Method for improving fuel mixing of scramjet engine through unstable movement of shock wave string
A scramjet engine technology, applied in the direction of combustion methods, combustion chambers, combustion equipment, etc., can solve the problems of insufficient fuel mixing in scramjet engines, and achieve the effect of improving work performance and efficiency
Active Publication Date: 2021-03-26
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology
The purpose of the present invention is to solve the problem of insufficient fuel mixing in the scramjet engine, in order to improve the fuel mixing effect in the scramjet engine by using the large unstable movement of the shock wave train itself without adding additional devices , improve engine performance
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[0017] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.
[0018] according to figure 1 Flowchart for the design of the scramjet fuel blending method using the unstable motion of the shock train, when the shock train is located outside the shock-boundary layer interference region figure 2 The dynamic mode of its internal flow is given, and there is no obvious longitudinal unstable flow. When the shock train is located in the shock wave-boundary layer interference region image 3 It shows that the internal flow has obvious longitudinal unstable flow, and this method can form longitudinal unstable flow inside the shock train, thereby enhancing the mixing effect of fuel and air.
[0019] The method steps of this embodiment are:
[0020] Step 1: According to the working Mach number and flight altitude of the scramjet engine, query the standard atmospheric parameter table to obtain the static pressure and static ...
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The invention provides a method for improving fuel mixing of a scramjet engine through unstable movement of a shock wave string. which comprises the following steps of: giving incoming flow through asupersonic spray pipe and a gas distribution console to obtain stable-state data of each pressure measuring point in a through-flow state of an isolation section of the scramjet engine, dividing the neighborhood of the wave crest position in the on-way pressure distribution of the isolation section into an interference area of a shock wave boundary layer in the isolation section, adjusting the equivalent ratio of an engine through a fuel supply system, and changing different back pressures at an outlet of the isolation section until a pressure measuring point signal periodically fluctuates. Unstable movement of the shock wave string can be effectively utilized, and the longitudinal unstable flow generated by the oscillation characteristic of the shock wave string is utilized under the condition of not adding extra devices and total pressure loss, so that the fuel is mixed with main flow in the engine. The mixing effect of fuel and air of the scramjet engine can be improved within a short distance, the efficiency of a combustion chamber is improved, and the working performance of an engine is improved.
Description
technical field [0001] The invention relates to the field of hypersonic propulsion, in particular to a scramjet fuel mixing method. Background technique [0002] The scramjet engine relies on the shock wave generated by its own intake port to compress the incoming flow without rotating mechanical devices. It has the characteristics of high specific impulse, simple structure, and fast speed. Therefore, the scramjet engine is the first choice for hypersonic flight. The system is widely used in hypersonic aircraft, hypersonic cruise missiles and other fields. [0003] For a scramjet engine, the residence time of the airflow in the combustion chamber is on the order of milliseconds. In this extremely short time, it is necessary to complete the mixing and combustion of the fuel and the main flow. If better blending cannot be achieved, the fuel will not be fully organized for combustion, and the thrust will be severely reduced, which will seriously affect the performance of the ...
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IPC IPC(8): F23R3/28
CPCF23R3/286
Inventor 李楠张伟伟
Owner NORTHWESTERN POLYTECHNICAL UNIV