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A manufacturing method of a 400mw class g/h class heavy-duty gas turbine nozzle fairing

A technology for a gas turbine and a manufacturing method, applied in the field of gas turbines, can solve problems such as difficult production, easy deformation, complex structure, etc., and achieve the effects of reducing difficulty, solving technical difficulties, and improving production efficiency and qualification rate

Active Publication Date: 2022-06-21
HARBIN TURBINE +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problems that the existing fairing structure product structure is complex, easily deformed during processing, and conventional mechanical processing and manufacturing are difficult to manufacture, a method for manufacturing a 400MW class G / H class heavy-duty gas turbine nozzle fairing is proposed.

Method used

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  • A manufacturing method of a 400mw class g/h class heavy-duty gas turbine nozzle fairing
  • A manufacturing method of a 400mw class g/h class heavy-duty gas turbine nozzle fairing
  • A manufacturing method of a 400mw class g/h class heavy-duty gas turbine nozzle fairing

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specific Embodiment approach 1

[0016] Embodiment 1: Combining Figure 1 to Figure 3 Illustrating this embodiment, the method for manufacturing a nozzle fairing for a 400MW-class G / H-class heavy-duty gas turbine described in this embodiment includes the following steps:

[0017] Step 1: Parts splitting: According to the fairing drawing, design three dividing lines along the axial direction of the fairing, and split the parts into the first workpiece, the second workpiece, the third workpiece and the fourth workpiece;

[0018] Step 2: Machining each subsection: According to the size of the divided drawings, the shapes of the first workpiece, the second workpiece, the third workpiece and the fourth workpiece are respectively processed;

[0019] Step 3: Positioning welding: After the first workpiece, the second workpiece, the third workpiece and the fourth workpiece are assembled and positioned, the first workpiece and the second workpiece, the second workpiece and the third workpiece, and the third workpiece a...

specific Embodiment approach 2

[0026] Specific implementation mode 2: Combining Figure 2 to Figure 3 Describing this embodiment, in step 1 of this embodiment, the first dividing line is set between the cover plate 1 and the arc bottom surface of the inner cover 2 , and the second dividing line is set at the arc of the inner cover 2 . Between the bottom surface and the circular arc bottom surface of the intermediate cover body 3 , the third dividing line is provided on the outer side of the circular arc bottom surface of the intermediate cover body 3 . The technical features not disclosed in this embodiment are the same as those in the first embodiment.

specific Embodiment approach 3

[0027] Specific implementation three: combination Figure 2 to Figure 3 Illustrating this embodiment, in step 2 of this embodiment, turning is used when processing the outer shape of the first workpiece A, and low melting point alloy casting is used when processing the outer shape of the second workpiece B, the third workpiece C, and the fourth workpiece D. method for turning. The technical features not disclosed in this embodiment are the same as those in the second embodiment.

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Abstract

The invention discloses a manufacturing method of a 400MW class G / H class heavy-duty gas turbine nozzle fairing, which relates to the technical field of steam turbines. The present invention aims to solve the problems that the structure of the existing fairing structure product is complex, easy to deform during processing, and difficult to manufacture in a conventional mechanical processing and manufacturing manner. The manufacturing method includes dismantling of parts; machining of each segment; positioning welding; grinding of weld seam; and machining of waist-shaped holes. The invention is used for processing thin-wall fairings.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a method for manufacturing a nozzle fairing of a 400MW-class G / H-class heavy-duty gas turbine. Background technique [0002] The nozzle fairing of the 400MW class G / H heavy-duty gas turbine is a cylindrical thin-walled part. The whole is a three-layer structure inside and outside. The two inner walls are of a bell mouth structure. It is only 13.5mm and 12.5mm, the length of the straight section is 88mm and 74mm, and the wall thickness is only 1.5mm. Due to the insufficient rigidity of thin-walled parts, it is easy to deform during processing, and it is difficult to manufacture by conventional machining methods, resulting in overall processing and manufacturing. extremely difficult. SUMMARY OF THE INVENTION [0003] In order to solve the problems that the existing fairing structure products are complex in structure, easy to deform during processing, and difficult to manufa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 王通王昌军杨克振安天成张景龙沈阳威张仁军孙柏慧武尚尚隋妍于华
Owner HARBIN TURBINE
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