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Method for producing silicon-based ceramic core for aircraft engine blade

An aero-engine and ceramic core technology, applied in the field of ceramic cores, can solve problems such as difficult shapes

Inactive Publication Date: 2011-06-01
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Moreover, the core removal of ceramic cores with complex shapes and small channels is still a difficult problem at home and abroad.

Method used

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  • Method for producing silicon-based ceramic core for aircraft engine blade
  • Method for producing silicon-based ceramic core for aircraft engine blade
  • Method for producing silicon-based ceramic core for aircraft engine blade

Examples

Experimental program
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Effect test

preparation example Construction

[0047] The present invention is a kind of preparation method that is applicable to the silicon-based ceramic core that aeroengine blade is used, and it comprises following steps:

[0048] Step 1. Mixing of powder

[0049] Put the fine powder, medium powder and coarse powder of high-purity (mass percentage purity: 99.99%) silicon dioxide by weighing into a polytetrafluoroethylene ball mill tank, and dry-mill for 30 minutes to 60 minutes to obtain a mixed powder;

[0050] Then put the mixed powder into an oven with a temperature of 80°C to 100°C and a drying time of 10min to 30min to obtain a dry mixed powder;

[0051] Dosage: 8-15g of fine powder, 15-30g of medium powder and the rest of coarse powder in 100g of mixed powder;

[0052] The average particle size of the fine powder is 1-5 μm;

[0053] The average particle size of medium powder is 10-25μm;

[0054] The average particle size of the coarse powder is 40-80 μm;

[0055] In the present invention, the mixed powder aft...

Embodiment 1

[0079] Step 1. Mixing of powder

[0080] Put the fine powder, medium powder and coarse powder of high-purity (mass percentage purity: 99.99%) silicon dioxide into a polytetrafluoroethylene ball mill tank, and dry mill for 40 minutes to obtain a mixed powder;

[0081] Then put the mixed powder into an oven with a temperature of 80°C and a drying time of 30 minutes to obtain a dry mixed powder;

[0082] Dosage: 12.5g of fine powder, 25g of medium powder and the rest of coarse powder in 100g of mixed powder;

[0083] The average particle size of the fine powder is 2.7 μm;

[0084] The average particle size of medium powder is 12.44μm;

[0085] The average particle size of coarse powder is 43.09μm;

[0086] In the present invention, the appearance of high-purity (mass percentage purity is 99.99%) silica mixed powder is as follows figure 1 As shown, the particles in the figure have a relatively regular spherical structure, which is conducive to improving the fluidity of the sil...

Embodiment 2

[0108] Step 1. Mixing of powder

[0109] Put the fine powder, medium powder and coarse powder of high-purity (mass percentage purity: 99.99%) silicon dioxide into a polytetrafluoroethylene ball mill tank, and dry mill for 30 minutes to obtain a mixed powder;

[0110] Then put the mixed powder into an oven with a temperature of 90°C and a drying time of 15 minutes to obtain a dry mixed powder;

[0111] Dosage: 10g of fine powder, 20g of medium powder and the rest of coarse powder in 100g of mixed powder;

[0112] The average particle size of the fine powder is 4.5 μm;

[0113] The average particle size of medium powder is 20.2μm;

[0114] The average particle size of the coarse powder is 59.8 μm;

[0115] Step 2. Preparation of slurry

[0116] The plasticizer is put into an oil bath temperature and melted in a stirrer with a temperature of 90° C. to obtain the first intermediate; the plasticizer is a mixture of paraffin wax and beeswax, and the mass ratio of paraffin wax to...

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Abstract

The invention discloses a method for producing a silicon-based ceramic core for an aircraft engine blade. The method comprises the steps of: producing the complex ceramic core through hot injection molding by utilizing three high-purity silica powders with different particle sizes as raw materials, the high-purity silica powder in large particle size as a framework, the high-purity silica powder in small particle size as sintering additives, paraffin and beewax as plasticizers, and oleic acid as a surface active agent, carrying out low-temperature dewaxing and high-temperature roasting to themolded bisque ceramic core in a padding alumina to finally obtain the silicon-based ceramic core for the aircraft engine blade.

Description

technical field [0001] The invention relates to a ceramic core, more particularly, to a method for preparing a high-purity silica ceramic core suitable for aeroengine blades. Background technique [0002] As we all know, the thrust-to-weight ratio is an important index to measure the performance of an aero-engine, and the gas turbine is the heart of an aero-engine. To increase the thrust-to-weight ratio of an aero-engine, the gas temperature of the turbine must first be increased. Since the 1950s, the thrust-to-weight ratio of aero-engines produced in advanced countries has increased by an average of 16% per year, and the temperature in front of the turbine has increased at a rate of 20°C to 25°C per year. There are two main ways to increase the temperature before the turbine: improving the temperature bearing capacity of the material and the cooling technology of the hollow blade. At present, the temperature in front of the advanced engine turbine has to reach 1757°C. Due...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/14C04B35/622
Inventor 张跃代晶谷景华唐保军
Owner BEIHANG UNIV
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