CN113857498B - Processing method of aero-engine high-pressure compressor disk - Google Patents
Processing method of aero-engine high-pressure compressor disk Download PDFInfo
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- CN113857498B CN113857498B CN202111247325.6A CN202111247325A CN113857498B CN 113857498 B CN113857498 B CN 113857498B CN 202111247325 A CN202111247325 A CN 202111247325A CN 113857498 B CN113857498 B CN 113857498B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B1/00—Methods for turning or working essentially requiring the use of turning-machines; Use of auxiliary equipment in connection with such methods
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B5/00—Turning-machines or devices specially adapted for particular work; Accessories specially adapted therefor
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Abstract
The invention relates to the field of compressor disc machining, in particular to a machining method of a high-pressure compressor disc of an aero-engine. The invention provides the following technical scheme: a processing method of a high-pressure compressor disk of an aeroengine is characterized by carrying out finish turning and processing, comprising the following steps: 1) A step of turning a reference surface; 2) Finely turning an outer circle; 3) Finely turning the inner cavity of the first surface; 4) Finely turning the inner cavity of the second surface. The invention can improve the processing quality and the processing efficiency of parts and shorten the production period.
Description
Technical Field
The invention relates to the field of compressor disc machining, in particular to a machining method of a high-pressure compressor disc of an aero-engine.
Background
The high-pressure compressor disks of aeroengines are always processed according to the traditional process route: turning reference, grinding reference, washing, finish turning the second outer molded surface, grinding reference, washing, finish turning the matching surface, grinding reference, washing, finish turning the first surface inner cavity, finish turning the second surface inner cavity, finish turning the outer diameter and turning the welding seam allowance. In order to ensure that the reference surfaces on two sides of the compressor disk meet the qualification requirement, the machining is carried out by three times of clamping, and in order to ensure the flatness requirement of each machining, the grinding and cleaning procedures are added. The 10 processes are only turning reference, and the finish turning outer diameter and turning welding seam allowance processes are needed to finish the machining of all parts. Therefore, the machining of the parts of the compressor disk is completed by 12 working procedures. And each procedure has a special fixture, and multiple complicated steps such as hoisting parts, clamping parts, aligning parts, compacting parts and the like are needed, so that a great deal of time and labor are wasted. The two reference surfaces of the compressor disk are processed in different working procedures, and the working steps of processing in each working procedure are rough turning, half finish turning, and finish turning. Thus, after the first surface standard is finished in finish turning, the second surface standard also needs to be subjected to rough turning for removing the allowance, semi-finish turning for removing the allowance and finish turning once. This causes a certain processing stress to the part, which causes a slight deformation of the part. Because of the specificity of the part structure, the reference surface and the pressing surface force acting point are not on the same straight line, so that a certain torque force can be generated, and the torque force can lead to the increase of the stable range of the part machining precision. The traditional process route cannot guarantee the quality qualification rate of the parts and cannot meet the goal of shortening the production period of the parts.
Disclosure of Invention
The invention aims to provide a processing method of a high-pressure compressor disk of an aero-engine, which realizes the improvement of the processing quality and the processing efficiency of parts and shortens the production period.
In order to achieve the above object, the present invention provides the following technical solutions:
a processing method of a high-pressure compressor disk of an aeroengine is characterized by carrying out finish turning and processing, comprising the following steps:
1) A step of turning a reference surface;
the first surface is used as a positioning reference surface, the second surface is pressed tightly, and a hub hole of the first surface are machined; the first surface hub and the hub hole provide positioning reference surfaces for the process of finish turning the outer circle;
2) Finely turning an outer circle;
the first surface hub and the hub hole are used as positioning reference surfaces, the second surface hub is pressed, and the first surface, the second surface, the third surface, the fourth surface, the fifth surface, the sixth surface, the seventh surface and the eighth surface are finish-machined; the eighth surface is used as a positioning reference surface for finely turning the inner cavity of the first surface;
3) Finely turning the inner cavity of the first surface;
pressing the sixth surface by taking the fifth surface and the eighth surface as positioning reference surfaces, and finish turning the first surface radial plate and the first surface hub;
4) Finely turning the inner cavity of the second surface;
and pressing the eighth surface by taking the fifth surface and the sixth surface as positioning reference surfaces, and finish turning the second surface web and the second surface hub.
Further, in the process 2) of finish turning the outer circle, finish turning of the first surface and the seventh surface is completed after one clamping, and the parallelism requirements of the first surface and the seventh surface are guaranteed.
Further, in the step 2) of finish turning the outer circle, the first surface is used as a front reference surface, the seventh surface is used as a rear reference surface, and the machining steps are sequentially front reference surface rough machining, rear reference surface rough machining, front reference surface semi-finishing, rear reference surface semi-finishing, front reference surface finishing and rear reference surface finishing, so that the parallelism requirements of the first surface and the seventh surface are met, and the circumferential wall thickness difference between the first surface web and the second surface web and the circumferential wall thickness difference between the first surface hub and the second surface hub are ensured.
The technical scheme of the invention has the following technical effects:
(1) According to the invention, through optimization and improvement of the process route and improvement of the clamping and positioning mode of the finish turning reference surface, the processing quality and processing efficiency of the high-pressure compressor disk part of the aeroengine can be improved, and the production cycle of the part can be shortened.
(2) The parallelism of the first surface and the seventh surface is smaller than 0.02mm, and the first surface and the seventh surface are alternately finish-machined, so that the relative stress generated by the parts is minimized, and the deformation of the parts in the process of turning the reference surface is avoided.
(3) A process reference table, namely an eighth surface, is machined on the outer circle structure of the high-pressure compressor disc and is used as a clamping and positioning surface of the fine turning first inner cavity, torque force generated by the fact that the reference surface and the pressing surface force acting point are not in the same straight line when the first inner cavity is subjected to fine turning is subtracted, the stable range of the machining precision of the part is reduced, and the machining quality of the part is improved.
(4) In the improved process route, a plurality of parts of the compressor disk are combined and processed, so that the original 10 processing parts can be completed by only 1 processing step. And only 1 car reference process is required to be arranged before the process. The tool is replaced and the alignment time is reduced from 2 hours to 15 minutes, the precision of the tool can be reduced from 0.05 to within 0.01, the machining efficiency of the compressor disc is greatly improved, and all machined parts on the compressor disc are machined through one-time clamping, so that the strict technical conditions of the two sides of the disc which are not easy to guarantee originally are met, and the high-precision qualification standard is achieved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. Wherein:
FIG. 1 is a schematic view of a processing procedure of a high pressure compressor disk processing method of the present invention;
FIG. 2 is a schematic view of the processing steps of the front datum surface and the rear datum surface of the present invention;
FIG. 3 is a schematic diagram of clamping and positioning by using a rear reference surface when the front reference surface is used in the comparative example;
reference numerals illustrate: 1-a first surface; 2-a second surface; 3-a third surface; 4-a fourth surface; 5-a fifth surface; 6-a sixth surface; 7-seventh surface; 9-a first web; 10-a second web; 11-a first face hub; 12-a second face hub; 13-a hub hole; 8-eighth surface; 21-rough machining of a front reference surface; 22-rough machining of a rear reference surface; 23-semi-finishing the front datum plane; 24-semi-finishing the rear datum plane; 25-finish machining of a front datum plane; and (5) finishing the rear datum plane.
Detailed Description
The invention will be described in detail below with reference to the drawings in connection with embodiments. The examples are provided by way of explanation of the invention and not limitation of the invention. Indeed, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features illustrated or described as part of one embodiment can be used on another embodiment to yield still a further embodiment. Accordingly, it is intended that the present invention encompass such modifications and variations as fall within the scope of the appended claims and their equivalents.
In the description of the present invention, the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", etc. refer to the orientation or positional relationship based on that shown in the drawings, merely for convenience of description of the present invention and do not require that the present invention must be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. The terms "coupled," "connected," and "configured" as used herein are to be construed broadly and may be, for example, fixedly connected or detachably connected; can be directly connected or indirectly connected through an intermediate component; either a wired electrical connection, a radio connection or a wireless communication signal connection, the specific meaning of which terms will be understood by those of ordinary skill in the art as the case may be.
One or more examples of the invention are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms "first," "second," and "third," etc. are used interchangeably to distinguish one component from another and are not intended to represent the location or importance of the individual components.
As shown in fig. 1 to 2, according to an embodiment of the present invention, there is provided a finish turning method for machining a high pressure compressor disk of an aeroengine, the finish turning method including the steps of:
1) Vehicle reference surface: the first surface 1 is used as a positioning reference surface, the second surface 2 is pressed tightly, and a first surface hub 11 and a disc center hole 13 are machined; the first hub 11 and the hub hole 13 provide a positioning reference surface for the next process for the finish turning process.
2) Finely turning an outer circle: the first surface hub 11 and the hub hole 13 are used as positioning reference surfaces, the second surface hub 12 is pressed, and the first surface 1, the second surface 2, the third surface 3, the fourth surface 4, the fifth surface 5, the sixth surface 6, the seventh surface 7 and the eighth surface 8 are processed by finish turning; it should be noted that the outer circle includes a first surface 1, a second surface 2, a third surface 3, a fourth surface 4, a fifth surface 5, a sixth surface 6, a seventh surface 7, and an eighth surface 8; finish turning is finished on the first surface 1 and the seventh surface 7 after the same clamping, so that the parallelism requirements of the first surface 1 and the seventh surface 7 are ensured; the eighth surface 8 is a positioning reference surface of the inner cavity of the first surface of the finish turning; it should be noted that the first side cavity includes a first side web 9 and a first side hub 11.
The first surface 1 is used as a front reference surface, the seventh surface 7 is used as a rear reference surface, the machining steps are sequentially a front reference surface rough machining 21, a rear reference surface rough machining 22, a front reference surface semi-finishing 23, a rear reference surface semi-finishing 24, a front reference surface finishing 25 and a rear reference surface finishing 26, and the requirement that the parallelism requirement of the first surface 1 and the seventh surface 7 is smaller than 0.02mm is met, so that the circumferential wall thickness difference between the first surface web and the second surface web and the circumferential wall thickness difference between the first surface hub and the second surface hub are ensured, and the circumferential wall thickness difference between the first surface web and the second surface hub is smaller than 0.05mm.
3) Finely turning an inner cavity of a first surface: the fifth surface 5 and the eighth surface 8 are used as positioning reference surfaces, the sixth surface 6 is pressed, and a first surface inner cavity is finished, wherein the first surface inner cavity comprises a first surface radial plate 9 and a first surface hub 11.
4) Finely turning the inner cavity of the second surface: the fifth surface 5 and the sixth surface 6 are used as positioning reference surfaces, the eighth surface 8 is pressed, and a second surface inner cavity is finished, wherein the second surface inner cavity comprises a second surface web 10 and a second surface hub 12.
The zero point positioning of the part clamp is also improved, before the improvement, the positioning matching surface of the part and the clamp is in clearance fit, the maximum clearance of the fit is 0.15mm, an operator needs to align the part before processing the part, in order to ensure the high-precision size of the part, the part needs to be aligned in the optimal state, and a great amount of time is consumed in the necessary process. After improvement, a novel clamp is used, the clamp is provided with a zero flexible positioning system, a zero positioning master disc is arranged on the clamp and can be connected with a part positioning connection sub-disc, and then the sub-disc is used for clamping parts. The master disc and the sub disc have high-precision quick-change functions, and can realize quick clamping and repeated positioning with the precision of 0.005mm. And the clamping of the parts and the sub-discs can be carried out on the pre-adjusting table, so that the clamping and aligning time of the parts is greatly saved, and the precision of part processing is improved.
The process method has realized the problem of improving the processing efficiency of the compressor disk. Under the condition that the original production line of the parts is unchanged, the optimization and improvement of the process route, the improvement of the clamping and positioning of the finish turning reference surface, the control method of the finish turning reference, the improvement of the zero point positioning of the part clamp and the improvement of the clamping and positioning of the finish turning radial plate are ensured, and the purposes of high production efficiency, good application effect and good economic benefit are achieved. The process method is applied to improving the processing efficiency of the high-pressure compressor disc, shortens the production period, is applied for the first time in China, has great innovation, successfully solves the problem that the high-pressure compressor disc is processed all the time according to the traditional process route, cannot meet the requirements of improving the processing quality and the processing efficiency of the compressor disc and shortening the production period, and simultaneously improves the processing quality of parts. The process method has good effect on solving the problem of improving the processing efficiency of the compressor disk, and is convenient to operate and safe and reliable to produce. Therefore, the technical method has wide domestic market prospect.
Examples
A processing method of a high-pressure compressor disk of an aero-engine comprises the following steps:
1) A vehicle datum plane;
as shown in fig. 1-2, a disk center hole positioning mode is adopted, a disk center hole 13 of a high-pressure compressor disk and a first surface hub 11 of the high-pressure compressor disk are taken as clamping positioning surfaces, and a second surface hub 12 is pressed tightly; the machining process of the first surface 1 and the seventh surface 7 of the high-pressure compressor disc is finished through one-time clamping, and the clamping and positioning mode has low requirements on the clamping and alignment of parts and the skill level of operators, and the technical conditions such as parallelism of two reference surfaces are easy to ensure. The first surface and the seventh surface processing steps of the finish turning excircle are as follows: front datum surface rough machining 21, rear datum surface rough machining 22, front datum surface semi-finishing 23, rear datum surface semi-finishing 24, front datum surface finish machining 25 and rear datum surface finish machining 26, wherein the machining sequence enables machining stress of the part to be minimum, and deformation of the part during turning of the datum surface is avoided;
2) Finely turning a reference table of the outer circle 4;
then finely turning the first surface 1, the second surface 2, the third surface 3, the fourth surface 4, the fifth surface 5, the sixth surface 6 and the seventh surface 7 of the outer circle of the high-pressure compressor disk in place; a process reference table, namely an eighth surface 8, is processed on the excircle 4 structure of the high-pressure compressor disk and is used as a clamping and positioning surface of the finish turning inner cavity;
3) Finely turning an inner cavity;
as shown in fig. 1, an outer circle positioning mode is adopted, a fifth surface 5 and an eighth surface 8 are used as positioning reference surfaces for clamping an inner cavity of a finish turning machine, and meanwhile, a sixth surface 6 is pressed, and a first surface radial plate 9 and a first surface hub 11 of a high-pressure compressor disc are finish turned in place; the eighth surface 8 and the sixth surface 6 are on the same straight line, torque force can not be generated when clamping the part, and the stable range of the dimensional accuracy of the part during processing is reduced.
Comparative example
The traditional processing technology route of the high-pressure compressor disk comprises the following steps: turning reference, grinding reference, washing, finish turning the second outer molded surface, grinding reference, washing, finish turning the matching surface, grinding reference, washing, finish turning the first surface inner cavity, finish turning the second surface inner cavity, finish turning the outer diameter and turning the welding seam allowance.
In order to ensure that the front datum plane and the rear datum plane of the compressor disk meet the qualification requirements, as shown in fig. 3, when the first surface 1 of the front datum plane is finish machined, the seventh surface 7 of the rear datum plane is adopted for clamping and positioning; when the seventh surface 7 of the rear datum plane is finish machined, the first surface 1 of the front datum plane is adopted for positioning; the grinding and cleaning procedures are added for ensuring the flatness requirement of each machining; each procedure needs a special fixture, and a plurality of steps such as hoisting parts, clamping parts, aligning parts, compacting parts and the like are needed;
as shown in fig. 2, the front reference surface is a first surface 1 and the rear reference surface is a seventh surface 7, which are processed in different processes, and the processing steps of the first surface 1 are a front reference surface rough processing 21, a front reference surface semi-finishing 23 and a front reference surface finishing 25 in this order; after the reference of the first surface 1 has been finished, the seventh surface 7 is finished again, and the reference surfaces of the seventh surface 7 are machined in the sequence of the rear reference surface rough machining 22, the rear reference surface semi-finishing 24 and the rear reference surface finishing 25, which causes a certain machining stress to the part and a slight deformation to the part.
As shown in fig. 3, the force points of the clamping and positioning surface first surface 1 and the pressing surface sixth surface 6 are not on the same straight line, so a certain torque force is generated, and the stability range of the machining precision of the parts is enlarged due to the torque force.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (1)
1. The processing method of the aero-engine high-pressure compressor disk is characterized by comprising the following steps of:
1) A step of turning a reference surface;
the first surface is used as a positioning reference surface, the second surface is pressed tightly, and a hub hole of the first surface are machined; the first surface hub and the hub hole provide positioning reference surfaces for the process of finish turning the outer circle;
2) Finely turning an outer circle;
the first surface hub and the hub hole are used as positioning reference surfaces, the second surface hub is pressed, and the first surface, the second surface, the third surface, the fourth surface, the fifth surface, the sixth surface, the seventh surface and the eighth surface are finish-machined; the eighth surface provides a positioning reference surface for the inner cavity of the finish turning first surface; finish turning is finished on the first surface and the seventh surface after one-time clamping and positioning, so that the parallelism requirements of the first surface and the seventh surface are ensured; the first surface is used as a front reference surface, the seventh surface is used as a rear reference surface, and the processing steps comprise front reference surface rough processing, rear reference surface rough processing, front reference surface semi-finishing, rear reference surface semi-finishing, front reference surface finishing and rear reference surface finishing in sequence, so that the parallelism requirements of the first surface and the seventh surface are met, and the circumferential wall thickness difference between the first surface web and the second surface web and the circumferential wall thickness difference between the first surface hub and the second surface hub are ensured;
3) Finely turning the inner cavity of the first surface;
pressing the sixth surface by taking the fifth surface and the eighth surface as positioning reference surfaces, and finish turning the first surface radial plate and the first surface hub;
4) Finely turning the inner cavity of the second surface;
and (3) pressing the eighth surface by taking the fifth surface and the sixth surface as positioning reference surfaces, and finish turning the second surface radial plate and the second surface hub.
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| CN116984847B (en) * | 2023-09-27 | 2023-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining method for deep groove of compressor disc hub |
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| US6969312B2 (en) * | 2002-09-16 | 2005-11-29 | Derby Worx, Inc. | Hub conditioning and alignment tool |
| CN103706817B (en) * | 2013-12-13 | 2017-01-04 | 中国燃气涡轮研究院 | A kind of Novel integral multistage hub rotor unit deep cavity process tool and method thereof |
| CN105562717A (en) * | 2014-10-13 | 2016-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerical control turning method for large deep cavity structure of aircraft engine disc part |
| CN107214477A (en) * | 2017-06-12 | 2017-09-29 | 中国航发哈尔滨东安发动机有限公司 | A kind of compressor disc processing method |
| CN108340172A (en) * | 2018-02-11 | 2018-07-31 | 安徽江淮汽车集团股份有限公司 | A kind of processing technology of diesel engine piston |
| CN108655417B (en) * | 2018-05-30 | 2020-04-14 | 中国航发动力股份有限公司 | Method for turning complex thin-wall part profile by adopting quasi-symmetric layered circulation |
| CN110280782B (en) * | 2019-06-20 | 2020-09-11 | 中国航发贵州黎阳航空动力有限公司 | Machining method of thin-wall part |
| CN110340734A (en) * | 2019-06-20 | 2019-10-18 | 中国航发贵州黎阳航空动力有限公司 | Point depth measurement method and device on discoid part inclined-plane |
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