Method for processing TC11 material blade

Abstract

The present invention relates to a method for processing a TC11 material vane. The method can conveniently machine out a TC11 material aviation vane which has large torsional angle, large string width, large rough blank profile margin and uneven margins at all positions and is easy to machine. The method comprises the steps as follows: retesting a central forging hole, processing the back of a middle body, a technical reference of the air outlet side and a vane top axial reference face, rough machining a vane root and a vane root bottom surface technical button, processing for reverse adjustment, finish milling the profile, polishing the profile, processing the total length, removing a vane top central hole and removing the vane root bottom surface button. The present invention is characterized in that the vane top central hole during swaging processing is always kept until the total length is cut; a forging vane top central hole is considered as the reference; after the distressing treatment, the reverse adjustment is conducted, and the vane root and the surface of the vane root bottom surface technical button is fine finished; a vane root positioning area is increased, so the technical button is reserved at the vane root bottom surface, a vane root molding knife is used for processing the vane root and the surface of the vane root bottom surface technical button to ensure that the surface of the vane root bottom surface technical button is consistent with the vane root; and when milling comprehensively, the vane root and the surface of the vane root bottom surface technical button are used for positioning, and the vane profile is rough milled and fine milled.

Description

(1) Technical field [0001] The invention relates to the technical field of blade processing, in particular to a processing method for blades made of TC11 material. (2) Background technology [0002] With the advancement of domestic aero-engines, the requirements for high mechanical properties and light weight are put forward for aero-engine blades. Therefore, the design trend of aero-engine blades is to select high-performance and difficult-to-machine materials such as TC11 titanium alloys, and to design blade shapes , continuously reduce the thickness of the blade, and increase the twist angle and chord width of the blade. This has just brought big problem to the manufacture of blade. Because the titanium alloy will rebound after cold correction, it is difficult to meet the design requirements of the blade once the processing deformation occurs. Therefore, the traditional TC11 material blade processing scheme does not use the method of profile milling, but uses the profil...

AI Technical Summary

Problems solved by technology

However, with the increase of blade twist angle and chord width in blade design, the difficulty of precision forging of blades is increasing, and die forging has to be adopted.

However, the die forging accuracy is insufficient, resulting in the continuous increase of the margin of the blade rough surface, and the uneven margin everywhere, so that the blade surface cannot be processed by the chemical milling process with the same margin.

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