Turbojet engine with afterburner and thrust augmentation ejectors

摘要

A thrust propulsion unit for an aircraft comprises an engine, such as a turbojet engine with afterburner or a rocket engine, capable of producing thrust by expulsion of hot gases at near sonic or greater velocity through a nozzle portal and a primary ejector connected to the engine comprising a primary air intake for directing ambient air to an intake end of a primary ejector duct and a primary ejector duct having a lateral cross sectional area greater than the nozzle portal. The primary ejector duct receives the gases expelled from the engine portal and the air from the primary air intake and expels them out an exhaust end with increased momentum. An auxiliary ejector may be provided including an auxiliary air intake for directing ambient air to an intake end of an auxiliary ejector duct and an auxiliary ejector duct having a lateral cross sectional area greater than the lateral cross section of the primary ejector duct, an intake end disposed to receive the gases expelled from the exhaust end of the primary ejector duct and the air from the auxiliary air intake and an exhaust end which may flare to form a diffuser. An ejector duct may include a flame holder assembly including ignitor and atomizer.