Oil cooling system for a gas turbine engine

摘要: A gas turbine engine fuel delivery and control system is provided with means to recirculate all in excess of requirements back the aircraft tank, thereby increasing pump heat sink decreasing temperature rise without addition valving other than that normally employed. fuel/oil exchanger associated circuitry maintain hot oil exchange relationship cool fuel. Where anti-icing filter required, are entering at or above a minimum level prevent freezing thereof. In one embodiment, divider valve take from either upstream downstream route it tanks, ratio extraction being function discharge pressure. addition, fluid through plurality exchangers disposed within provide for selective cooling oil.