Machining method for giant tubular turbine unit rotor support

Abstract

The invention relates to the field of through-flow unit rotor machining and production, in particular to a giant through-flow unit rotor support machining method. The machining method is suitable for the machining process of the giant cross-flow unit rotor support. By adjusting the machining method and the machining sequence of all the parts of the rotor support, the purposes of improving the machining quality of the rotor support and shortening the machining period are achieved. According to the method, the strict size requirement of the giant through-flow unit rotor bracket is met, meanwhile, the machining period can be greatly shortened, and therefore the general applicability to machining of similar giant through-flow unit rotor brackets is achieved.

Description

Technical Field

[0001] The invention relates to the field of production and processing of giant tubular unit rotors, and in particular to a method for processing a giant tubular unit rotor bracket. Background Art

[0002] The tubular turbine generator is a horizontal structure. The rotor parts are affected by their own weight and bend, which affects the air gap size between the stator and rotor of the unit and directly affects the performance of the unit. The machining accuracy of the rotor parts directly affects the degree of rotor deflection and the performance of the unit.

[0003] The rotor bracket of a giant tubular unit has large dimensions. The machining dimensions of the rotor bracket vary greatly and require high precision, which places high demands on machining equipment and makes machining difficult. The conventional machining method for the rotor bracket center body requires multiple turning and realignment, which results in a long machining cycle and large alignment errors.

[0004] A large number of ventilation holes and pole-joint holes need to be processed on the yoke ring of the rotor bracket of the giant tubular unit. Due to the large thickness and special material of the yoke ring, the conventional gas cutting method for the ventilation holes is difficult to process and the processing effect is not good. There are many pole-joint holes, and the dimensional accuracy requirements are high, which makes processing difficult. Summary of the invention

[0005] The present invention aims to provide a method for machining a rotor support of a giant tubular unit on the basis of lower cost, lower machining cycle and stronger applicability, which specifically includes the following contents:

[0006] S1. The rotor bracket is machined first and then bored;

[0007] S2. The ventilation holes on the rotor bracket yoke ring are processed by boring machine instead of gas cutting;

[0008] S3, the rotor bracket adopts the sequence of "rough turning-boring-finishing turning" to process the center body of the rotor bracket;

[0009] S4. Put the rotor bracket on the boring machine, align it according to the line and the processed surface, and CNC turn the tire to process the holes on the yoke ring.

[0010] As a preferred implementation, the S1 turning-then-boring processing method is to first use a lathe to complete the overall dimensions of the rotor bracket, use the turning and boring integrated function to complete the fine processing of the rotor bracket center body, and then use a boring machine to complete the processing of all holes on the rotor bracket yoke ring.

[0011] As a preferred implementation, in S2, a yoke ventilation hole processing line is drawn on the outer circle of the rotor support yoke ring, and the yoke ventilation hole is processed by milling along the line using a boring machine.

[0012] As a preferred embodiment, in S3, when machining the rotor support center body, the spindle mating surface and the spindle engaging surface are first rough-machined, then the coupling engaging hole is bored, and then the spindle mating surface and the spindle engaging surface are fine-machined to complete the machining of the rotor support center body.

[0013] As a preferred implementation, in S4, processing lines for the engagement holes and threading holes are drawn on the yoke ring of the rotor bracket, the rotor bracket is aligned according to the drawn lines and the processed plane on a boring machine, and each hole is processed. During the processing, the CNC tire is used to drive the rotor bracket to rotate to achieve indexing.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present invention is applicable to the processing of rotor brackets of giant tubular units. By adjusting the processing sequence and processing method, auxiliary operations are reduced, processing quality is improved, and processing time is shortened. While meeting the requirements for rotor bracket processing, the present invention can greatly improve processing quality and shorten the construction period, thereby achieving universal applicability to various giant tubular unit rotor bracket processing problems. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall structure of the rotor support of the present invention;

[0017] Figure 2 It is a schematic diagram of the structure of the rotor support yoke ring of the present invention;

[0018] Figure 3 This is a schematic diagram of the central body structure of the rotor support of the present invention;

[0019] Explanation of the markings in the figure: 1- rotor bracket yoke ring, 2- rotor bracket center body, 3- yoke ventilation hole, 4- handle hole, 5- threading hole, 6- spindle mating surface, 7- spindle handle surface, 8- coupling handle hole. DETAILED DESCRIPTION

[0020] In order to make the technical solutions and beneficial effects of the present invention more clear, the technical solutions in the embodiments of the present invention are clearly and completely described below in conjunction with the accompanying drawings.

[0021] Specific implementation method 1: refer to Figures 1 to 3 The present processing method is described as follows: This processing method provides a method for processing a rotor bracket of a giant tubular unit, which specifically includes the following steps:

[0022] S1. The rotor bracket is machined first and then bored;

[0023] S2. The ventilation holes on the rotor bracket yoke ring are processed by boring machine instead of gas cutting;

[0024] S3, the rotor bracket adopts the sequence of "rough turning-boring-finishing turning" to process the center body of the rotor bracket;

[0025] S4. Put the rotor bracket on the boring machine, align it according to the line and the processed surface, and CNC turn the tire to process the holes on the yoke ring.

[0026] In this embodiment, by adjusting the overall processing method of the rotor bracket, auxiliary procedures such as workpiece transfer and turning are reduced, the processing cycle is shortened, and the impact of repeated alignment of the workpiece on the processing quality is reduced, thereby improving the processing quality, thereby achieving universal applicability for the processing of rotor brackets of giant cross-flow units.

[0027] Specific implementation method 2: refer to Figure 1 This embodiment is described, and this embodiment further limits S1 described in the specific embodiment 1. In this embodiment, the turning-before-boring processing method in S1 is to first use a lathe to complete the overall dimensions of the rotor bracket, and use the turning-boring integrated function to complete the fine processing of the rotor bracket center body 2, and then use a boring machine to complete the processing of all holes on the rotor bracket yoke ring 1.

[0028] In this embodiment, the turning-then-boring processing method only requires one turning and one transfer of the workpiece, thereby greatly reducing the time occupied by the turning and transfer work. At the same time, after turning and transferring, the processed surface is used as the processing reference, which can reduce the processing error caused by the re-alignment of the workpiece after turning and transferring.

[0029] Specific implementation method three: refer to Figure 2 This embodiment is described as further limiting S2 described in Specific Embodiment 1. In this embodiment, in S2, a processing line for the yoke ventilation hole 3 is drawn on the outer circle of the rotor support yoke ring 1, and the yoke ventilation hole 3 is milled along the line using a boring machine.

[0030] In this embodiment, the conventional processing method of the yoke ventilation hole 3 is gas cutting. Since the yoke ring 1 of the rotor support of the giant crossflow unit is made of special materials and has a large thickness, the processing cycle of the yoke ventilation hole 3 using gas cutting is long and the processing quality cannot be guaranteed. Using a boring machine processing method can ensure the processing quality of the yoke ventilation hole 3 and shorten the processing cycle.

[0031] Specific implementation method 4: refer to Figure 3 To explain this embodiment, this embodiment further limits S3 described in the specific embodiment 1. In this embodiment, when machining the rotor support center body 2, the spindle mating surface 6 and the spindle handle surface 7 are first rough-machined, and then the coupling handle hole 8 is bored, and then the spindle mating surface 6 and the spindle handle surface 7 are fine-machined to complete the machining of the rotor support center body 2.

[0032] In this embodiment, the size and shape and position tolerance of the main shaft mating surface 6 and the main shaft engaging surface 7 on the rotor support center body 2 directly affect the performance of the unit, so the size accuracy and shape and position tolerance accuracy are required to be very high. After the boring process of the coupling engaging hole 7 is completed, the fine turning process can be performed to avoid the deformation of the main shaft mating surface 6 and the main shaft engaging surface 7 caused by the processing stress generated during the boring process, thereby ensuring the processing quality of the rotor support.

[0033] Specific implementation method five: refer to Figure 2 This embodiment is described, and this embodiment further limits S4 described in the first embodiment. In this embodiment, in S4, processing lines for the engagement holes 4 and threading holes 5 are marked on the rotor bracket yoke ring 1, and the rotor bracket is aligned on the marked lines and the processed plane on a boring machine to process each hole. During the processing, the rotor bracket is driven to rotate by a CNC tire to achieve indexing.

[0034] In this embodiment, alignment according to the processed surface can reduce the alignment error, and CNC tire rotation can ensure the indexing accuracy between each group of holes, thereby ensuring the machining quality of the rotor bracket.

[0035] Finally, the protection scope of the present invention is not limited to the above-mentioned embodiments. Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the scope and spirit of the present invention. If these changes and modifications fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these changes and modifications.

Claims

1. A method for machining a rotor support of a giant tubular unit, the characteristics of which include the following contents: S1. The rotor bracket is machined first and then bored; S2. The ventilation holes on the rotor bracket yoke ring are processed by boring machine; S3. The rotor bracket adopts the sequence of "rough turning-boring-finishing turning" to process the center body of the rotor bracket; S4. Put the rotor bracket on the boring machine, align it according to the line and the processed surface, and CNC turn the tire to process the holes on the yoke ring.

2. A method for machining a rotor support of a giant tubular unit according to claim 1, characterized in that: The S1 turning-then-boring processing method is to first use a lathe to complete the overall dimensions of the rotor bracket, use the turning and boring integrated function to complete the fine processing of the rotor bracket center body, and then use a boring machine to complete the processing of all holes on the rotor bracket yoke ring.

3. The method for machining a rotor support of a giant tubular unit according to claim 1, characterized in that: In the above S2, a processing line for the yoke ventilation holes is drawn on the outer circle of the rotor support yoke ring, and the yoke ventilation holes are processed by milling along the line using a boring machine.

4. The method for machining a rotor support of a giant tubular unit according to claim 1, characterized in that: In S3, when machining the rotor support center body, the spindle mating surface and the spindle engaging surface are firstly rough-machined, then the coupling engaging hole is bored, and then the spindle mating surface and the spindle engaging surface are fine-machined to complete the machining of the rotor support center body.

5. The method for machining a rotor support of a giant tubular unit according to claim 1, characterized in that: In the above S4, processing lines for the engagement holes and threading holes are marked on the yoke ring of the rotor bracket, and the rotor bracket is aligned according to the marked lines and the processed plane on a boring machine to process each hole. During the processing, the rotor bracket is driven to rotate by a CNC tire to achieve indexing.

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