Turbojet engine with afterburner and thrust augmentation ejectors

A thrust propulsion unit for an aircraft comprising:

• an engine capable of producing thrust by expulsion of hot gases at or near sonic or greater velocity through a portal;
• and
• a primary ejector connected to said engine comprising:
• primary air intake means connected to said engine for directing ambient air to an intake end of a primary ejector duct;
• a primary ejector duct, connected to said engine and having a lateral cross sectional area greater than said portal, comprising:
• an intake end disposed to receive the gases expelled from said engine portal and the air from said primary air intake means;
• and
• an exhaust end for expelling combined the gases and air received by said intake end;
• and
• an auxiliary ejector connected to said engine comprising:
• auxiliary air intake means connected to said engine for directing ambient air to an intake end of an auxiliary ejector duct;
• an auxiliary ejector duct, connected to said engine and having a lateral cross sectional area greater than the lateral cross section of said primary ejector duct, comprising:
• an intake end disposed to receive the gases expelled from said exhaust end of said primary ejector duct and the air from said auxiliary air intake means;
• a flame holder assembly mounted in said auxiliary ejector duct in the combined flow of the gasses expelled by said engine and the air from said intake means for combustion of the combined flow;
• and
• a exhaust end for expelling combined the burned gases and air received by said intake end of said auxiliary ejector duct, such that the momentum of the burned gasses and air exiting said exhaust end of said auxiliary duct is greater than the momentum of the gasses expelled from said engine portal.

A thrust enhancer for a turbojet engine of the type having a combustion chamber, a turbine for receiving hot gases from said combustion chamber, an afterburner duct connected to the output of said turbine for receiving turbine discharge gas, a turbine bypass duct connecting said combustion chamber with said afterburner duct for receiving hot combustion chamber gasses from said combustion chamber and for tangentially injecting the received hot gasses at high speed into said afterburner duct such that a flame stabilizing vortex is created of the injected gasses and the received turbine discharge gas, said afterburner duct including a nozzle out of which the hot gases are expelled at near sonic or greater velocity, said thrust enhancer comprising:

• an ejector connected to said engine comprising:
• air intake means connected to said engine for directing ambient air to an intake end of a duct;
• a duct, connected to said engine and having a lateral cross sectional area greater than said afterburner nozzle, comprising:
• an intake end disposed to receive the gases expelled from said afterburner nozzle and the air from said air intake means;
• a flame holder assembly mounted in said duct in the combined flow of the gasses expelled by said engine and the air from said intake means for combustion of the combined flow:
• and
• an exhaust end for expelling combined the burned gases and air received by said intake end, such that the momentum of the burned gasses and air exiting said exhaust end of said auxiliary duct is greater than the momentum of the gasses expelled from said engine portal.

A thrust enhancer for a turbojet engine of the type having a combustion chamber, a turbine for receiving hot gases from said combustion chamber, an afterburner duct connected to the output of said turbine for receiving turbine discharge gas, a turbine bypass duct connecting said combustion chamber with said afterburner duct for receiving hot combustion chamber gasses from said combustion chamber and for tangentially injecting the received hot gasses at high speed into said afterburner duct such that a flame stabilizing vortex is created of the injected gasses and the received turbine discharge gas, said afterburner duct including a nozzle out of which the hot gases are expelled at near sonic or greater velocity, said thrust enhancer comprising:

• a primary ejector connected to said engine comprising:
• primary air intake means connected to said engine for directing ambient air to an intake end of a primary ejector duct;
• a primary ejector duct, connected to said engine and having a lateral cross sectional area greater than said afterburner nozzle, comprising:
• an intake end disposed to receive the gases expelled from said afterburner nozzle and the air from said primary air intake means;
• and
• an exhaust end for expelling combined the gases and air received by said intake end;
• and
• an auxiliary ejector connected to said engine comprising:
• auxiliary air intake means connected to said engine for directing ambient air to an intake end of an auxiliary ejector duct;
• an auxiliary ejector duct, connected to said engine and having a lateral cross sectional area greater than the lateral cross section of said primary ejector duct, comprising:
• an intake end disposed to receive the gases expelled from said exhaust end of said primary ejector duct and the air from said auxiliary air intake means;
• and
• a exhaust end for expelling combined the gases and air received by said intake end of said auxiliary ejector duct, such that the momentum of the gasses and air exiting said exhaust end of said auxiliary duct is greater than the momentum of the gasses expelled from said engine portal.