A rocket ramjet combination engine with ring ejection structure

A technology of ejection structure and engine, which is applied in the direction of combined engine, ramjet engine, mechanical equipment, etc., can solve the problems of difficulty and limitation of technical realization, and achieve the effect of improving space utilization, reducing weight and reducing size

Active Publication Date: 2016-08-24
清航空天(浙江)科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, as technically achievable or beneficial exploratory attempts, as well as limitations in the difficulty of technical realization, these solutions have certain defects

Method used

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  • A rocket ramjet combination engine with ring ejection structure
  • A rocket ramjet combination engine with ring ejection structure
  • A rocket ramjet combination engine with ring ejection structure

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Embodiment Construction

[0012] The rocket ramjet combined engine with ring ejection structure proposed by the present invention has a structure such as figure 1 As shown, the engine housing 9, the inner housing 13, the rectifier head, the fixed guide column 5 and the fixed ring 6 are included. The engine housing 9 is relatively fixed to the rectifier via a fixed guide column 5, the fixed guide column 5 is provided with an oxidizer inlet 3 and a fuel inlet 4, and the front end of the engine housing is an air inlet 2, such as figure 2 Shown in. The front body 1 of the rectifier head extends out of the front end of the engine housing 9, the rear body 10 of the rectifier head is stepped, and the stepped rectifier rear body 10 is inserted into the engine housing 9. The rear end of the engine housing 9 is a horn-shaped supersonic nozzle 12. The inner shell 13 is fixed in the middle of the rectifier head by a fixed ring 6. The fixed ring 6 is provided with a fuel-oxidant mixing injection port 7, such as ima...

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PUM

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Abstract

The invention relates to a rocket stamping combination engine with an annular injection structure, and belongs to the technical field of space equipment. An outer shell of the engine and a rectification head are oppositely fixed through a fixing guide column, an oxidizing agent inlet and a fuel inlet are formed in the fixing guide column, and an air inlet is formed in the front end of the outer shell. The front body of the rectification head stretches out of the front end of the outer shell of the engine, the rear body of the rectification head is in a step shape and is inserted into the outer shell, and a trumpet-shaped supersonic velocity nozzle is formed in the rear end of the outer shell. An inner shell is fixed in the middle of the rectification head through a fixing ring, a fuel and oxidizing agent mixing jet opening is formed in the inner shell, an annular combustion chamber is formed between the inner shell and the rectification head, and a mixed combustion chamber is formed between the outer shell and the rectification head. According to the rocket stamping combination engine, the size of the engine combustion chambers is reduced, the weight of the combination engine is reduced, and the economical performance of a power system is improved. Fuel gas is evenly sprayed out in the circumferential direction through the annular combustion chamber, the spayed fuel gas can be mixed with the air twice, and combustion efficiency is improved.

Description

Technical field [0001] The invention relates to a rocket ramjet combined engine with a ring ejection structure, belonging to the technical field of aerospace equipment. Background technique [0002] One of the key technologies of the rocket ramjet combined engine is to use an effective ejector rocket structure to better ensure that the engine can achieve full mixing of fuel and air as soon as possible when the engine is started at a low speed, and achieve combustion in the shortest possible combustion chamber space. , So that the combined engine can generate enough thrust at low speed, so as to ensure the takeoff power of the combined engine at low speed. This is of great significance for realizing the structural integration of the combined engine and reducing the structural weight. In recent years, adjacent space, as the airspace between satellites and aircraft, has been increasingly valued by related countries. Mainly because the atmosphere in this space is extremely thin, an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/18
Inventor 谢峤峰王兵
Owner 清航空天(浙江)科技有限公司
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