| 摘要 |
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 |
