Machining method for air inlet fairing of air compressor of heavy-duty gas turbine

A technology of air intake fairing and processing method, which is applied to the processing of fairings and the processing of air intake fairings of heavy-duty gas turbine compressors, and can solve the problem of no clamping position and the like

Inactive Publication Date: 2021-07-06
HARBIN TURBINE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention solves the problem that there is no clamping position for the fairing during processing, and it is impossible to ensure the finishing of all positions by clamping the workpiece, and further provides a processing method for the intake fairing of the heavy-duty gas turbine compressor

Method used

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  • Machining method for air inlet fairing of air compressor of heavy-duty gas turbine
  • Machining method for air inlet fairing of air compressor of heavy-duty gas turbine
  • Machining method for air inlet fairing of air compressor of heavy-duty gas turbine

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specific Embodiment approach 1

[0026] Specific implementation mode one: combine Figure 1 to Figure 6 Illustrate this embodiment, a kind of auxiliary fixture that is used for processing the intake fairing of heavy-duty gas turbine compressor described in this embodiment, this processing method is carried out according to the following steps:

[0027] Step 1: Since the inner hole of the workpiece 1 is a casting surface, no processing is required. In order to find out the uniform wall thickness, the concentricity between the outer circle of the casting blank and the inner hole is re-measured by scribing; At the outer blank margin of the end clamping position, the alignment datum plane and outer circular molding line are used for the turning process;

[0028] Step 2: leave margins at the positions of the plurality of flange holes 1-2, drill six process screw holes evenly distributed on the outer surface of the workpiece 1 along the circumferential direction, and the six process screw holes are used to connect ...

specific Embodiment approach 2

[0033] Specific implementation mode two: combination Figure 3-Figure 6 To describe this embodiment, the number of flange holes 1-2 in this embodiment is eighteen, and the eighteen flange holes 1-2 are evenly distributed along the circumferential direction.

[0034] Other components and connections are the same as those in the first embodiment.

specific Embodiment approach 3

[0035] Specific implementation mode three: combination Figure 3 to Figure 6 To describe this embodiment, the flange hole 1-2 in this embodiment is a stepped hole.

[0036] Other compositions and connections are the same as those in Embodiment 1 or 2.

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Abstract

The invention relates to a machining method for an air inlet fairing of an air compressor of a heavy-duty gas turbine, and relates to the machining method of the fairing. The machining method aims to solve the problems that when the fairing is machined, no clamping position exists, and finish machining of all positions cannot be guaranteed by clamping a workpiece. According to the machining method, workpiece blank allowance is determined through scribing measurement, the workpiece is clamped on one side with thick wall thickness of the workpiece, most of external molded lines are finely turned, a part of process alignment benchmarks are finely turned, subsequently, the positions of air inlet fairing flange holes are aligned according to the benchmarks, allowance is reserved for pre-drilling process screw holes, the process screw holes are connected with an auxiliary tool to serve as a clamping position for next-step finish machining of the workpiece, after the surface of a product and a vibration reduction groove are machined, an auxiliary clamp is detached, the flange holes are machined in the positions of the process screw holes, so that clamping is guaranteed, and the appearance of the product is not damaged.

Description

technical field [0001] The invention relates to a processing method of a fairing, in particular to a processing method of a heavy-duty gas turbine compressor intake fairing, and the invention belongs to the technical field of heavy-duty gas turbines. Background technique [0002] For the air intake fairing in the second half of the compressor of the company's re-ignition project, because the blank incoming material does not reserve a chuck position, the workpiece is spherical as a whole, and there is no reference and clamping position during machining, so it is impossible to guarantee all parts by clamping the workpiece. The finishing machining of the position requires high precision, and if there is a deviation, it will easily lead to scrapping. Contents of the invention [0003] The present invention solves the problem that there is no clamping position for the fairing during processing, and it is impossible to ensure the finishing of all positions by clamping workpieces...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 吴雯莉吕思佳隋妍周君泰成国富杨克振李铁成
Owner HARBIN TURBINE
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