TURBINE ENGINE CONTROL SYSTEM, AIRCRAFT ENGINE FUEL DELIVERY SYSTEM

摘要

A fuel flow control system for turbine engine compries a hot-start overtemperature avoidance system. The fuel line to the engine nozzle includes a pump (15) having a pressure regulation bypass and additionally, a trim line (33) connecting the main fuel control (17) to the inlet of pump (15). The main fuel control (17) delivers fuel to the nozzle via line (19). A solenoid valve (21) is used to reduce the fuel flow at start-up depending on the engine speed detectors (37, 39, 43) and the exhaust gas sensors (35).