Abstract: A fuel flow system for a gas turbine engine includes a first pump, a second pump, a bypass loop, an integrating bypass valve and a pilot valve. The first pump connects to an actuator and a metering valve. The second pump connects to the metering valve and is arranged in parallel with the first pump. The bypass loop recycles fuel flow from the first pump and the second pump to inlets of the first pump and second pump integrating bypass valve includes first and second windows. The first window regulates fuel from the first pump through the bypass loop and the second window that regulates fuel from the second pump through the bypass loop. The pilot valve controls the size of the first and second windows.

Abstract: A fuel flow system for a gas turbine engine includes a first pump, a second pump, a bypass loop, an integrating bypass valve and a pilot valve. The first pump connects to an actuator and a metering valve. The second pump connects to the metering valve and is arranged in parallel with the first pump. The bypass loop recycles fuel flow from the first pump and the second pump to inlets of the first pump and second pump integrating bypass valve includes first and second windows. The first window regulates fuel from the first pump through the bypass loop and the second window that regulates fuel from the second pump through the bypass loop. The pilot valve controls the size of the first and second windows.

Abstract: A fluid flow system for a gas turbine engine provides combustion fuel to a main pump and an actuator pump significantly reducing heat generation at low flow demand, while regulating actuator flow temperature at high flow demand. Fuel flow from the actuator pump in excess of the actuators needs is directed through an actuator minimum pressure valve and into a thermal bypass valve (TBV.) Depending upon the temperature of the fuel, the TBV determines the path of the excess actuator pump fluid flow. The TBV divides the fuel flow between being recirculated to the actuator pump inlet and the main pump output flow path to the engine fuel input conduit. The engine actuators are thereby assured of receiving flow which preclude freezing of water entrained in the fuel. When there is minimal concern with the possibility of freezing water entrained in the fuel, the TBV passes a greater percentage of fuel through to join together in the engine fuel input conduit.

Abstract: A fluid flow system for a gas turbine engine provides combustion fuel to a main pump and an actuator pump significantly reducing heat generation at low flow demand, while regulating actuator flow temperature at high flow demand. Fuel flow from the actuator pump in excess of the actuators needs is directed through an actuator minimum pressure valve and into a thermal bypass valve (TBV.) Depending upon the temperature of the fuel, the TBV determines the path of the excess actuator pump fluid flow. The TBV divides the fuel flow between being recirculated to the actuator pump inlet and the main pump output flow path to the engine fuel input conduit. The engine actuators are thereby assured of receiving flow which preclude freezing of water entrained in the fuel. When there is minimal concern with the possibility of freezing water entrained in the fuel, the TBV passes a greater percentage of fuel through to join together in the engine fuel input conduit.