Supersonic airflow generation system beneficial to uniform scattering of nano particles

Abstract

The invention provides a supersonic airflow generation system beneficial to uniform scattering of nano particles. The system comprises a first stabilizing section, a second stabilizing section, a spray pipe test section and an outlet section in sequential fixed connection. The first stabilizing section comprises a cavity, gas inlets, nano particle inlets, a hole throttling part and a stabilizing net. The stabilizing net is positioned in the middle of the cavity to partition the cavity into a first stabilizing section front portion and a first stabilizing section rear portion; the gas inlets are symmetrically distributed on two sides of the first stabilizing section front portion and connected with a high-pressure gas source; the nano particle inlets are distributed, close to the gas inlets, on the first stabilizing section front portion and perpendicularly axially intersected with the gas inlets. The supersonic airflow generation system is capable of isolating a supply pipeline from mutual interference of pressure fluctuation of a wind tunnel stabilizing section to provide uniform, continuous, low-turbulivity and high-total-pressure supersonic airflow, and uniform scattering of the nano particles in high-pressure airflow can be realized.

Description

technical field [0001] The invention relates to the wind tunnel test technology in the field of aerospace, in particular to a supersonic airflow generation system which is beneficial to the uniform distribution of nanoparticles. Background technique [0002] Adequate mixing of fuel and oxidant is a prerequisite for efficient combustion. In a scramjet, the liquid fuel undergoes atomization, evaporation, mixing, and combustion in the supersonic air flow. Evaporation and mixing processes are decisive for the engine's ignition and efficient combustion. It is generally believed that an effective hypersonic propulsion system requires enhanced fuel-air mixing, fuel injection at the expense of lower drag, and efficient distribution of fuel across the combustion chamber cross-section. [0003] In order to reveal the inherent laws of liquid jet atomization and mixing in supersonic airflow, researchers have carried out a large number of experimental studies on this topic. Lai Lin "S...

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Problems solved by technology

[0007] 1. Transverse jet flow research in the air-breathing wind tunnel cannot simulate the Reynolds number of the incoming flow in the real flight state, and the Reynolds number is an important parameter for flow similarity; at the same time, due to the limitation of the total pressure of the incoming flow, it is not easy in the air-breathing wind tunnel Conducting Back Pressure Effects Study Tests

[0008] 2. Installing a rectifier device in the stable section of the wind tunnel can achieve a certain rectification effect, but the total pressure loss is large, and the space length of the rectifier is relatively large, especially for the down-blown wind tunnel, the length of the stable section and the rectifier is larger, and it cannot be used in the wind tunnel. Effectively reduce the turbulence of the flow field in a limited space

[0009] 3. The method of installing a suction device in front of the nozzle can effectively reduce the turbulence of the flow field and improve the uniformity of the flow field, but the structure of the suction device is complex and difficult to implement, and this method still needs to be used with a rectification device

[0010] 4. There are problems in the distribution of nanoparticles, and the problem of agglomeration of nanoparticles cannot be further improved. The process of mixing nanoparticles and gas is a passive mixing process, mainly due to natural mixing during the flow process, which cannot achieve the best uniform distribution of nanoparticles Effect

[0011] 5. The pressure fluctuation of the supply pipeline and the pressure fluctuation in the stable section of the wind tunnel are likely to cause mixed interference, which affects the stability of the downstream flow field

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