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Method for preparing iridium-silicide composite coating for engine thrust chamber body

A thrust chamber and engine technology, applied in coating, metal material coating process, vacuum evaporation plating, etc., can solve the problem that there is no report on the overall preparation plan of the engine thrust chamber, the structure and preparation method are not disclosed to the public, and the price is high. Problems, to achieve the effect of wide application range, high temperature resistance, and prolong life

Active Publication Date: 2015-12-02
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the rhenium / iridium engine, it is currently only used in the United States, but the specific structure and preparation method have not been disclosed to the public, especially the overall preparation of the thrust chamber of the engine has not been reported
In addition, for rhenium / iridium engines, due to the high price of rhenium and iridium, the overall engine material rhenium / iridium material cost will be very high

Method used

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  • Method for preparing iridium-silicide composite coating for engine thrust chamber body
  • Method for preparing iridium-silicide composite coating for engine thrust chamber body
  • Method for preparing iridium-silicide composite coating for engine thrust chamber body

Examples

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Effect test

Embodiment 1

[0044] to manufacture a size of Body ( is the minimum diameter of the body, is the maximum diameter of the body, and 500mm is the total length of the body) as an example to illustrate the specific implementation of the method of the present invention.

[0045] (a) Combustion chamber and extension assembly preparation

[0046]According to the requirements of the drawing of the body, reserve the allowance for the assembly and welding, and process the combustion chamber separately (Such as figure 1 ), spinning processing extension (Such as figure 2 );

[0047] (b) Preparation of iridium coating in combustion chamber

[0048] It uses the following steps to prepare a molybdenum layer on the surface of the combustion chamber:

[0049] 1) Process the pure iridium (99.9at.%) cathode target according to the size of the drawing, and install it on the vacuum cathodic arc deposition equipment after degreasing, as the cathode;

[0050] 2) The rhenium combustion chamber is de...

Embodiment 2

[0071] to manufacture a size of Body ( is the minimum diameter of the body, is the maximum diameter of the body, and 500mm is the total length of the body) as an example to illustrate the specific implementation of the method of the present invention.

[0072] (a) Combustion chamber and extension assembly preparation

[0073] According to the requirements of the drawing of the body, reserve the allowance for the assembly and welding, and process the combustion chamber separately (Such as figure 1 ), spinning processing extension (Such as figure 2 );

[0074] (b) Preparation of iridium coating in combustion chamber

[0075] It uses the following steps to prepare a molybdenum layer on the surface of the combustion chamber:

[0076] 1) Process the pure iridium (99.9at.%) cathode target according to the size of the drawing, and install it on the vacuum cathodic arc deposition equipment after degreasing, as the cathode;

[0077] 2) The rhenium combustion chamber is d...

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Abstract

The invention relates to a method for preparing iridium-silicide composite coating for an engine thrust chamber body. According to the invention, based on the characteristic that the working temperature from a combustion chamber to an extended section decreases in a gradient manner, by utilizing the characteristic that the oxidation resistance of rhenium / iridium coating is better than that of niobium alloy / silicide coating, by adopting two coating preparation technologies of vacuum arc ion plating and slurry sintering respectively, and through the optimization of the technology for preparing aluminide coating in a welded seam position through plasma spraying, the prepared coating has the advantages of raising the working temperature of the engine combustion chamber, prolonging the service life of an engine and improving the working efficiency and can meet the working condition requirements of the engine; in addition, the method is flexible and diversified, a plurality of preparation methods can be adopted to meet different preparation demands, and the application range is wide.

Description

technical field [0001] The invention relates to a high-temperature anti-oxidation coating, in particular to a method for preparing an iridium coating for the engine thrust chamber body for the combustion chamber, a silicide coating for the extension section, and an aluminide coating for the welding seam position, It can be applied to the two-component liquid rocket rail / attitude control engine. Background technique [0002] Bipropellant liquid propellant attitude control engine is an important part of modern spacecraft and strategic and tactical weapons. It is widely used in satellite orbit control, attitude adjustment, precise positioning, and spacecraft docking, rendezvous and landing. The engine thrust chamber material and its surface high temperature anti-oxidation coating performance determine the working temperature and service life of the thrust chamber. The coating preparation process and coating system of the existing engine thrust chamber in my country cannot meet...

Claims

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Application Information

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IPC IPC(8): C23C14/28C23C14/16C23C4/12C23C4/08C23C24/08
Inventor 李海庆张绪虎徐方涛陈道勇贾文军何开民贾中华张春基胡国林
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH