FIELD: engines and pumps.
SUBSTANCE: proposed system comprises pump to feed fuel into combustion chamber and pump to feed fuel into engine control units. The latter have their inlets communicated with fuel boost pump and their outlets communicated, via engine ACS fuel feed controller. Pump to feed fuel into combustion chamber is coupled with engine shaft via hydrodynamic torque converter with its inner chamber communicated via jet pump and check valve with the inlet of pump to feed fuel into combustion chamber, and, via switch, with pressure chamber of said pump, as well as via extra jet pump with fuel boost pump inlet. Hydrodynamic converter control element and switch control chamber are connected to engine ACS fuel feed controller.
EFFECT: reduced overheat in fuel feed system elements, hence, their longer life, lower thermal visibility of aircraft.
3 cl, 3 dwg
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