Supersonic combustion chamber fuel injection design method based on air inlet channel non-uniform airflow

A supersonic combustion chamber and combustion chamber technology, applied in design optimization/simulation, instrumentation, electrical digital data processing, etc., can solve problems such as injection dispersion and penetration depth limitation, so as to improve thrust performance and improve blending combustion efficiency Effect

Active Publication Date: 2021-04-16
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

However, due to the dispersion of the injection, the penetration depth of a single injection hole is limited by the area of ​​the injection hole and the injection pressure

Method used

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  • Supersonic combustion chamber fuel injection design method based on air inlet channel non-uniform airflow
  • Supersonic combustion chamber fuel injection design method based on air inlet channel non-uniform airflow
  • Supersonic combustion chamber fuel injection design method based on air inlet channel non-uniform airflow

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Embodiment Construction

[0048]In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present application, and are not intended to limit the present application.

[0049] A supersonic combustor fuel injection design method based on non-uniform airflow in the intake port provided by this application can be applied to such as figure 1 shown in the application environment. figure 1 Shown is the side wall surface of the side section of the supersonic combustion chamber, where 101 is the supersonic inlet, 102 is the injection section of the supersonic combustion chamber, 103 is the concave cavity flame stabilizer, 104 is the engine tail nozzle, and 105 is the engine profile The central axis, 106, is the incoming air from the combustion ch...

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Abstract

The invention relates to a supersonic combustion chamber fuel injection design method based on air inlet channel non-uniform airflow, and the method comprises the steps: obtaining spray hole parameters of a combustion chamber according to supersonic air inlet channel parameters and engine parameters, wherein the spray hole parameters comprise the number of spray holes, spray hole groups and spray hole aperture ranges; obtaining the set distance range of the spray hole according to the fuel diffusion characteristic and the ignition delay characteristic; obtaining the set angle range of the spray holes according to the distribution angle of the low-speed airflow area in the combustion chamber, and obtaining the global equivalent ratio of each group of spray holes according to the angle proportion of the distribution angle in the airflow flow direction section. According to the method, the arrangement mode of the spray holes is determined based on the circumferential distribution characteristics of the airflow velocity of the fuel on the flow direction section of the combustion chamber, the circumferential and radial blending combustion efficiency of the fuel on the circular section of the combustion chamber can be improved, and then the engine thrust performance is improved.

Description

technical field [0001] The present application relates to the field of supersonic combustor configuration design, in particular to a supersonic combustor fuel injection design method based on non-uniform airflow in the intake port. Background technique [0002] The high air velocity and short fuel residence time in the scramjet combustion chamber make it very difficult to organize robust and efficient combustion. Therefore, it is necessary to adopt a suitable fuel injection scheme to achieve efficient mixed combustion of fuel and incoming flow. The fuel injection scheme is usually combined with the flame stabilization scheme in the combustion chamber. It is usually divided into two categories. One is the injection scheme of the branch plate in the combustion chamber. Hole injection, direct mixed combustion with the incoming air in the flow channel; the other is the horizontal jet injection scheme on the wall, by installing fuel nozzles on the wall of the combustion chamber, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F119/14
Inventor 王亚男孙明波王翼杨揖心汪洪波蔡尊
Owner NAT UNIV OF DEFENSE TECH
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