Fuel injector control method for combustion chamber of aircraft engine, involves respectively comparing rising and descending flow rates of injector with reference flow rates to determine homogeneity of injector relative to set of injectors

摘要

The method involves acquiring rising flow rate of a fuel injector (23) for increasing pressure gradients, and acquiring descending flow rate of the injector for decreasing pressure gradients. The rising and descending flow rates of the injector are respectively compared with reference rising and descending flow rates in an independent manner according to a homogenization criterion so as to determine homogeneity of the injector with respect to a set of injectors intended for a combustion chamber. The homogenization criterion is defined by allowable limits of heterogeneities. An independent claim is also included for a system for controlling a fuel injector mounted in a combustion chamber of an engine of an aircraft.