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AssigneeThe United States of America as represented by the United States National Aeronautics and Space Administration Office of General Counsel-Code GP
InventorsGeorge A. Coffinberry, Howard B. Kast
Estimating the term…
A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure. In addition, fluid circuitry is provided to route hot engine oil through a plurality of heat exchangers disposed within the system to provide for selective cooling of the oil.
In a method of operating a gas turbine engine fuel delivery and control system, the steps of:
In a method of operating a gas turbine engine fuel delivery and control system, the steps of:
In a method of operating a gas turbine engine fuel delivery and control system, the steps of:
Dependencies are inferred from the claim text.