Extended operability aircraft fuel delivery system
AssigneeUnited Technologies Corporation
InventorsLouis Spadaccini, Scott Kaslusky, Robert McLaughlin
Life of this patent
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Abstract
A fuel delivery system for a gas turbine engine includes a main fuel pump supplying fuel to a fuel-metering device. The operational flow range of the fuel system is dependent on a minimum net positive suction pressure at the main pump inlet required to prevent pump cavitation. A mixture of fuel and dissolved gases increases the minimum net positive suction pressure required to prevent cavitation. A fuel de-aerator including a permeable membrane removes dissolved gases from the fuel to eliminate formation of dissolved gases. The elimination of dissolved gases from within the liquid fuel reduces the required net positive suction pressure, enabling a greater operational flow range.
Claims13
1-18. (canceled)
A method of improving fuel system operational capacity comprising the steps of:
- a) flowing fuel containing dissolved gases through a de-aerator;
- b) removing dissolved gases from fuel within the de-aerator;
- and
- c) flowing fuel to an inlet of a main fuel pump at a required net positive suction pressure.
A method of operating a fuel system for a gas turbine engine assembly comprising the steps of:
- a) supplying fuel from a fuel source to a main fuel pump at a net positive suction pressure;
- b) removing dissolved gases from fuel supplied to the main fuel pump with a fuel de-aerator including a membrane filter permeable to gases dissolved within the fuel.
Dependencies are inferred from the claim text.