A Central Ignition Mechanism of Scramjet Combustion Chamber

Abstract

The invention discloses a central igniting mechanism of a combusting chamber of a scramjet engine. The mechanism comprises a front blunt body, a back blunt body, a concave cavity which is formed between the front blunt body and the back blunt body, and flow passage compensating sections, wherein the concave cavity is formed in a main flow; the flow passage compensating sections are positioned on both sides of each of the front blunt body 1 and the back blunt body 2. The mechanism is characterized in that the concave cavity is built in the combusting chamber of the scramjet engine to generate a low-speed recirculation zone, fuel oil is supplied into the low-speed recirculation zone to combust to form a stable sub combustion zone, a supersonic flow is ignited in the stable sub combustion zone to realize the supersonic high-efficiency combustion, and the problem that the main supersonic flow cannot be ignited because the fuel oil and the flame at the position of the concave cavity are not easy to spread to the center of the flow passage is solved. The igniting mechanism disclosed by the invention can realize multi-point and multi-section oil spraying in the center and on the wall surfaces, and the scramjet combustion can be reasonably controlled.

Description

technical field [0001] The invention belongs to the technical field of scramjet engines, in particular to a central ignition mechanism of a scramjet combustion chamber. Background technique [0002] Because the air velocity in the scramjet combustion chamber is very fast, greater than the speed of sound, the time for the mixed gas to stay in the combustion chamber is only a few milliseconds. It is very difficult to ignite the mixed gas directly in the supersonic flow, and the ignition and flame stability in the supersonic combustion chamber is a key technology that needs to be solved urgently for the scramjet engine. In order to solve the ignition and flame stabilization problems in supersonic airflow, the local subsonic low-velocity zone is usually used to form an ignition source, and the subsonic combustion zone is used to heat and ignite the supersonic flow. Therefore, a low-velocity recirculation zone needs to be constructed in the flow field. In the existing scramjet c...

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Problems solved by technology

[0003] The problem to be solved by the present invention is to construct a concave cavity in the combustion chamber of a scramjet to generate a low-velocity recirculation zone, supply fuel oil to burn in the low-velocity recirculation zone to form a stable sub-combustion zone, and use the sub-combustion zone to ignite the supersonic flow to realize Supersonic high-efficiency combustion avoids the problem that the fuel and flame in the concave cavity are not easy to spread to the center of the flow channel, resulting in the failure to ignite the supersonic mainstream

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