The aero-engine blade profile is characterized by its thin-wall weak rigid structure, complex space curved surface shape, poor material cutting performance, strict contour and positional accuracy, etc., so that it can be processed even with advanced multi-axis machining equipment and better tool materials. Processing, if the process measures are not appropriate, it is still not easy to obtain satisfactory processing efficiency and processing quality. Among them, the fixture structure used for processing plays a crucial role in ensuring satisfactory precision machining results.
Due to the lack of structural considerations in the initial fixture structure, the machining quality of the blade is not affected by the clamping deformation, but also due to the deformation of the blade due to the insufficient rigidity of the blade. The deformation effect of the situation is more difficult to control because of the poor machinability of the blade material and the easy wear of the tool . It not only makes the machining of the blade profile difficult to obtain the guarantee of machining accuracy, but also limits the change of cutting parameters. The processing efficiency is improved. To this end, we have designed a reasonable fixture structure by comprehensive analysis of blade profile characteristics, geometric accuracy requirements and machining mode characteristics, so that the blade profile processing not only achieves satisfactory machining accuracy quality, but also eliminates passing. Potential obstacles to changing cutting parameters for efficiency gains.
I. Analysis of the problems caused by fixture structure factors
The problem that arises
A kind of biaxial neck blade structure is shown in Fig. 1. It consists of three main parts: the journals of the two ends and the edge plate and the intermediate profile. The blade profile structure to be processed has a three-dimensional surface shape (see Figure 1 and Figure 2). The geometry accuracy requirement of the profile is to ensure its own shape accuracy and positional accuracy with respect to the blade's specified reference plane.
Since the blade profile structure is a spatial three-dimensional surface form, the five-axis linkage CNC machining center equipment is selected for the forming process. The initial machining positioning mode of the blade profile is to use a special clamp coupled with the front end rotary shaft of the device, outside the front end of the blade. The circular surface A, the angular plane D, and the front end edge end face B are positioned and associatedly pressed, and the top end of the blade rear end face is tightened using the tip on the rotary shaft of the rear end of the device. The blade machining is a helical rotary milling controlled by a numerical control program, and the machining trajectory is shown in FIG.
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