Machining tooling and machining method for ultra-large gas turbine blade

Abstract

The invention discloses machining tooling and machining method for an ultra-large gas turbine blade. The machining tooling comprises a rotary table, and a first clamp and a second clamp fixed to the rotary table; the rotary table is provided with a through hole penetrating through two opposite ends of the rotary table and used for containing the turbine blade; the first clamp is located at the first end of the through hole, and is used for positioning and clamping an extension root of the turbine blade; and the second clamp is located at the second end of the through hole, and is used for positioning and clamping a blade body of the turbine blade. According to the machining tooling, the rotary table is arranged in a hollow form, the turbine blade is placed in the hollow through hole, and the first clamp and the second clamp are arranged at the two ends of the through hole so as to fix the extension root of the end where a tenon of the turbine blade is located and the blade body of the end where a blade crown of the turbine blade is located, thus guaranteeing that the tenon and the blade crown of the turbine blade cannot deviate when the turbine blade is machined, and further, the machining precision of the tenon and the blade crown of the turbine blade is improved, the size of the whole machining tooling is also reduced, the machining range of the machine tooling is effectively reduced, and cost is reduced.

Description

technical field [0001] The invention relates to the technical field of gas turbine blade processing, in particular to a processing tool and a processing method for an ultra-large gas turbine blade. Background technique [0002] Gas turbine blades are one of the important parts of gas turbines, such as figure 1 As shown, it usually includes four parts: tenon, extension root, leaf body and leaf crown. At present, there are still a large number of processing technical problems for gas turbine blades that need to be resolved urgently, such as key technologies such as end processing (tenons and blade crowns) of gas turbine blades. [0003] Existing gas turbine blades have complex mortise structures, many surfaces to be processed, and high processing precision. Therefore, the end processing of existing gas turbine blades is usually carried out step by step with multiple fixtures. First, a The fixture fixes the turbine blade, and then performs multiple unilateral grinding on the ...

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Problems solved by technology

[0003] Existing gas turbine blades have complex mortise structures, many surfaces to be processed, and high processing precision. Therefore, the end processing of existing gas turbine blades is usually carried out step by step with multiple fixtures. First, a The fixture fixes the turbine blade, and then performs multiple unilateral grinding on the tenon, then removes the turbine blade and fixes it again with another fixture, and then performs multiple unilateral grinding on the blade crown, not only manual reversing alignment The error affects the machining accuracy, and it is necessary to turn the turbine blade continuously when actually machining the surface of different parts of the tenon or blade crown. The whole machining process is cumbersome and time-consuming, which increases the labor intensity of the operator.

[0004] Especially when processing super large gas turbine blades for aviation or marine use, due to the large volume and high weight of super large gas turbine blades, and the related equipment is backward and there are process bottlenecks, the above processing method is used to process the end of turbine blades The implementation is more difficult, and the blade may be shifted, under-processed or over-processed during processing, which cannot meet the later assembly requirements and lead to material scrap

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