Aeroengine main combustion chamber based on plasma jet ignition and combustion

Abstract

A main combustion chamber of an aero-engine based on plasma jet ignition and combustion comprises a combustion outer casing, a flame tube and a plasma jet igniter. The flame tube is located in the outer casing of the combustion chamber, and the plasma jet igniter is located at the upper end of the flame tube, wherein the jet outlet extends into about one-third of the flame tube, and the plasma jet igniter is connected to the inlet end of the combustion chamber through an external thread. The outer casing of the combustion chamber, the flame tube and the plasma jet igniter are coaxial. The present invention is based on a very small aero-engine with plasma jet ignition and combustion. And the weight and volume of the combustion chamber, improve the ignition reliability of the aero-engine combustion chamber, and then improve the performance of the aero-engine.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a structure of a main combustion chamber of an extremely small aero-engine based on plasma jet ignition and combustion. Background technique [0002] At present, the main combustion chamber of the aviation turbine engine used on the aircraft includes the main combustion chamber air inlet channel 1, the spark plug igniter 2, the flame cylinder 3, the combustion chamber outlet 4, the fuel nozzle 5, the combustion chamber 6 and the flame cylinder diffusion In section 7, the head of the combustion chamber with swirler is basically used, and at the same time, electric spark is used for ignition. The combustion chamber of this ignition method has many shortcomings, and due to the limitation of the principle, there is little room for improvement. Combustion chambers based on swirlers and spark ignition mainly have the following disadvantages: [0003] 1. The swirler at the head of the main ...

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Problems solved by technology

[0003] 1. The swirler at the head of the main combustion chamber of a traditional aero-engine promotes the rotation of the incoming air, reduces the flow velocity, and causes a large flow loss of the airflow entering the combustion chamber;

[0004] 2. The volume of the combustion area produced by the swirler is relatively large, and the airflow entering from the main combustion hole on the rear side of the combustion chamber is large, which increases the length of the combustion chamber, resulting in a substantial increase in the volume and weight of the combustion chamber;

[0005] 3. The ignition energy of the spark plug is small, and the mixture cannot be ignited smoothly under many conditions, especially at high altitudes, where the ignition boundary is small and the ignition success rate is low;

[0006] 4. Due to the small flame propagation velocity and the fast airflow propagation velocity, the flame is stabilized by the backflow boundary during ignition and combustion, and the airflow loss is further increased

[0011] GE Corporation of the United States, Siemens Engine Precision Systems Corporation, and Aviation Plasma Technology Corporation applied for a number of patents after 1992 on the main combustion chamber or afterburner of aeroengines, but they basically applied for plasma jet ignition. There is also no integration of the igniter, fuel injector and combustion chamber

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