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Multiple-connection-blade precision casting method

A technology of precision casting and concatenation, applied in the direction of casting molding equipment, molds, mold components, etc., can solve problems such as low pass rate, crack structure, looseness, etc., and achieve cracks and looseness, consistent cooling rate, cooling uniform effect

Active Publication Date: 2016-02-03
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The guide vanes of low-pressure turbines are mostly hollow triplet-five-joint blades. The wall thickness of the blade body is required to be 0.8mm-1.5mm, and the thickness of the edge plate is about 2mm. During the development process, due to the many runners and the complexity of the gating system, The filling process of the pouring process is disordered, because the filling time of each blade shell is inconsistent, and the local heat dissipation during the cooling process is poor, which makes the cooling process complicated, and it is easy to produce cracks and loose tissue at the transition of the small edge plate of the blade and the edge plate of the blade body. less than 20%

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] The concatenated blade precision casting method of this embodiment is carried out according to the following steps:

[0024] (1) Use a high-pressure press to press the multi-joint blade wax mold, keep the temperature of the wax storage tank at 80°C, and the temperature of the wax injection nozzle at 73°C, inject the wax liquid into the multi-joint blade ceramic core, and the injection pressure is 2.0MPa , the mold clamping pressure is 5.0MPa, and the holding time is 30s to obtain the concatenated blade wax mold;

[0025] (2) From the inside to the outside, three layers of refractory materials are coated on the surface of the concatenated blade wax model in sequence, and after the third layer of refractory material is coated, at the positions of the large edge plate 6 and the small edge plate 7 of the concatenated blade Coating coolant, the coolant is made by mixing silica sol, corundum powder and iron pellets according to the weight ratio of 1:5:8, and then continue to ...

Embodiment 2

[0029] (1) Use a high-pressure press to press the multi-joint blade wax model, keep the temperature of the wax storage tank at 80°C, and the temperature of the wax injection nozzle at 71°C, inject the wax liquid into the multi-joint blade ceramic core, and the injection pressure is 2.0MPa , the clamping pressure is 5.0MPa, and the holding time is 40s to obtain the concatenated blade wax mold;

[0030] (2) From the inside to the outside, three layers of refractory materials are coated on the surface of the concatenated blade wax model in sequence, and after the third layer of refractory material is coated, at the positions of the large edge plate 6 and the small edge plate 7 of the concatenated blade Coating coolant, the coolant is made by mixing silica sol, corundum powder and iron pellets according to the weight ratio of 1:6:5, and then continue to coat the fourth to eighth layers of refractory materials, and finally pass through Drying and hardening, dewaxing, and then roast...

Embodiment 3

[0034] (1) Use a high-pressure press to press the multi-joint blade wax mold, keep the temperature of the wax storage tank at 80°C, and the temperature of the wax injection nozzle at 75°C, inject the wax liquid into the multi-joint blade ceramic core, and the injection pressure is 2.0MPa , the mold clamping pressure is 5.0MPa, and the holding time is 50s to obtain the concatenated blade wax mold;

[0035] (2) From the inside to the outside, three layers of refractory materials are coated on the surface of the concatenated blade wax model in sequence, and after the third layer of refractory material is coated, at the positions of the large edge plate 6 and the small edge plate 7 of the concatenated blade Coating coolant, the coolant is made by mixing silica sol, corundum powder and iron pellets according to the weight ratio of 1:4:6, and then continue to coat the fourth to eighth layers of refractory materials, and finally pass through Drying and hardening, dewaxing, and then r...

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Abstract

The invention belongs to the technical field of precision casting, and particularly relates to a multiple-connection-blade precision casting method. The position of an edge plate of a multiple-connection-blade shell is coated with a cooling agent, a pouring system is improved, a flow gate and a cross gate at the air inlet edge are removed, and the preheating temperature and the pouring temperature of the shell are further optimized. According to the technical scheme, the problems of cracks and looseness during precision casting multiple-connection-blade production are effectively solved, the qualified rate of a guide blade of a low-pressure turbine is improved to more than 60% from 20%, the production efficiency is improved, and the economic benefit is obvious.

Description

technical field [0001] The invention belongs to the technical field of precision casting, and in particular relates to a precision casting method for conjoined blades. Background technique [0002] The guide vanes of low-pressure turbines are mostly hollow triplet-five-joint blades. The wall thickness of the blade body is required to be 0.8mm-1.5mm, and the thickness of the edge plate is about 2mm. During the development process, due to the many runners and the complexity of the gating system, The filling process of the pouring process is disordered, because the filling time of each blade shell is inconsistent, and the local heat dissipation during the cooling process is poor, which makes the cooling process complicated, and it is easy to produce cracks and loose tissue at the transition of the small edge plate of the blade and the edge plate of the blade body. less than 20%. Contents of the invention [0003] Aiming at the problems existing in the prior art, the present ...

Claims

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Application Information

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IPC IPC(8): B22C9/22B22C9/04B22C9/08B22C1/18B22D27/04
Inventor 王永明祝世哲王铁军刘家胜张松胜
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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