Partially premixed preevaporation dual-channel injection device for rotary detonation engines

Abstract

The invention discloses a partially premixed preevaporation dual-channel injection device for a rotary detonation engine, which comprises a front flange, an outer ring, an inner ring, a guide tube, an oil injection ring and a cyclone. The guide tube divides the passage into two passages: the large flow passage is used as the mainstream air passage, and is directly connected to the rotary detonation combustion chamber through the throat; The air in the channel flows in for preliminary mixing; the cyclone further enhances the circumferential mixing effect of the mixed air in the pre-mixed pre-evaporation channel. The outlet of the channel is located upstream of the throat, and the pre-mixed gas and Further mixing of mainstream air. The invention effectively shortens the mixing distance of liquid fuel and air, so that the mixing effect of liquid fuel and air in the main combustion chamber is enhanced; at the same time, it effectively prevents the flame in the combustion chamber from returning to the upstream, and realizes the stable operation of the rotary detonation engine .

Description

technical field [0001] The invention relates to the field of aviation technology, and relates to a partially premixed and preevaporated dual-channel injection device for a rotary detonation engine. Background technique [0002] The rotary detonation engine is a new type of engine that uses detonation combustion to generate thrust. Compared with traditional detonation combustion, detonation combustion produces chemical reactions through the leading shock wave compression reactants, and its flame propagation speed can reach kilometers per second. The fuel can release heat more quickly during the combustion process, so the detonation combustion has higher combustion efficiency. At present, the rotary detonation engine mainly adopts the annular combustion chamber, and the rotating detonation wave propagates along the circumferential direction in the annular combustion chamber. Since the injection direction of the fuel and oxidant is perpendicular to the propagation direction of ...

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Problems solved by technology

[0003] At present, the research on the rotary detonation engine model is mainly based on gaseous fuel, the injection of fuel and oxidant is mainly in the form of separate injection, and the fuel and oxidant are mixed and burned while injecting in the detonation combustion chamber. The first injection method can easily cause uneven mixing of fuel and oxidant when the volatility of the fuel is poor, which has a great impact on the stable propagation of the detonation wave

When the fuel is a liquid fuel, the fuel needs to go through the process of atomization and evaporation before being evenly mixed with the oxidant. Compared with the working characteristics of the rotary detonation combustion chamber, this process requires a long time and a large space. If the above blending method is used, the length of fuel blending in the combustion chamber will be increased, and the height of the fresh air mixture will be increased, which will have an adverse effect on the propagation characteristics of the detonation wave in the combustion chamber and the performance of the detonation engine.

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