An injection system based on two-component liquid fuel mixing reaction

Abstract

The invention discloses an injection system based on the mixed reaction of two-component liquid fuels, which relates to the technical field of scramjets, and includes an injection panel group, a first fuel control system and a second fuel control system. Connected with the first fuel control system and the second fuel control system; the injection panel group is configured so that the first liquid fuel and the second liquid fuel injected into the injection can be quickly mixed and reacted efficiently, and the first liquid fuel and the second liquid fuel can be mixed at the same time. The high heat released after the reaction of the two liquid fuels and the generated intermediate active substances are injected into the combustion chamber to realize the ignition reaction of the scramjet when flying under the condition of low Mach number (Mach number < 4.0); the first liquid fuel is The boron-containing complex, the second liquid fuel is an unsaturated hydrocarbon. The system of the invention is simple in structure, safe and efficient, and solves the problem that the scramjet engine is not easy to catch fire under the condition of low Mach number.

Description

technical field [0001] The invention relates to the technical field of scramjets, in particular to an injection system based on the mixed reaction of two-component liquid fuels. Background technique [0002] A scramjet is a ramjet in which fuel is burned in a supersonic airflow. When using hydrocarbon fuel, the flight Mach number of the scramjet is below 8. Because the scramjet works in the supersonic airflow, it can obtain oxygen from the atmosphere during the climbing process and give up carrying the oxidant. It has the advantages of simple structure, light weight and low cost. [0003] However, it cannot start by itself in a static state, and it must be pushed to a certain speed by a boosting method before it can work effectively, and its low-speed performance is not good. Especially in scramjet combustion chambers flying at low Mach numbers (Mach number < 4.0), reliable ignition and efficient combustion of hydrocarbon fuels remains a challenge. The total temperatur...

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Problems solved by technology

[0007] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present invention is to develop a system with simple structure, reliable and safe operation based on the content disclosed in the above-mentioned patents and to improve the ambient temperature of the combustion chamber to solve the problem of scram Difficult ignition problem when the engine is flying at low Mach number (Mach number<4.0)

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