초록 ▼

A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydraulic pump to provide pressurized fluid for e

A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydraulic pump to provide pressurized fluid for exhaust nozzle actuation. An augmentor fuel bypass arrangement is provided to enable the augmentor fuel pump to provide pressurized fuel to the main fuel pressurizing valve and to components operated by the main fuel system in the event of failure of the main fuel pump. The augmentor fuel pump pressure and output flow are controlled as a function of thrust augmentation demand and main fuel system operation. The system provides redundancy by enabling either the main fuel system or the augmentor fuel system to maintain engine operation if one of the fuel systems fails or provides inadequate fuel flow.

대표청구항 ▼

1. A fuel system for an augmented aircraft gas turbine engine, said fuel system comprising:a main fuel system including a main fuel pump for providing pressurized fuel to a main engine combustion chamber; an augmentor fuel system including a unitary, variable displacement augmentor fuel pump for pro

1. A fuel system for an augmented aircraft gas turbine engine, said fuel system comprising:a main fuel system including a main fuel pump for providing pressurized fuel to a main engine combustion chamber; an augmentor fuel system including a unitary, variable displacement augmentor fuel pump for providing pressurized fuel to a thrust augmentation system, wherein the augmentor fuel system is operatively connected with at least one engine variable geometry control system for providing pressurized augmentor fuel for operating at least one pressurized-fluid-operated actuator for positioning a variable geometry element of the at least one engine variable geometry system in response to engine operating conditions and power output demands, and wherein the augmentor fuel pump is driven independently of the main fuel pump.