FIELD: engines and pumps.
SUBSTANCE: fuel supply system of gas turbine engine is intended for fuel systems of aircrafts, in which engines are located above the main fuel tanks. System comprises the main pump-controller with serially installed make-up centrifugal and gyrating stages. Relief valve with servopiston is installed at gyrating stage. Inlet of valve via filter is connected to outlet of gyrating stage, and its outlet - to its inlet. Piston cavity of servopiston is connected to inlet of centrifugal stage, and stem cavity of valve - to its outlet. Valve is controlled by value of difference at centrifugal stage.
EFFECT: increased reliability of system operation in case of release of air dissolved in fuel, or in case of inlet pipeline damage, and also to reduce system weight and consumed power.
1 dwg
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