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A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine

A wax model and working technology, which is applied in the direction of manufacturing tools, metal processing equipment, casting molding equipment, etc., can solve the problems of blade wax model deformation, etc., and achieve the effects of improving the pass rate of precision casting, saving production costs, and reducing scrap rates

Active Publication Date: 2015-04-22
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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AI Technical Summary

Problems solved by technology

But there is still no effective way to solve the deformation problem of the blade wax model

Method used

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  • A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine
  • A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine
  • A method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine

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Embodiment Construction

[0030] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0031] In this embodiment, the blade body length of the turbine working blade that needs to be developed and produced is 190mm, the blade body chord width is 25mm, and the thickness of the inlet and outlet edges of the blade is 0.5-0.6mm. Among them, the airfoil parameters of the blade wax model and The turbine working blades are the same.

[0032] The method for eliminating the deformation of the ultra-thin and slender turbine working blade wax model comprises the following steps:

[0033] Step 1: Design the wax mold mold according to the parameters of the blade back shape of the turbine working blade;

[0034] Step 2: According to the theoretical coordinate value of the blade back surface of the turbine working blade, calculate the coordinate value of the working surface of the wax mold, and the calculation formula is:

[0035] Xb...

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Abstract

The invention relates to a method of eliminating deformation of a wax mould for an ultrathin elongated working blade of a turbine, and belongs to the technical field of manufacturing of blades of aviation engines. The method overcomes disadvantages in the prior art, provides a scheme of carrying and installing the blade wax mould by utilizing a wax mould clamping fixture, and discloses a design scheme of the wax mould clamping fixture. In an actual development and production process of a turbine working blade, because the wax mould clamping fixture is utilized to carry and install the blade wax mould, deformation of the blade wax mould is effectively controlled, and the deformation amount of the turbine working blade manufactured by utilization of the blade wax mould is reduced from original about 1 mm to now about 0.3 mm. Because the deformation amount is reduced, blade correction becomes relatively easy, thus avoiding generation of correction cracks, increasing the yield of precision casting of the turbine working blade by about 20%, largely reducing the rejection rate of the blade and largely saving the production cost.

Description

technical field [0001] The invention belongs to the technical field of manufacturing aeroengine blades, in particular to a method for eliminating the deformation of a wax model of an ultra-thin and slender turbine working blade. Background technique [0002] As an important type of aero-engine blades—turbine working blades, it has the characteristics of thin and slender blades. Taking a certain type of turbine working blades as an example, the length of the turbine working blades is 190mm, and the chord width of the blades is The thickness of the inlet and outlet sides of the blade is only 0.5-0.6mm, and the whole blade body has a certain twist angle. [0003] In the development and production process of turbine working blades, it is often found that the blade has a problem of excessive deformation. The deformation is about 1mm. At this time, the blade can only be corrected. It becomes quite difficult, and in the blade straightening process, correction cracks often occur at...

Claims

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Application Information

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IPC IPC(8): B22C7/02B22C9/04
CPCB22C7/02B22C9/04
Inventor 韩宏张民政顾欣朱洪斌张贺
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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