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Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine

A technology of a rocket engine and a simulation device, which is applied in the direction of chemical analysis using combustion, and achieves the effect of simple structure and convenient use.

Inactive Publication Date: 2015-08-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, domestic literature rarely mentions the experimental technology of thermal insulation layer ablation under the condition of alumina particle deposition.

Method used

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  • Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine
  • Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine

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Experimental program
Comparison scheme
Effect test

Embodiment

[0030] In the experiment, the experimental device of the present invention is according to figure 1 As shown, it is assembled, wherein the front head ejector rod 1, the gas generator 2, the converging section 5, the transition section 7, the deposition section 8, the cover plate 13 and the nozzle 10 are all 45# steel. The selection of the propellant 3, the diameter of the adjusting ring 6, the insulation layer test piece 11, and the throat diameter of the nozzle 10 are all determined by the experimental conditions.

[0031] The front head rod 1 is a two-stage structure with adjustable length, and is connected with the gas generator 2 by M16*1.5 thread; the gas generator 2 is a hollow cylinder with a length of 195mm, an outer diameter of 220mm, and an inner diameter of 200mm , its surface is welded with an ignition head seat and a pressure sensor seat, which is used to connect the ignition powder pack 4 arranged in the gas generator 2; there are 20 equally spaced holes on the f...

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PUM

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Abstract

The invention discloses a simulation device of thermal insulation layer ablation under the condition of particle phase deposition in a rocket engine, wherein the simulation device includes a fuel gas generator for combusting a solid propellant, a convergence section, a transition section, a deposition section and a spray tube are successively and coaxially connected to one end of the fuel gas generator to form a penetrated chamber body. The other end of the fuel gas generator is sealed. The solid propellant and an ignition powder bag are arranged inside the fuel gas generator. The simulation device is simple in structure and is convenient to install and use. By means of changing the diameter of an adjustment ring and deposition depth of a deposition trough, the concentration of a particle phase can be adjusted and further the thermal insulation layer ablation under the condition of the particle phase deposition at a back wall concave chamber of a submerged nozzle in a large-scale solid rocket engine can be simulated.

Description

technical field [0001] The invention belongs to the technical field of rocket engines, and relates to a simulation device for ablation of a thermal insulation layer under particle phase deposition conditions in a rocket engine. Background technique [0002] In the design of modern solid rocket motors, in order to increase the specific impulse and shorten the overall length of the motor, metal powders (such as Al, Mg) are usually added to the propellant, and submerged nozzles are widely used. However, during the working process of the engine, a cavity is gradually formed in the area of ​​the back wall of the submerged nozzle as the combustion surface progresses, and there is a complex recirculation zone in this cavity. Due to the large inertia of the particle phase, it is not easy to follow the streamline , so the back wall area of ​​the nozzle with large airflow deflection is easy to separate from the airflow and enter the recirculation area, and then deposits in the cavity ...

Claims

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Application Information

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IPC IPC(8): G01N31/12
Inventor 刘洋关轶文何国强李江刘佩进陈剑
Owner NORTHWESTERN POLYTECHNICAL UNIV