Machining method for tenon tooth of shrouded turbine blade

Abstract

The invention discloses a machining method for a tenon tooth of a shrouded turbine blade. The method includes the steps of A, selecting six positioning points for a blank part and guaranteeing the position dimensions of the positioning points in the process of producing the blank part; B, providing a clamp according to the position dimensions of the positioning points determined in the step A; C, clamping the blank part produced in the step A on the clamp provided in the step B and machining a tenon tooth blank part to form the tenon tooth; and D, carrying out clamping with the tenon tooth as the clamping and locating datum, and machining a lower flange plate and an upper flange plate to complete machining of the turbine blade. According to the machining method for the tenon tooth of the shrouded turbine blade, datum conversion errors can be reduced, accumulated errors caused by datum conversion can be avoided, and the qualification rate of delivery of each time can reach above 90% in actual production.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a method for machining crowned turbine blade mortise teeth. Background technique [0002] figure 1 It is a structural schematic diagram of a turbine blade of an aero-engine, see figure 1 as shown, figure 1 The turbine blade 1 shown in includes blade body 11, lower edge plate 12, mortise teeth 13 and upper edge plate 14, which has more upper edge plate 14 than ordinary gas turbine blades, that is, more blade crown parts , Therefore, the structure of the turbine blade 1 is usually referred to simply as a shrouded blade. The machining of the turbine blade 1 requires high dimensional accuracy, and its profile is more complex than that of ordinary gas turbine blades, so it is difficult to process, especially the central position of the airfoil 11 is very important to the performance parameters of the engine. [0003] figure 2 for the preparation figure 1 The schematic stru...

AI Technical Summary

Problems solved by technology

In addition, as mentioned above, in the existing processing method, due to the need to go through multiple reference transformations, it is inevitable that there will be transformation errors, which will directly affect the machining accuracy of the airfoil position and installation angle.

The pass rate of the existing method does not exceed 40% in one submission in actual production

Images