Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector

A test device and multi-nozzle technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as unfavorable nozzle installation and replacement, complicated connection methods, etc., and achieve compact structure, simple and reliable sealing, The effect of convenient welding

Inactive Publication Date: 2011-04-20
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In July 2005, the American Society of Aeronautics and Astronautics published the document number AIAA2005-3572 "Benchmark wall heat flux data for a GO 2 / GH 2 "single element combustor" records the relevant design and test of hydrogen-rich / oxygen-rich gas single nozzle with oxygen-rich pre-combustion chamber and hydrogen-rich pre-combustion chamber, but its connection method is complicated, which is not conducive to the installation and replacement of nozzles, while There are no relevant records on the research on hydrogen-rich / oxygen-rich gas multi-nozzle gas injectors

Method used

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  • Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector
  • Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector
  • Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector

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Embodiment Construction

[0025] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0026] Hydrogen-enriched / oxygen-enriched gas multi-nozzle gas injector test device of the present invention, such as figure 1 As shown, it mainly includes three parts: an oxygen-enriched pre-chamber 1 , a hydrogen-enriched pre-chamber 2 and a main combustion chamber 3 .

[0027] Oxygen-enriched pre-combustion chamber 1 is used to generate oxygen-enriched gas, such as figure 2 As shown, the main components are: the head 4 of the oxygen-enriched chamber, the body 5 of the oxygen-enriched chamber, the outlet section 6 of the oxygen-enriched chamber and the outlet flange 7 of the oxygen-enriched chamber. The head 4 of the oxygen-enriched chamber is connected with the body 5 of the oxygen-enriched chamber with bolts, and the body 5 of the oxygen-enriched chamber is connected with the outlet section 6 of the oxygen-enriched chamber with bolts, and the joi...

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Abstract

The invention discloses a test unit for a hydrogen-rich / oxygen-rich gas multinozzle gas-gas injector, relating to the design field of hydrogen-rich / oxygen-rich gas multinozzle combustion chambers of liquid propellant rocket engines. The test unit mainly comprises an oxygen-rich prechamber, a hydrogen-rich prechamber and a main combustion chamber. An oxygen-rich chamber outlet flange is connectedto the oxygen-rich chamber outlet section of the oxygen-rich prechamber by a thread structure, an oxygen inlet supported flange is connected to an oxygen-rich gas inlet section of the main combustionchamber, a hydrogen-rich chamber outlet flange is connected to the hydrogen-rich chamber outlet section of the hydrogen-rich prechamber by the thread structure, and a hydrogen inlet coupling flange is connected to the hydrogen-rich gas inlet section of the main combustion chamber. The flanges in an experimental facility are made of A3 carbon steel material, and thus the cost is lowered. In addition, each part of the device is convenient to connect and install, and wall surface temperature is convenient to measure.

Description

technical field [0001] The invention relates to the design field of a hydrogen-rich / oxygen-rich gas multi-nozzle combustor for a liquid rocket engine, in particular to a test device for a hydrogen-rich / oxygen-rich gas multi-nozzle gas injector. Background technique [0002] The injector is one of the key components of the liquid rocket engine, and the performance of the injector directly affects the performance of the engine. The full-flow afterburning cycle system is a new type of rocket engine cycle system. It is the staged combustion technology with the highest combustion performance at present, and it is one of the important development directions of liquid rocket engine technology. In the technical research of full-flow afterburning cycle engine, gas-gas combustion is one of the key technologies. All flow of hydrogen and oxygen is combusted once in the pre-combustion chamber to drive the turbine and then enters the combustion chamber for the second combustion. Therefor...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96
Inventor 蔡国飙李茂高玉闪金平
Owner BEIHANG UNIV
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