Gas Turbine Engine Fuel System for an Aircraft Propulsion System

A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:

• a vented fuel tank;
• a first fuel pump and a second fuel pump, the first fuel pump includes a fuel inlet and a fuel outlet, the fuel inlet is connected in fluid communication with the vented fuel tank, and the fuel outlet is connected in fluid communication with the second fuel pump;
• an inlet ejector including an ejector nozzle, the ejector nozzle includes an ejector nozzle inlet and an ejector nozzle outlet, and the ejector nozzle outlet is disposed in fluid communication with the first fuel pump at the fuel inlet;
• and
• an ejector control valve connected in fluid communication between the fuel outlet and the ejector nozzle inlet, and the ejector control valve is selectively positionable in an open position or a closed position to control a flow of fuel from the fuel outlet, through the ejector nozzle, and to the ejector nozzle outlet.