Clamping positioning device for finish machining aero-engine turbine blade

Abstract

The invention discloses a clamping positioning device for finish machining an aero-engine turbine blade, and the clamping positioning device comprises a framework consisting of a front cover plate, a rear cover plate, a left cover plate, a right cover plate, an upper cover plate and a lower cover plate through screws, a back surface positioning compression block which is arranged inside the framework and matched with the back molded surface of a blade body, a pelvic surface positioning compression block which is matched with a pelvic molded surface of the blade body, a positioning compression block which is matched with the blade body or an exhaust edge molded surface and a compression component which is used for compressing the other edge of the blade body, wherein one of the back surface positioning compression block and the pelvic surface positioning compression block is adjustably arranged on the front cover plate or the rear cover plate in the compression direction, the right cover plate or the left cover plate is provided with a blade body placing opening, and the cover plate is provided with a blade axial positioning component. Compared with the prior art, a fixing way for utilizing low-melting-point alloy to position the blade is adopted, so that the blade machining cost is greatly reduced, and problems caused by removing the low-melting-point alloy on the blade body can be avoided.

Description

technical field [0001] The invention relates to the processing of tenons of turbine blades of aero-engines, and more specifically relates to a clamping and positioning device for finishing the tenons of turbine blades of aero-engines. Background technique [0002] The turbine blades in aero-engines are formed by precision casting, in which the airfoil is formed in one step, without finishing allowance, and does not need to be machined, but the crown and tenon of the blade need to be further finished by machining to meet the Blade assembly requirements. Since the airfoil surface is a free-form surface formed by spatial coordinate points, it is difficult to realize its positioning and clamping by conventional fixture schemes. The finishing positioning of traditional engine turbine blades is to fix the blade body by pouring low melting point alloy in a square box. Although this method can realize the positioning of the blades, there are problems and hidden dangers in terms of ...

AI Technical Summary

Problems solved by technology

[0005] Aiming at the problems existing in the prior art of fixing blades by pouring low-melting point alloys in square boxes, the purpose of the present invention is to provide a device for positioning and clamping blades by means of mechanical clamping to complete the finishing of blade tenons. In order to fundamentally solve various problems and troubles in removing the residual alloy on the surface of the airfoil and the alloy in the cavity of the airfoil

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