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Mold for forming hollow static blade flow guide core of light-weight gas turbine engine turbine

A technology for gas turbines and stationary blades, applied to forming tools, manufacturing tools, metal processing equipment, etc., can solve the problems of complex processing procedures, difficulty in unifying individual size and profile deviations, etc., and achieve simplified preparation procedures, simple operations, Guaranteed the effect of external dimensions and line deviation

Inactive Publication Date: 2014-12-24
HARBIN TURBINE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The object of the present invention is to provide a light-duty gas turbine turbine hollow static vane guide core molding mold, because of the complex profile structure of the guide core in the process of processing the light-duty gas turbine turbine hollow stationary vane guide core. The processing procedure is complicated, and the size and profile deviation between individuals are difficult to unify

Method used

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  • Mold for forming hollow static blade flow guide core of light-weight gas turbine engine turbine
  • Mold for forming hollow static blade flow guide core of light-weight gas turbine engine turbine
  • Mold for forming hollow static blade flow guide core of light-weight gas turbine engine turbine

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specific Embodiment approach 1

[0012] Specific implementation mode one: combine figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Image 6 , Figure 7 with Figure 8 This embodiment is described. In this embodiment, a light-duty gas turbine turbine hollow vane guide core molding mold includes a convex module 1, a concave module 2 and a mandrel 3, and a convex edge is processed on the lower end surface of the convex module 1. 4. The lower end surface of the rib 4 is the first curved surface 14, and the upper end surface of the concave module 2 is processed with a groove 5 that matches the rib 4 on the convex module 1, and the groove bottom of the groove 5 It is the second curved surface 15 , when the male module 1 is fastened with the female module 2 , when the convex rib 4 is in the groove 5 , the mandrel 3 is located in the groove 5 and has a gap with the convex rib 4 .

[0013] The raw material for manufacturing the diversion core in the present invention is a preformed high temperature all...

specific Embodiment approach 2

[0016] Specific implementation mode two: combination figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Image 6 , Figure 7 with Figure 8 To illustrate this embodiment, the mold for forming the guide core of a light-duty gas turbine turbine hollow stator vane described in this embodiment also includes two auxiliary limit blocks 6, and two auxiliary limit blocks 6 are fixedly connected to the upper end surface of the concave module 2. The limit block 6, the two auxiliary limit blocks 6 are respectively located on both sides of the groove 5. In this embodiment, the two auxiliary limit blocks 6 are provided for the convenience of mold ejection. After stamping and forming using the present invention, there is a gap between the convex module 1 and the concave module 2 through the two auxiliary limit blocks 6, and the gap makes the convex module 1 The separation between the module 1 and the concave module 2 is easier, which facilitates the smooth progress of the proc...

specific Embodiment approach 3

[0017] Specific implementation mode three: combination figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Image 6 , Figure 7 , Figure 8 , Figure 9 with Figure 10 To illustrate this embodiment, a light-duty gas turbine turbine hollow stator vane guide core molding mold in this embodiment also includes a baffle 7, when the convex module 1 and the concave module 2 are engaged, the baffle 7 can be Disassemble the connection on the same side of the male module 1 and the female module 2. The setting of the baffle 7 is to make the position between the convex module 1 and the concave module 2 stable and not easy to misalign when the male module 1 and the female module 2 are in the buckled state to stamp the mandrel 3 with the preformed superalloy steel cylinder . The processing accuracy of the processed flow guiding core is effectively guaranteed. Other compositions and connections are the same as those in Embodiments 1 and 2.

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Abstract

The invention provides a mold for forming a hollow static blade flow guide core of a light-weight gas turbine engine turbine, and relates to a mold. The existing hollow static blade flow guide core of the light-weight gas turbine engine turbine has the problems that in the processing process, the molded line structures of the flow guide core are complicated, so the processing work procedures are complicated, and the dimensions and the molded line deviation among individuals are difficult to unify. The mold for forming the hollow static blade flow guide core of the light-weight gas turbine engine turbine comprises a convex module, a concave module and a mandrel, wherein a convex edge is processed on the lower end surface of the convex module, the lower end surface of the convex edge is a first curve surface, a groove matched with the convex edge arranged on the convex module is processed on the upper end surface of the concave module, the groove bottom of the groove is a second curve surface, and when the convex module and the concave module are buckled and the convex edge is positioned in the groove, the mandrel is positioned in the groove and is arranged in a way of forming a gap with the convex edge. The mold provided by the invention is used in the forming process of the hollow static blade flow guide core of the light-weight gas turbine engine turbine.

Description

technical field [0001] The invention relates to a mold for forming a guide core of a light-duty gas turbine turbine hollow stationary vane. Background technique [0002] The hollow stationary blade of a gas turbine is a blade that can accelerate the expansion of high-temperature gas in it and convert the internal energy of the gas into kinetic energy. Due to the harsh conditions of the turbine hollow static blades, which are mainly surrounded by high temperature and large temperature difference gas, the guide core is installed in the hollow cavity of the turbine hollow static blades, and its function is to work in the turbine hollow static blades. During the operation, guide the flow direction of the compressed air in the turbine hollow static blades, increase the residence time of the compressed air in the turbine hollow static blades to cool the turbine hollow static blades, and prevent the turbine hollow static blades from being burned. Therefore, when the flow guide cor...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21D37/10
Inventor 王德彪傅晓萍邸春光刘钧周卫潇王民保王恒朴永伟
Owner HARBIN TURBINE
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