Patent ID: 6810671
Filing Date: 2004-11-02
Classification: F02C,F05D

Abstract:
A fuel supply system for an aircraft equipped with at least one gas turbine engine and at least at least one fuel tank, comprising:a low pressure pump; a first fuel line connecting the fuel tank to the low-pressure pump from the fuel tank to the low-pressure pump; a high pressure pump; a second fuel line connecting the high-pressure pump to the low-pressure pump downstream of the low-pressure pump for supplying fuel from the low-pressure pump to the high-pressure pump; a fuel return line connected downstream of at least one of the low-pressure pump and the high-pressure pump for returning excess fuel to the fuel tank; a recirculation valve connected to the fuel return line for controlling flow of the excess fuel to the fuel tank; and a pressure signal device connected to the first fuel line, for detecting a low pressure situation in the first fuel line and signaling the recirculation valve to increase flow of excess fuel to the fuel tank in response thereto.