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Integrated double-component injector, manufacturing method thereof and space equipment

An injector and bicomponent technology, applied in mechanical equipment, machines/engines, jet propulsion devices, etc., can solve the problems of low combustion efficiency of injectors and high manufacturing costs of integrated bicomponent injectors

Pending Publication Date: 2020-10-30
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the low defect of the injector in the prior art that the combustion efficiency is low, thereby providing a kind of integrated two-component injector with high combustion efficiency
[0004] Another technical problem to be solved by the present invention is to overcome the defect of high manufacturing cost of integrated dual-component injectors in the prior art, thereby providing a manufacturing method for integrated dual-component injectors that reduces manufacturing costs
[0005] Another technical problem to be solved by the present invention is to overcome the defect that the injector combustion efficiency of the aerospace equipment is relatively low in the prior art, thereby providing a kind of aerospace equipment with a higher injector combustion efficiency

Method used

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  • Integrated double-component injector, manufacturing method thereof and space equipment
  • Integrated double-component injector, manufacturing method thereof and space equipment
  • Integrated double-component injector, manufacturing method thereof and space equipment

Examples

Experimental program
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Effect test

Embodiment 1

[0054] combine Figure 1-Figure 4 As shown, this embodiment provides an integrated two-component injector, including:

[0055] fuel chamber 50;

[0056] The first bottom surface 10 is arranged at the bottom of the fuel chamber 50;

[0057] The second bottom surface 20 is arranged on the top of the fuel chamber 50 and is opposite to the first bottom surface 10; and

[0058] At least one injection unit is communicated between the first bottom surface 10 and the second bottom surface 20;

[0059] Both the first bottom surface 10 and the second bottom surface 20 are curved surface structures.

[0060] Preferably, the fuel chamber 50 is configured as a closed or partially open cavity structure, the bottom and top of which are surrounded by the first bottom surface 10 and the second bottom surface 20 respectively, between the first bottom surface 10 and the second bottom surface 20. At least one injection unit is arranged between the second bottom surface 20, that is, the inject...

Embodiment 2

[0073] Based on the integrated dual-component injector described in the above embodiment, this embodiment introduces in detail the injection unit arranged inside the integrated dual-component injector.

[0074] Specifically, several injection units with different lengths are arranged between the first bottom surface 10 and the second bottom surface 20.

[0075] Since a plurality of injection units are arranged in the fuel chamber 50, the distribution form of the plurality of injection units in the fuel chamber 50 may be honeycomb distribution, checkerboard distribution, concentric circle distribution, etc. In addition, the structural form of the injection unit includes self-impact type, mutual impact type, coaxial direct current type, coaxial centrifugal type, etc. Preferably, in this embodiment, the injection unit adopts a coaxial straight-line injection unit.

[0076] This embodiment provides an integrated dual-component injector, and the injection units arranged between th...

Embodiment 3

[0093] This embodiment provides a method for manufacturing an integrated dual-component injector. The integrated dual-component injector described in Embodiment 1 and Embodiment 2 above is manufactured by 3D printing.

[0094] The manufacturing method of the integrated dual-component injector provided in this embodiment can reduce the development cost of the integrated dual-component injector and improve the production efficiency of the product by making the integrated dual-component injector through 3D printing , relying on 3D printing technology, the three-bottom two-cavity injector structure and hundreds of injection units are printed together in the form of an integral part, which greatly reduces the number of parts and reduces the product cost of the integrated two-component injector. cost; at the same time, the number of parts of the integrated dual-component injector is integrated from hundreds of pieces into one, which improves the production efficiency of the product, ...

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Abstract

The invention relates to the technical field of space equipment, in particular to an integrated double-component injector, a manufacturing method thereof and the space equipment. The integrated double-component injector comprises a fuel agent cavity, a first bottom face arranged at the bottom of the fuel agent cavity, a second bottom face arranged on the top of the fuel agent cavity and opposite to the first bottom face and at least one injection unit communicating between the first bottom face and the second bottom face. The first bottom face and the second bottom face are of curved structures. According to the integrated double-component injector, the structural strength of the integrated double-component injector can be improved, the fuel agent cavity has the isostatic pressure flow equalizing characteristic, the flow of each injection unit is more uniformly distributed, and the injection combustion efficiency can be improved.

Description

technical field [0001] The invention relates to the technical field of aerospace equipment, in particular to an integrated dual-component injector, a manufacturing method thereof, and aerospace equipment. Background technique [0002] The injector is the core component of the liquid rocket engine. It is located at the head of the thrust chamber. Its function is to inject the propellant evenly into the combustion chamber under the specified propellant flow rate, mixing ratio and injection pressure drop to ensure mixing. The ratio and mass distribution meet the requirements of the design state, and the atomization and mixing process of the propellant are quickly completed, so that the propellant can be burned efficiently and fully in the combustion chamber. The design level and processing accuracy of the injector have a great influence on the stability, efficiency and life of the combustion chamber. Every percentage point lost in the efficiency of combustion through the injec...

Claims

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Application Information

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IPC IPC(8): F02K9/52F02K9/60F02K9/64
CPCF02K9/52F02K9/60F02K9/64
Inventor 彭小波张玺高翔宇鲍启林刘岳曦
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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