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

FIELD: engines and pumps.

SUBSTANCE: proposed invention can be used in control systems of aircraft and electric power station gas turbine engines (GTE). Proposed control system comprises engine parametres pickups that can be connected with amplifiers connected with adder, metering unit feeding fuel into engine combustion chamber, two comparators. First input of the second comparator is connected with engine mode setter. System incorporates also minimum selector and isodromic governor. Additionally, control system comprises adapter, limiter, units to convert logarithm and anti-logarithm with inputs connected with adder output and its output connected with second input of second comparator. Output of second comparator is connected with second input of minimum selector with its first input connected with output of first comparator. Minimum selector output is connected with isodromic governor second input. First input of the latter is connected with adapter and output connected with metering unit. Note that every pickup is connected with its logarithm conversion unit. Output of every conversion unit is connected with input of its amplifier. Outputs of amplifiers are connected with adder inputs. Note also that pickups are connected with adder inputs. Mind that pickups are additionally connected with first input of first comparator with its second input connected with parametre limiting unit.

EFFECT: higher accuracy of gas turbine control.

1 dwg