Liquid oxygen methane thrust chamber injector

A liquid oxygen methane and thrust chamber technology, which is used in machines/engines, jet propulsion devices, indirect carbon dioxide emission reduction, etc. and other problems, to achieve the effect of energy partition release, compact structure and improved work reliability

Active Publication Date: 2021-09-03
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention proposes a liquid oxygen methane thrust chamber injector, the purpose of which is to solve the problem of using direct current shear nozzles or impact spray nozzles during the working process of the liquid oxygen methane injector because both liquid oxygen and methane belong to liquid low-temperature propellants. The structure of the injector will lead to poor propellant mixing effect and insufficient combustion efficiency of the thrust chamber injector, which is difficult to meet the technical problems of the existing injector design requirements for high efficiency and stable combustion

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  • Liquid oxygen methane thrust chamber injector
  • Liquid oxygen methane thrust chamber injector
  • Liquid oxygen methane thrust chamber injector

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Embodiment Construction

[0041] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.

[0042] Such as figure 1 and figure 2 As shown, the liquid oxygen methane thrust chamber injector in this embodiment includes a plurality of injection units, a midsole 2, and a top cover 1, a deflector 3 and an inner bottom coaxially arranged in sequence on the midsole 2 4;

[0043] A plurality of injection units are fixed on the midsole 2, the deflector 3 and the inner bottom 4;

[0044] A liquid oxygen cavity 31 is formed between the top cover 1, the midsole 2, and a plurality of injection units, and a liquid oxygen inlet pipe 12 is arranged on the liquid oxygen chamber 31, and a collector is also arranged on the liquid oxygen inlet pipe 12. The liquid container 11; the midsole 2 is provided with a flow eq...

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Abstract

The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector, and aims to solve the problems that in the working process of an existing liquid oxygen methane injector, both liquid oxygen and methane belong to liquid low-temperature propellants, a direct-current shear type nozzle or an impact type injector structure is adopted and consequently the propellant mixing effect of the thrust chamber injector is poor, and the combustion efficiency is insufficient. The liquid oxygen methane thrust chamber injector comprises a plurality of injection units, a middle bottom, a top cover, a fluid director and an inner bottom, wherein the top cover, the fluid director and the inner bottom are coaxially and sequentially arranged on the middle bottom. The multiple injection units are fixed to the middle bottom, the fluid director and the inner bottom; a liquid oxygen cavity is formed among the top cover, the middle bottom and the multiple injection units, and a methane cavity is formed among the middle bottom, the inner bottom and the multiple injection units; and the multiple injection units are provided with nozzles with retraction chambers, and the nozzles comprise a central area nozzle, a main combustion area nozzle and an edge area nozzle.

Description

technical field [0001] The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector. Background technique [0002] Oxygen and methane are natural resources with abundant reserves in nature, and methane is a widely used hydrocarbon fuel with low price, abundant reserves and no pollution. As a liquid rocket engine propellant combination, the specific impulse of the combination of liquid oxygen and methane is between that of liquid oxygen kerosene and liquid oxygen liquid hydrogen. Compared with kerosene, liquid methane has better cooling performance, its coking temperature is higher than that of kerosene, and its combustion products have less carbon deposition, so methane has greater advantages as a coolant. Compared with liquid oxygen and liquid hydrogen, methane is a low-temperature propellant, but its low price and high density can effectively reduce the launch cost of rockets. Therefore, the combination of liquid oxy...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52
CPCF02K9/52Y02E20/34
Inventor 银晋瑞吴海波亓占峰卢钢夏开红郭灿琳
Owner XIAN AEROSPACE PROPULSION INST
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