Fuel Control System For A Gas Turbine Engine Of An Aircraft
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United States of America Patent
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Dec 8, 2016
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Dec 11, 2015
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Abstract
A fuel control system for a gas turbine engine of an aircraft having an engine gearbox, a fuel tank, and an engine combustion chamber, wherein the system includes a high pressure fuel pump, at least one electrically controlled fuel injector, a fuel pressure and temperature sensors, and a fuel controller coupled with the sensors to calculate the fuel density, the controller being also coupled with the fuel injector to determine the fuel flow injection rate, the controller being further coupled with the fuel pump to establish a pump output pressure value, according to the fuel density and the flow injection rate of the pumped fuel, such that a constant fuel pressure value is supplied to the fuel injector, to finally inject a constant high fuel injection pressure in the combustion chamber.
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