Silicon-base ceramic core and preparation thereof

Abstract

A silicon-based ceramic core is characterized in that the core is prepared from following materials at mass percentages as 30-50% porous quartz glass powder, 10-15% mullite mineralizer, 18-22% plasticizer, and quartz glass powder at left amount, wherein the porosity of the porous quartz glass powder is 10-20%, which granularity is 150-180, the granularity of the mullite mineralizer is lower than 320, the granularity of the quartz glass powder is 180-240, the plasticizer is the mixture of 10-15% wax, 3-5% polythene, and mineral wax at left amount. The preparation comprises that uniformly mixes materials, to be pressed and shaped on a core press via moulds, to be baked, while the bake temperature is 200+-10DEG C for 4-8h, 400+-10DEG C for 4-8h, 600+-10DEG C for 1h, 900+-10DEG C for 1h, and 1200+-10DEG C for 6-10h, to be strengthened at high and low temperatures. The invention can produce ceramic core with demanded requirements, to support the production of R0110 heavy combustion engine II-stage guider blade.

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...

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 spe...

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