Casting method for heavy combustion engine II-stage diverter blade

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...

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

[0004] In addition, the blades of the R0110 heavy-duty gas turbine II stage guide have large dimensions and high dimensional accuracy requirements. The upper and lower edge plates have large areas, the blades are heavy, and there are 5mm sealing grooves on the edge plates (see figure 2 )

The above structural features make the casting of the R0110 heavy-duty gas turbine II-level guide vane very difficult, and there are special requirements for its investment casting shell, which requires sufficient high-temperature strength, high high-temperature deflection and good yield. It is required that the self-weight deformation of the shell is small, and the traditional shell manufacturing method can no longer meet the requirements.

[0005] Finally, for the previous turbine guide vane, according to its structural characteristics, the traditional gating system and combination scheme is a side injection type, although it has the advantages of good exhaust performance and less impact of molten metal on the mold. , but it is not applicable to the R0110 heavy-duty gas turbine II class guide vane

This is because the inner chamber of the R0110 heavy-duty gas turbine II-stage guide vane is an intricate grid structure, and the wall thickness is relatively thin. The ceramic core acts as a barrier to the feeding of the metal inside, resulting in poor feeding. The side-injection scheme causes large shrinkage cavity defects at the thick part of the blade body, and easily causes cold shut and under-casting defects

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