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Ultrasonic nonuniform flow nozzle and design method thereof

A non-uniform flow and design method technology, applied in the direction of injection devices, injection devices, etc., can solve the problems of no non-uniform flow nozzle design technology, no non-uniform flow nozzle, etc., to ensure the quality of the flow field and improve the supersonic non-uniform uniform effect

Active Publication Date: 2011-10-19
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0011] Since the non-uniform flow nozzle has no urgent demand in the past experimental research and engineering applications, there was no design technology directly for the non-uniform flow nozzle in the past

Method used

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  • Ultrasonic nonuniform flow nozzle and design method thereof
  • Ultrasonic nonuniform flow nozzle and design method thereof
  • Ultrasonic nonuniform flow nozzle and design method thereof

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Embodiment Construction

[0052] Hereinafter, the present invention will be described in detail with reference to the drawings and examples. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0053] In the present invention, the subsonic section refers to the part where the flow velocity of the airflow is less than the speed of sound after entering the constriction section of the nozzle, and the subsonic section is also the transonic section, which refers to the junction between the airflow entering the supersonic state from the subsonic state, Generally, the Mach number in the subsonic section is less than 0.8, the Mach number in the subsonic section is between 0.8 and 1.2, and the Mach number in the supersonic section is greater than 1.2.

[0054] Such as figure 1 As shown, according to the supersonic non-uniform flow nozzle design method of the present invention, first determine the n...

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Abstract

The invention provides an ultrasonic nonuniform flow nozzle and a design method thereof. The design method for the ultrasonic nonuniform flow nozzle comprises the following steps of: determining a subsonic speed section curve according to the diameter of an inlet of a subsonic speed section; determining a left characteristic line boundary and a right characteristic line boundary of an outlet dependence domain according to Mach number distribution of an outlet and a method of characteristics; determining an initial characteristic line from a throat; determining an equi-flow line of the nonuniform flow nozzle; and determining upper and lower wall curves by using the initial characteristic line and the equi-flow line according to conservation of mass and the method of characteristics. By thedesign method for the ultrasonic nonuniform flow nozzle, the ultrasonic nonuniform flow nozzle can be designed, so that the ultrasonic nonuniform flow nozzle generates the required nonuniform flow, and can continuously eliminate waves, eliminate or reduce centralized compression or expansion waves and ensure the quality of a flow field. According to the ultrasonic nonuniform flow nozzle, the design method for the ultrasonic nonuniform flow nozzle is used.

Description

technical field [0001] The invention relates to the field of fluid dynamics, in particular to a supersonic non-uniform flow nozzle and a design method thereof. Background technique [0002] Supersonic / hypersonic 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 wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B05B1/34
Inventor 王振国赵玉新刘卫东梁剑寒
Owner NAT UNIV OF DEFENSE TECH
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