Method for precisely controlling boundary dimension of hollow single-crystal turbine moving blade

A technology of precise control of the shape and size, applied in the direction of single crystal growth, single crystal growth, chemical instruments and methods, etc., can solve the problems of airfoil profile, torsion angle, and position tolerance, so as to avoid damage, Avoid multiple size measurements and repeated grinding and polishing, and improve the effect of development and production efficiency

Pending Publication Date: 2020-07-10
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Application Information

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Problems solved by technology

[0005] The present invention is designed to solve the above-mentioned problems in the prior art and provides a method for precise control of the external dimensions of hollow single crystal turbine blades. Unreasonable coefficient setting leads to out-of-tolerance profile, torsion angle, position, etc. of the airfoil profile, improves the dimensional conformity of blade precision castings, and meets the needs of advanced aero-engines for precise control of the size of single-crystal turbine blades

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  • Method for precisely controlling boundary dimension of hollow single-crystal turbine moving blade

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Embodiment 1

[0025] See attached figure 1 As shown, in this implementation, the hollow single crystal turbine working blade is taken as an example. The casting has the characteristics of compound bending and twisting of the blade body 1, and the wall thickness is thin, and the blade edge plate 2 and tenon 3 are thick. According to the requirements of the drawing, when designing the shape mold of the working blade of a single crystal turbine, the blade body is taken as one part, and the blade edge plate and tenon are taken as the other part, and the shrinkage coefficients are set respectively, specifically: the blade body 1 shrinks in the direction of the stacking axis The coefficient is 1.4%, the shrinkage coefficient of blade edge plate 2 and tenon 3 in the direction of stacking axis is 1.8%, the shrinkage coefficient of blade edge plate 2 and tenon 3 in the direction of stacking axis-the shrinkage coefficient of blade body 1 in the direction of stacking axis= 0.4%.

[0026] Using the sh...

Embodiment 2

[0028] See attached figure 1 As shown, in this implementation, the hollow single crystal turbine working blade is taken as an example. The casting has the characteristics of compound bending and twisting of the blade body 1, and the wall thickness is thin, and the blade edge plate 2 and tenon 3 are thick. According to the requirements of the drawing, when designing the shape mold of the working blade of a single crystal turbine, the blade body is taken as one part, and the blade edge plate and tenon are taken as the other part, and the shrinkage coefficients are set respectively.

[0029] Specifically: the shrinkage coefficient of the blade body 1 in the stacking axis direction is 1.6%, the shrinkage coefficient of the blade edge plate 2 and the tenon 3 in the stacking axis direction is 1.6%, and the positions of the blade edge plate and the tenon are along the blade stacking axis The direction of blade body moves 0.15mm.

[0030] Adopting the method for precise control of th...

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Abstract

The invention discloses a method for precisely controlling the boundary dimension of a hollow single-crystal turbine moving blade. In the design process of a wax mold compacting tool set of the hollowsingle-crystal turbine moving blade, a blade body serves as one part, a blade margin plate and a tenon serve as the other part, shrinkage coefficients are set correspondingly, and the setting mode isrealized by means of one of the following methods: the first method: when the shrinkage coefficient of the blade body and the shrinkage coefficient of the blade margin plate and the tenon are different, the ratio of the shrinkage coefficient of the blade margin plate and the tenon in the direction of an accumulating and overlapping axis to the shrinkage coefficient of the blade body in the direction of the accumulating and overlapping axis is 0.1-0.5%; and the second method: when the shrinkage coefficient of the blade body and the shrinkage coefficient of the blade margin plate and the tenonare the same, the position of the blade margin plate and the tenon moves by 0.05-0.3 mm in the direction of the accumulating and overlapping axis of the blade towards the blade body. By means of the method, the manual grinding and polishing repairing caused by the out-of-tolerance of the boundary dimension can be effectively avoided, the precise control over the boundary dimension of the blade isrealized, and the percent of pass of the boundary dimension of the hollow single-crystal turbine moving blade is greatly improved.

Description

technical field [0001] The invention relates to a method for precisely controlling the external dimensions of hollow single-crystal turbine working blades, and belongs to the technical field of investment casting precision casting of single-crystal high-temperature alloy turbine blades of aeroengines. Background technique [0002] The overall structure of the single crystal superalloy turbine working blade of an aero-engine can be divided into the blade body, the edge plate and the mortise and tenon parts. The cross-sectional dimension of the tenon is significantly larger than that of the blade body. At present, the working blades of single crystal turbines all adopt the investment casting process, and the main processes include mold design and manufacture, core preparation, wax mold preparation, shell preparation, melting and pouring, etc. [0003] When designing the wax mold pressing mold (hereinafter referred to as the shape mold) of the hollow single crystal turbine wor...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22C9/04B22C9/24C30B11/00C30B29/52
CPCB22C9/04B22C9/24C30B11/006C30B29/52
Inventor 杨亮
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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