초록 ▼

A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to b

A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.

대표청구항 ▼

1. A method of thrust augmenting a jet turbine engine on an aerospace vehicle, comprising the steps of: injecting liquid oxidizer into a duct upstream of an engine compressor section, and evaporating to injected liquid oxidizer, to create oxidizer vapor, in a stream of air containing oxygen flowi

1. A method of thrust augmenting a jet turbine engine on an aerospace vehicle, comprising the steps of: injecting liquid oxidizer into a duct upstream of an engine compressor section, and evaporating to injected liquid oxidizer, to create oxidizer vapor, in a stream of air containing oxygen flowing into the engine compressor section; compressing the stream of air, and the oxidizer vapor in the engine compressor section; burning a portion of the oxidizer vapor, and oxygen in the air with an oxidizable fuel, to create an oxidizer rich combustion stream within a combustion chamber downstream of the engine compressor section; extracting energy from the oxidizer rich combustion stream with a power turbine downstream of the combustion chamber, and driving the compressor section with the output of the power turbine; afterburning the oxidizer rich combustion stream with additional oxidizable fuel, to create an exhaust gas stream in an afterburner chamber downstream of the power turbine; and accelerating the exhaust gas stream through a nozzle to develop thrust, wherein sufficient liquid oxidizer is injected into the duct upstream of the engine compressor section to increase the unaugmented thrust of the engine by approximately five times when said injected sufficient liquid oxidizer is combusted with the oxidizable fuel and the additional oxidizable fuel. 2. The method of claim 1 wherein the liquid oxidizer is liquid oxygen. 3. The method of claim 1 wherein the liquid oxidizer is selected from the group consisting of nitrogen tetroxide, nitrous oxide, liquid air, hydrogen peroxide and a hydrogen peroxide water solution. 4. The method of claim 1 wherein the afterburning of the oxidizer rich combustion stream with additional oxidizable fuel is to approximate stoichiometric conditions. 5. The method of claim 1 wherein the step of injecting a selected quantity of liquid oxidizer is conducted through an injector mounted to inject oxidizer radially inwardly of the duct inlet inner surface.