Casting method for heavy combustion engine II-stage diverter blade

A casting method and guide technology, applied in the direction of mold, core, mold composition, etc., can solve the problems of low void ratio, affecting the core removal speed, large deformation, etc., to improve wet strength and high temperature strength, reduce Possibility of cracking, effect of solving cracks and deformation

Inactive Publication Date: 2008-04-30
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional silicon-based core will produce about 0.4-1.2% firing shrinkage during the firing process, which will generate a large internal stress during the firing process, causing the core to break. If the filling is not compacted before firing If the crack is reduced, it will cause a large amount of deformation, which will cause a pair of contradictions between the crack and the deformation, take care of one and lose the other, or both exist at the same time
Due to the particularity of the ceramic core used for the second-stage guide vane of the R0110 heavy-duty gas turbine, the traditional process cannot meet the production of this core at all.
Secondly, the ceramic core produced by the traditional process still faces the problem of removing the ceramic core from the blade after the blade is poured.
Due to the structural characteristics of the blade, the air-cooling channels in the inner cavity are intricate, and the removal opening of the ceramic core is narrow, which determines that it is extremely difficult to remove the ceramic core from the blade. If the blade is soaked in the corrosive solution For a long time, it will cause corrosion to the metal material of the blade, which will seriously affect the normal use of the blade and must be scrapped
The porosity of the silicon-based ceramic core manufactured by the traditional process is low, generally 23-30%, so it is not conducive to the penetration of the corrosive liquid into the ceramic core, so it affects the core removal speed

Method used

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  • Casting method for heavy combustion engine II-stage diverter blade
  • Casting method for heavy combustion engine II-stage diverter blade
  • Casting method for heavy combustion engine II-stage diverter blade

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0044] Example 1

[0045] The porous silica glass powder has a porosity of 10-20%, and should not be too fine. The dosage is 30% between 150 mesh and 180 mesh. At the same time, a mullite mineralizer with a particle size of less than 320 mesh is added, and the amount is 10%. The use amount of plasticizer (10% beeswax, 3% polyethylene, and the rest is a mixture of paraffin wax) is 18%. The particle size of the traditional quartz glass powder is between 180 mesh and 240 mesh.

[0046] Mix the above-mentioned raw materials thoroughly, and press the core machine according to figure 1 After the shown shape is pressed and molded, it is fired, and the wet ceramic core must be fully tapped in the filler before firing. The baking temperature is 200±10℃, 8h+400±10℃, 8h+600±10℃, 1h+900±10℃, 1h+1200±10℃, 10h.

[0047] After being out of the furnace, it is strengthened by ethyl silicate at high temperature and phenolic varnish is strengthened at low temperature. The prepared silicon-based cer...

Example Embodiment

[0048] Example 2

[0049] The porous silica glass powder has a porosity of 10-20%, and should not be too fine. Between 150 mesh and 180 mesh, the dosage is 35%. At the same time, a mullite mineralizer with a particle size of less than 320 mesh is added, and the dosage is 15%. The amount of plasticizer (12% beeswax, 3% polyethylene, and the rest is a mixture of paraffin wax) is 20% of the powder's specific gravity. The particle size of the traditional quartz glass powder is between 180 mesh and 240 mesh.

[0050] Mix the above-mentioned raw materials thoroughly, and press the core machine according to figure 1 After the shown shape is pressed and molded, it is fired, and the wet ceramic core must be fully tapped in the filler before firing. The baking temperature is 200±10℃, 6h+400±10℃, 6h+600±10℃, 1h+900±10℃, 1h+1200±10℃, 8h.

[0051] After being out of the furnace, it is strengthened by ethyl silicate at high temperature and phenolic varnish is strengthened at low temperature. T...

Example Embodiment

[0052] Example 3

[0053] The porous silica glass powder has a porosity of 10-20%, and should not be too fine. The dosage is 40% between 150 mesh and 180 mesh. At the same time, a mullite mineralizer with a particle size of less than 320 mesh is added, and the amount is 10%. The amount of plasticizer (15% beeswax, 4% polyethylene, and the rest is a mixture of paraffin wax) is 22% of the powder proportion. The particle size of the traditional quartz glass powder is between 180 mesh and 240 mesh.

[0054] Mix the above-mentioned raw materials thoroughly, and press the core machine according to figure 1 After the shown shape is pressed and molded, it is fired, and the wet ceramic core must be fully tapped in the filler before firing. The baking temperature is 200±10℃, 8h+400±10℃, 8h+600±10℃, 1h+900±10℃, 1h+1200±10℃, 10h.

[0055] After being out of the furnace, it is strengthened by ethyl silicate at high temperature and phenolic varnish is strengthened at low temperature. The prepa...

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Abstract

A molding method of II level diverter fins of a R0110 heavy combustion engine utilizes roof pouring style molding scheme, which is characterized in that the insulating blanket thickness of the outer portion of the fin shape casing is thickened from top to bottom, from 10+-2mm to 40+-5mm, simultaneously the bottom of the fin shape casing is covered with a layer of iron bolus at a thickness of 20-30mm, a roof pouring style dead system utilizes a huge dead head, the volume of the dead head is 500 to 600cm3, and the height of the dead head is 110-120mm, the molding temperature is controlled at 1405-1480 DEG C and the molding time is 6-8 seconds. Through the design change of a prior guiding fin dead system and the improvement of a prior craft, the invention is capable of producing casts with fine and close organizations.

Description

Technical field: [0001] The present invention relates to the preparation technology of R0110 heavy-duty gas turbine class II guide vane, in particular, it provides the silicon-based ceramic core for casting R0110 heavy-duty gas turbine class II guide vane and its preparation, and the R0110 heavy-duty gas turbine class II casting core The manufacturing method of the deflector blade shell, the pouring method of the R0110 heavy-duty gas turbine II stage deflector blade. Background technique: [0002] R0110 heavy-duty gas turbine II-stage guide vane is a large-scale complex inner cavity structure equiaxed crystal no margin hollow investment casting vane, large in size (2-3 times the size of the previous guide vane, 6-9 times its volume) , the area of ​​the upper and lower edge plates is large, and the inner cavity is a complex structure of interlaced grids (such as figure 1 , 2 ), high dimensional accuracy is required. The structural design of the blade is still the first. In...

Claims

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Application Information

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IPC IPC(8): B22C9/22B22C9/08B22C9/10
Inventor 丛健冯文刚司连友贾东晨
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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