Composite material winding regeneration cooling thrust chamber and processing technology

A composite material and regenerative cooling technology, which is applied in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of increased thrust chamber wall thickness, increased cooling channel height, and reduced cooling effect of regenerative cooling channels, achieving improved Cooling effect, small wall thickness, low height effect

Pending Publication Date: 2022-06-21
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to the limitation of brazing technical conditions, there are defects such as increased thickness of the thrust chamber and increased height of the cooling channel when the regenerative cooling channel is processed by the brazing process, which leads to a decrease in the cooling effect of the regenerative cooling channel

Method used

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  • Composite material winding regeneration cooling thrust chamber and processing technology
  • Composite material winding regeneration cooling thrust chamber and processing technology
  • Composite material winding regeneration cooling thrust chamber and processing technology

Examples

Experimental program
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Embodiment 1

[0059] see figure 1 , This embodiment provides a composite material winding regeneration cooling thrust chamber (hereinafter referred to as "thrust chamber"), which is applied to a liquid rocket engine, which includes a thrust chamber body 100 and a composite material layer 200 .

[0060] The composite material layer 200 is sleeved on the side wall of the thrust chamber body 100 to form a sandwich structure, and a cooling channel exists between the composite material layer 200 and the thrust chamber body 100 . The purpose of cooling the thrust chamber body 100 can be achieved by using the propellant as a coolant, making it flow through the cooling channel, and removing the heat on the side wall of the thrust chamber body 100 through the convection heat exchange heat. After the propellant flows out of the cooling channel, it is injected into the combustion chamber inside the thrust chamber body 100 through the injection panel, and the heat absorbed by the propellant is then ret...

Embodiment 2

[0081] see Figure 4 , this embodiment provides a machining process for machining a cooling channel on the thrust chamber body 100, which includes the following steps:

[0082] S1, machining a cooling groove on the outer side wall of the thrust chamber body 100, the specific steps are as follows:

[0083] S1-1, design the thrust chamber body 100 profile and cooling groove.

[0084] S1-2, a cooling groove is milled on the outer side wall of the thrust chamber body 100, and a rib plate 130 is formed at the same time.

[0085] S2, install the measuring nozzle 300.

[0086] Specifically, all the measuring nozzles 300 arranged in the combustion chamber section 110 are connected to the combustion chamber section 110 by welding or sealing threads, and it is confirmed that there is no leakage between the combustion chamber and the cooling groove, so as to ensure the safety of the thrust chamber. sex.

[0087] S3, winding composite fibers on the thrust chamber body 100 to form a co...

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Abstract

The invention provides a composite material winding regenerative cooling thrust chamber and a machining process, and relates to the field of liquid rocket engines. The composite material winding regeneration cooling thrust chamber comprises a thrust chamber body and a composite material layer. A cooling groove is formed in the outer side wall of the thrust chamber body; the composite material layer is arranged on the thrust chamber body in a sleeving mode, the composite material layer wraps the cooling groove to form a cooling channel, and the composite material layer is formed by winding composite fibers on the thrust chamber body. The outer side wall of the thrust chamber body provided with the cooling groove is equivalent to an inner shell of a sandwich structure, and the composite material layer arranged on the thrust chamber body in a sleeving mode is equivalent to an outer shell of the sandwich structure. Due to the fact that the composite material layer is formed by winding the composite fibers on the thrust chamber body, a brazing process is not adopted in the machining process, the wall thickness of the thrust chamber body and the height of the cooling channel are not limited by brazing technical conditions, the wall thickness of the thrust chamber body can be smaller, the height of the cooling channel can be lower, and therefore the cooling effect of the cooling channel is improved.

Description

technical field [0001] The invention relates to the field of liquid rocket engines, in particular to a composite material winding regeneration cooling thrust chamber and a processing technology. Background technique [0002] Regenerative cooling refers to designing the side wall of the thrust chamber body as a sandwich structure, forming an inner shell, an outer shell and a regenerative cooling channel between the inner shell and the outer shell, and making the propellant flow through the regenerative cooling channel, so as to cool the inner shell. The thermal protection method of convective cooling is widely used in medium-thrust and high-thrust liquid rocket engines. [0003] The structure of the regenerative cooling channel is extremely complex, the processing is very difficult, and the rocket engine has high requirements on reliability. Therefore, when machining regenerative cooling channels, a very high machining quality must be guaranteed. [0004] At present, it is ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/64F02K9/34F02K9/97B29C53/58B23P15/00
CPCF02K9/64F02K9/34F02K9/97B29C53/582B23P15/00
Inventor 蔡国飙俞南嘉师浩然周闯焦博威
Owner BEIHANG UNIV
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