A fuel pumping system of an aircraft, having a first boost pump; a main pump; a main pump feed conduit fluidly coupled to the main pump and configured to receive fuel after it has passed through the first boost pump; a main pump discharge conduit fluidly coupled to the main pump; an ejector fluidly coupled to the main pump feed conduit, between the first boost pump and the main pump; a bypass conduit fluidly coupled to the main pump discharge conduit and the ejector such that the bypass conduit is configured to provide fluid to the ejector drawn from the output of the first boost pump into the main pump; and a backpressure regulating valve fluidly coupled to the bypass conduit, and configured to transition to an open state when pressure in the main pump discharge conduit is above a threshold.
AIRCRAFT FUEL PUMPING SYSTEM
09.11.2023
Patent
Elektronische Ressource
Englisch
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