Direct-current cold-wall type engine combustor

A combustion chamber and engine technology, which is applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of reducing cooling effect and engine performance loss, and achieve improved atomization effect, long jet impact distance, and improved thermal protection effect of ability

Active Publication Date: 2018-08-28
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For liquid film cooling, on the one hand, film boiling easily occurs under the high-temperature wall surface, which significantly reduces the cooling effect; on the other hand, it is difficult to effectively participate in the combustion reaction in the limited space of the liquid film, resulting in loss of engine performance

Method used

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  • Direct-current cold-wall type engine combustor
  • Direct-current cold-wall type engine combustor
  • Direct-current cold-wall type engine combustor

Examples

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Embodiment Construction

[0020] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention. In describing the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", The orientation or positional relationship indicated by "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the referred device Or elements must have...

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Abstract

The invention discloses a direct-current cold-wall type engine combustor. The direct-current cold-wall type engine combustor comprises a combustor upper cover, a combustor linear section, a jet section and a spray pipe convergence and expansion section which are connected in sequence. An oxidizing agent liquid collection cavity, an oxidizing agent jet hole, a fuel liquid collection cavity and a fuel jet hole are formed in the outer wall of the jet section in the circumferential direction. An oxidizing agent enters the oxidizing agent liquid collection cavity via an oxidizing agent regenerativecooling channel and then flows out from the oxidizing agent jet hole to form a jet flow, fuel enters the fuel liquid collection cavity via a fuel regenerative cooling channel and then flows out fromthe fuel jet hole to form a jet flow, the jet flows are close to the inner wall of the combustor linear section but being not in contact with the wall, and the jet flows impact for atomization, mixingand combustion on the combustor upper cover, and are discharged out of the combustor through the spray pipe convergence and expansion section. By means of the combustor, the propellant combustion efficiency and the thermal protection capacity of the combustor can be improved, and the combustor is simple in overall structure and easy to machine and obtain.

Description

technical field [0001] The invention relates to the technical field of rocket engines, in particular to a combustion chamber of a DC cold-wall engine. Background technique [0002] The improvement of the specific impulse performance of the rocket engine can reduce the propellant consumption during operation, thereby increasing the payload of the aircraft or prolonging the life of the aircraft. Improving the propellant combustion efficiency is an important way to improve the specific impulse performance of the engine. For liquid rocket engines, improving combustion efficiency will increase the thermal load of the combustion chamber, but too high a thermal load will make the combustion chamber material unbearable. Therefore, to improve the performance of liquid rocket engines, two problems need to be solved. One is to improve the propellant atomization and mixing effect to improve combustion efficiency, and the other is to optimize the thermal protection design of the combust...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/62F02K9/44F02K9/52
CPCF02K9/44F02K9/52F02K9/62
Inventor 杨成虎刘昌国张志远林庆国刘犇姚锋赵婷吴凌峰
Owner SHANGHAI INST OF SPACE PROPULSION
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