Machining technology of cobalt beryllium copper blade

Abstract

The invention relates to a machining technology of a cobalt beryllium copper blade. The machining technology of the cobalt beryllium copper blade comprises the following steps of step 1, milling a front end profile and a rear end profile of the cobalt beryllium copper blade and the edges of the front end profile and the rear end profile; step 2, polishing the front end profile and the rear end profile by utilizing a selected grinding wheel; step 3, machining a narrow groove; and step 4, machining a multi-cone shaft section of a shaft neck by utilizing a frock clamp. The machining technology of the cobalt beryllium copper blade has the advantages of being capable of well guaranteeing the accuracy of the front end profile and the rear end profile of the blade and the edges of the two profiles by utilizing a five-axis linkage type high speed numerical control machine tool and performing once clamping and milling machining; being convenient to perform machining and improving the machining efficiency by utilizing numerical control and electro spark to perform combined machining on the narrow groove; and being capable of well meeting the requirements for clamping locating accuracy of the multi-cone shaft section of the shaft neck to guarantee the grinding machining accuracy of the multi-cone shaft section by utilizing a circular arc profile and a profile template with an angle of inclination to locate.

Description

technical field [0001] The invention relates to the field of metal processing technology, in particular to a processing technology of a beryllium cobalt copper blade. Background technique [0002] see figure 1 , the beryllium-cobalt-copper blade of the aeroengine is welded together by the blade body 1, the cover plate 2 and the journal 3, and the three are welded to form a semi-finished beryllium-cobalt-copper blade, and then the finishing process described later is carried out. which, combined with figure 2 and image 3 , the airfoil 1 is a thin-walled curved surface profile, and its front end is provided with a boss 10 matching the journal 3, and the inside of the boss 10 is provided with an elongated narrow groove 100; the main part of the airfoil 1 is two opposite Curved profile profile, which includes a front profile and a rear profile opposite to the front profile, wherein the rear profile is a smooth smooth surface, called the leaf back, and the front profile is a...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a processing technology of beryllium-cobalt-copper blades, so as to solve the difficulty in processing the multi-cone surfaces of the front and rear end profiles of the airfoil, the front and rear edges of the two profiles, and the shaft neck in the prior art. The technical problems of narrow slots in the slender structure of the blade body are difficult and inefficient

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