Asymmetric supersonic velocity spray pipe and design method thereof

Abstract

The invention provides an asymmetric supersonic velocity spray pipe and a design method thereof. The design method of the supersonic velocity spray pipe comprises the following steps: according to an inlet coordinate and a throat area, determining a subsonic velocity segment curve; according to the subsonic velocity segment curve and a throat radius of curvature, determining a characteristic line in a transonic velocity area; according to one end point of the characteristic line and a corresponding supersonic velocity area outlet end point, determining a first wall surface curve; and according to an initial characteristic line and the Mach number distribution of the first wall surface curve, determining a second wall surface curve by mass conservation with a characteristic line method. With the design method of the asymmetric supersonic velocity spray pipe, concentrated compression wave in the flow field of the asymmetric supersonic velocity spray pipe can be reduced or eliminated, the quality of the flow field of the spray pipe is greatly improved, equipment performance is improved, and research funds can be saved. According to the asymmetric supersonic velocity spray pipe disclosed by the invention, the design method of the asymmetric supersonic velocity spray pipe is adopted.

Description

technical field [0001] The invention relates to the field of fluid power, in particular to an asymmetric supersonic nozzle and a design method thereof. Background technique [0002] Supersonic nozzles are widely used in high-speed aircraft, rockets, supersonic wind tunnels, high-energy lasers, ejector vacuum pumps and other equipment. The quality of the nozzle flow field has an important impact on the performance of the equipment. Obtaining an appropriate nozzle wall curve through certain design techniques can greatly improve the quality of the nozzle flow field, improve equipment performance, and save research funds. A supersonic nozzle is generally composed of a contraction section and an expansion section. Driven by a certain pressure, the gas gradually accelerates in the contraction section and reaches the speed of sound near the throat, and then continues to accelerate in the expansion section until the required Mach number and Supersonic gas flow with angular distribu...

AI Technical Summary

Problems solved by technology

Without viscosity correction for asymmetric walls, it is difficult to accurately evaluate the flow field structure changes caused by the adsorption surface layer effect

MLN expands too fast and its accuracy is not high, so it is not suitable for designing high Mach number nozzles

[0013] Based on the asymmetrical nozzle design method based on the empirical curve, parameters such as the nozzle exit Mach number and flow direction angle cannot be designed according to the requirements

[0014] The asymmetric nozzle design technology based on CFD optimization algorithm has a very large amount of calculation, low design efficiency, and the accuracy has not been greatly improved.

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