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Hafnium diboride-tantalum disilicide composite coating and preparation method thereof

A technology of tantalum disilicide and hafnium diboride, which is applied in the direction of coating, metal material coating process, fusion spraying, etc., can solve coating pores, poor high temperature oxidation resistance, and difficulty in meeting the requirements of aircraft hot-end parts and other problems, achieve the effect of low porosity and improve high temperature protection ability

Pending Publication Date: 2022-02-01
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the single-component silicide and boride ceramics also have the problems of low oxide melting point and violent volatilization of the oxide phase, which leads to defects such as pores in the coating and thus fails.
, so the high-temperature oxidation resistance of the single component is not good, and it is difficult to meet the requirements of the hot-end parts of the aircraft

Method used

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  • Hafnium diboride-tantalum disilicide composite coating and preparation method thereof
  • Hafnium diboride-tantalum disilicide composite coating and preparation method thereof
  • Hafnium diboride-tantalum disilicide composite coating and preparation method thereof

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preparation example Construction

[0028] The invention provides a method for preparing a hafnium diboride-tantalum disilicide composite coating, comprising the following steps:

[0029] Preheating the substrate, spraying hafnium diboride-tantalum disilicide composite powder with atmospheric plasma onto the surface of the preheated substrate to obtain a hafnium diboride-tantalum disilicide composite coating;

[0030] The hafnium diboride-tantalum disilicide composite powder is in a molten eutectic state, and its components include hafnium diboride and tantalum disilicide, and the mass ratio of the hafnium diboride to tantalum disilicide is 2-11:1.

[0031] In the present invention, the substrate is preheated first. In the present invention, the matrix is ​​preferably a matrix that requires high-temperature anti-oxidation protection on the surface; further, the matrix is ​​preferably a carbon fiber reinforced carbon matrix composite (C / C) or superalloy.

[0032] Before the preheating, the present invention pref...

Embodiment 1

[0078] (1) Add 739.9g of hafnium diboride, 260.1g of tantalum disilicide, 5g of PVA and 1500g of deionized water into the ball mill tank with a ball-to-material ratio of 4:1, and ball mill for 3 hours at 250r / min to mix the ingredients evenly , to obtain a suspension of precursor powder;

[0079] (2) Transfer the suspension obtained in step (1) to a spray drying granulation tower for agglomeration and granulation. The granulated powder is first dried in an oven at 80°C for 30 hours, and then passed through a test sieve to obtain granules. HfB with diameter 2 -TaSi 2 Agglomerated powder (HfB 2 with TaSi 2 The volume ratio is 7:3);

[0080] Among them, the spray drying granulation parameters are: inlet temperature 250°C, outlet temperature 130°C, nozzle speed 35Hz, peristaltic pump speed 30rpm;

[0081] (3) HfB 2 -TaSi 2 The agglomerated powder is sent to the induction plasma spheroidization equipment for spheroidization treatment and the spheroidized powder is collected. ...

Embodiment 2

[0092] (1) Add 830.2g of hafnium diboride, 169.8g of tantalum disilicide, 5g of PVA and 1500g of deionized water into the ball mill tank with a ball-to-material ratio of 4:1, and ball mill for 2 hours at 400r / min to mix the ingredients evenly , to obtain a suspension of precursor powder;

[0093] (2) Transfer the suspension obtained in step (1) to a spray drying granulation tower for agglomeration and granulation. The granulated powder is first dried in an oven at 150°C for 20 hours, and then passed through a test sieve to obtain granules. HfB with diameter 2 -TaSi 2 Agglomerated powder (HfB 2 with TaSi 2 The volume ratio is 8:2);

[0094] Among them, the spray drying granulation parameters are: inlet temperature 250°C, outlet temperature 130°C, nozzle speed 35Hz, peristaltic pump speed 35rpm;

[0095] (3) HfB 2 -TaSi 2 The agglomerated powder is sent to the induction plasma spheroidization equipment for spheroidization treatment and the spheroidized powder is collected....

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Abstract

The invention provides a hafnium diboride-tantalum disilicide composite coating and a preparation method thereof, belonging to the technical field of composite coatings. According to the invention, hafnium diboride-tantalum disilicide composite powder is used as a coating raw material, and tantalum disilicide serves as a modification component of hafnium diboride; on one hand, an oxidation product SiO2 of tantalum disilicide can serve as a good high-temperature sealing and filling phase, and hole defects of the hafnium diboride coating are sealed and filled; and on the other hand, another oxidation product Ta2O5 of tantalum disilicide can undergo a solid solution reaction with HfO2 to form HfTaOx, so the crystal transformation of HfO2 is inhibited to a certain extent, and the high-temperature thermal stability of the coating is improved. The obtained coating is an ultra-high-temperature ceramic coating and has good oxidation resistance at a temperature of 1800 DEG C. The coating is prepared in an atmospheric plasma spraying mode, hafnium diboride-tantalum disilicide powder is high in deposition efficiency, and the hafnium diboride-tantalum disilicide powder can be fully molten and does not decompose in a spraying process.

Description

technical field [0001] The invention relates to the technical field of composite coating materials, in particular to a hafnium diboride-tantalum disilicide composite coating and a preparation method thereof. Background technique [0002] Carbon fiber reinforced carbon matrix composites (C / C) have the characteristics of low density, low thermal expansion coefficient at high temperature and excellent mechanical properties, and are regarded as one of the most promising materials for application in aircraft hot-end parts. However, in an aerobic environment above 400 °C, carbon fiber reinforced carbon matrix composites are easily oxidized, resulting in reduced performance. One of the effective methods is to prepare an anti-oxidation ablation coating on its surface. [0003] At present, the existing anti-oxidation and ablation coating materials mainly include carbide ceramics such as ZrC, TaC, HfC, NbC, etc., silicide ceramics MoSi 2 、TaSi 2 , ZrSi 2 、HfSi 2 etc., boride cera...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/10
CPCC23C4/134C23C4/10
Inventor 柳彦博谢明劭刘少璞王一帆
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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