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A processing method for guide vane edge plate of aero-engine

An aero-engine and guide vane technology, which is applied in the field of aero-engine turbine guide vane processing, can solve problems such as inconvenient positioning and edge plate deformation, and achieve the effect of ensuring dimensional accuracy

Active Publication Date: 2016-04-06
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to overcome the defects of the prior art, provide a method for processing the edge plate of the guide vane of an aero-engine, and solve the problem that the edge plate of the guide vane of the low-pressure turbine is not easy to locate and easily lead to deformation of the edge plate in the existing processing technology

Method used

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  • A processing method for guide vane edge plate of aero-engine
  • A processing method for guide vane edge plate of aero-engine
  • A processing method for guide vane edge plate of aero-engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] Embodiment 1, the processing steps of the lower edge plate of the "I"-shaped cantilever structure of the guide vane are as follows:

[0024] (1) Use adhesive tape to fix the cloth bakelite or hard paper on both ends of the "I"-shaped cantilever structure of the clean blade lower edge plate (leaf pot, leaf back side lower edge plate), at this time the cloth bakelite Two groove cavities with side openings are formed with the "I"-shaped structural edge plate; when parts are in large batches, a fixing fixture can be designed to cover the groove cavities.

[0025] (2) Put the blade down, at this time, the groove on one side is facing upwards, lay the self-setting toothpaste powder in the groove, and then pour the self-setting toothpaste water, so that the toothpaste water just covers the toothpaste powder It is advisable; after more than ten minutes, the tray powder will solidify by itself to form a solid filling resin; or you can directly fill the groove with green low-melt...

Embodiment 2

[0030] Example 2, the processing steps of the lower edge plate of another two-stage guide vane "J"-shaped cantilever structure of a certain type of low-pressure turbine are as follows:

[0031] (1) Use adhesive tape to fix the cloth bakelite or hard paper on both ends of the "J"-shaped cantilever structure of the clean blade lower edge plate (leaf pot, lower edge plate on the back side of the leaf), at this time the cloth bakelite Form a side-opened groove cavity with the "J"-shaped structural edge plate. When the parts are in large batches, a fixed fixture can be designed to cover the formed cavity;

[0032] (2) Put the blade down, and at this time, the groove on one side is facing upwards, lay the toothpaste powder in the groove, the first layer is about 5mm thick, and it needs to be flat, then pour the self-setting toothpaste water, the toothpaste The ratio of the tray powder to the tray water is 10g: 5ml. It is advisable that the tray water just submerges the tray powder, ...

Embodiment 3

[0037] Embodiment 3, the processing steps of another welding assembly of high guide vane are as follows:

[0038] (1) in Figure 4 The guide vane edge plate shown has a number of exposed small cylinders (Φ0.8-Φ1.2). The partial area is filled with tray powder, and then poured with tray water. The ratio of tray powder to tray water is as follows: 10g: 5ml ratio, it is advisable to fill the groove with the tray water just submerged in the tray powder, mix it a little bit, and wait for more than ten minutes for the tray powder to solidify by itself to form a strong filling resin;

[0039] (2) Grinding the filling area, use a powerful slow-feed five-axis grinder MC607 or MFP50, and use a medium-pore grinding wheel to prevent the resin from blocking the pores of the grinding wheel and causing blade burns. The grinding wheel brand:

[0040]P350 (or 300) × 25 × 75 (76.2) WA70F9V35

[0041] (3) After the processing dimensions are all measured and qualified, the blades are put into a...

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Abstract

The invention discloses a method for machining guide vane margin plates of an aero-engine. The method includes the steps that the two ends of the lower margin plate of a guide vane workblank are respectively provided with a groove cavity, wherein the lateral sides of the groove cavities are open and the groove cavities are defined by baffles; firm filling resin formed by self-curing denture acrylic and self-curing liquid for denture acrylic is poured into the groove cavities or the groove cavities are directly filled with resin; the end face of the other side of the lower margin plate of the guide vane is positioned and ground with the end face of one side of the lower margin plate of the guide vane as the rough benchmark; the ground end face is used for positioning, a clamp clamps the position, filled with the resin, of the lower margin plate, and other positions of the upper margin plate and other positions of the lower margin plate are ground and turned respectively; the filling resin is gasified after machining. The denture acrylic is integrated with the vane after being self-cured, and therefore the positioning area is increased, one side of the left side end face and one side of the right side end face are used for positioning, the other side of the left side end face and the other side of the right side end face are used for clamping, and therefore the margin plates are stable and reliable. When a radial surface is turned, the clamp can easily move out of the inner arc turned position, a turning tool can not interfere with a clamp body, the vane can not deform due to radial force generated by point contact of the tuning tool, and therefore machining dimensional accuracy of the vane is guaranteed.

Description

technical field [0001] The invention relates to the processing technology of aero-engine turbine guide blades, in particular to a processing method for an aero-engine guide blade edge plate. Background technique [0002] For aero-engine turbine guide vanes, the blanks are generally cast with high-temperature alloy materials, and the lower edge plates of the guide vanes in the model are mostly such as figure 1 The "Π" shaped structure shown. For blades of this material and structure, especially the thickness of the lower edge plate, that is, the lower part of the "Π" shape, is 3-5mm, and the processing length of the end surface is generally not more than 15-18mm. The processing technology of Spey 202 engine blade of Luo company is to complete the processing by forming and grinding the end surface and radial surface of the left and right sides at one time, and the positioning and clamping of the tooling are easy to realize. For the high-performance low-pressure turbine guide...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/02
CPCB23P15/02
Inventor 刘建珺李绍鹏
Owner AECC AVIATION POWER CO LTD
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