A fuel supercritical combustion test equipment

Abstract

The invention discloses fuel supercritical combustion test equipment, which comprises a hydraulic propulsion device, a nylon plug, a heavy piston installation section, a heavy piston, a compression tube, a compression tube support device, a compression tube thrust device, a heavy piston backstop device, an experimental cabin, experimental cabin support device, rails and high pressure source, among which the nylon plug and heavy piston are respectively arranged on the left side of the heavy piston installation section and in the middle pipe, the lower side of the heavy piston installation section communicates with the lower high pressure source through a ball valve, and the right side of the heavy piston installation section The side is connected to the compression tube, the compression tube is supported by the compression tube support device, the compression tube thrust device is installed at one-third of the compression tube, and is positioned by the thrust ring, and the heavy piston backstop device is connected with the experimental cabin. The invention improves the anti-retraction efficiency of the heavy piston and the safety during the anti-retraction process, reduces the high stress and strain at the moment of contact between the heavy piston and the anti-retraction block, prolongs the service life of the heavy piston and the anti-retraction block, and improves the safety during the test process. The temperature and pressure stability of the test chamber.

Description

technical field [0001] The invention relates to the technical field of test equipment, in particular to fuel supercritical combustion test equipment. Background technique [0002] Evaporation and combustion are fundamental problems in the working of rocket engines. Combustion characteristics affect the performance of rocket engines. Compared with subcritical conditions, fuel evaporation and combustion rates are greatly improved under supercritical conditions, and liquid fuels exhibit similar characteristics to gaseous fuels. Therefore, there are essential differences between subcritical and supercritical combustion. Generally, there are pressure and temperature conditions in the rocket engine combustion chamber for fuel to undergo supercritical combustion, so supercritical combustion is a typical combustion problem of rocket engines. [0003] Both the shock tube and the heavy piston driver are experimental devices that can generate uniform, high-temperature and high-pressur...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a kind of fuel supercritical combustion test equipment. The structure design of the present invention is ingenious, and it is provided with a heavy piston stop device and an adjustment block for changing the compression ratio, so as to solve the problem of short test time and constant compression ratio of the existing experimental device. It can generate and maintain a high temperature and high pressure environment for a long time, effectively reducing the damage to the experimental equipment caused by the high-speed hard impact of the heavy piston in the equipment, and prolonging the service life of the equipment

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