportional to said difference is generated to correct program of fuel feed into afterburner combustion chamber to ensure preset surplus air factor (). Proposed control system comprises automatic device to feed fuel into afterburner chamber (G_f-ab) in response to signals of air pressure downstream of compressor (P_c) and turbine inlet air temperature (T_in), pickups of gas temperature behind the turbine (T_t), compressor rotor rpm (n) turbine pressure difference (π_T), and jet nozzle flap controller incorporating element to compare preset and actual magnitudes of π_t. System comprises additionally comparator of T_t=f(n) and comparator element. One input of the former device is connected with turbine outlet gas temperature T_t and output is connected with element to compare rpm. Another input of comparator element is connected to compressor rotor rpm transducer, while its output is connected, via Δn correction unit of fuel feed program C_f-ab with fuel feed automatic device.

EFFECT: optimised thrust in afterburner conditions.

1 dwg