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Machining method for large-diameter thin-wall diffuser of aero-engine

An aero-engine and processing method technology, applied in the field of mechanical processing, can solve the problems of low pass rate of large-diameter thin-walled diffusers of aero-engines, and achieve the effects of reduced deformation, high processing efficiency, and increased shift output

Inactive Publication Date: 2020-09-18
HUNAN SOUTH GENERAL AVIATION ENGINE CO LTD
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Problems solved by technology

[0006] In view of this, the object of the present invention is to provide a method for processing large-diameter thin-walled diffusers of aero-engines, which can effectively solve the problem of low qualification rate of large-diameter thin-walled aero-engine diffusers

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  • Machining method for large-diameter thin-wall diffuser of aero-engine
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  • Machining method for large-diameter thin-wall diffuser of aero-engine

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Embodiment Construction

[0066] The embodiment of the invention discloses a method for processing a large-diameter thin-walled diffuser of an aero-engine, so as to improve the qualification rate of the diffuser.

[0067] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0068] see Figure 30 , Figure 30 It is a schematic flowchart of a processing method for a large-diameter thin-walled diffuser of an aero-engine according to a specific embodiment of the present invention.

[0069] In a specific embodiment, the method for processing a lar...

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Abstract

The invention discloses a machining method for a large-diameter thin-wall diffuser of an aero-engine. The machining method comprises the following steps of clamping by using a soft claw, and semi-rough turning a diffuser outer contour; clamping by using the soft claw, and rough turning a diffuser inner contour; clamping by using a clamp, and rough turning the diffuser outer contour; rough millingradial vanes by using a pendulum-type cutter feeding; rough milling axial vanes; clamping by using a clamp, fine turning the radial vanes and an outer circle datum; clamping by using the clamp, fine turning an inner contour outer ring area, and semi-fine turning an inner contour inner ring area; clamping by using the clamp, and semi-fine turning an outer contour; fine-turning end surfaces of radial vanes; fine turning inner contour; fine turning outer contour; fine milling the radial vanes; and fine milling the axial blades. Through the machining method, the numerical milling rough machining efficiency of the radial vanes is high; the output per shift is improved by 150 percent; and the machining cost of components is reduced. The deformation of the diffuser is reduced; the machining quality is ensured; and then, the yield of diffusers is improved.

Description

technical field [0001] The invention relates to the technical field of mechanical processing, and more specifically relates to a processing method for a large-diameter thin-walled diffuser of an aero-engine. Background technique [0002] With the rapid development of the world's aviation industry, while aero-engines continue to develop new aircraft, they also put forward higher requirements for the material and structural characteristics of the engine. The latest generation of military turboshaft engine diffuser adopts a new design concept. The diffuser is made of domestic standard high-temperature alloy GH4XXX. The material removal rate is as high as 95%. Point and other design features, this new structure causes the diffuser to be easily deformed during processing, and there is stress inside the product after processing. In the natural state, the parts are prone to serious deformation and cannot meet the precision requirements. [0003] The conventional diffuser processin...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 何思洋张劲徐忠徐宇超陈雄黄如吴学深
Owner HUNAN SOUTH GENERAL AVIATION ENGINE CO LTD
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