CN105414889A - Machining and edge-removing method for holes of rotor alloy disc assembly - Google Patents

Machining and edge-removing method for holes of rotor alloy disc assembly Download PDF

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Publication number
CN105414889A
CN105414889A CN201510817680.0A CN201510817680A CN105414889A CN 105414889 A CN105414889 A CN 105414889A CN 201510817680 A CN201510817680 A CN 201510817680A CN 105414889 A CN105414889 A CN 105414889A
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China
Prior art keywords
hole
bolt hole
holes
reaming
rib degree
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CN201510817680.0A
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Chinese (zh)
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CN105414889B (en
Inventor
李希顺
孙延亮
孙文岩
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AECC Shenyang Liming Aero Engine Co Ltd
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Shenyang Liming Aero Engine Group Co Ltd
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00Restoring or reconditioning objects

Abstract

The invention provides a machining and edge-removing method for holes of a rotor alloy disc assembly, and belongs to the technical field of engine repairing. The location degree of bolt holes of a single disc is corrected, with bolt holes of an original rotor disc as reference, each hole is positioned, a tension bolt hole of a replacing part is machined to phi 10 from phi 9.5, and each bolt hole is concentric with the corresponding bolt hole of the original rotor disc; a rough machining reamer and a finishing reamer are used for expanding the tension bolt holes of the replacing part to enable the diameter of each tension bolt hole to be 0.2 mm smaller than that of the corresponding bolt hole of the original rotor disc; the replacing part and matched parts at the two adjacent sides are combined and assembled, and each hole is positioned through a drill plate, namely the spaced bolt holes are positioned through core bars; the tension bolt holes of the replacing part are machined to be identical with the bolt holes of the original rotor disc in diameter, combined parts are assembled through the positioning core bars, and the holes are reamed in a combined mode; and after combination and assembly, tension bolts are mounted in the spaced bolt holes, and an edge removing process is carried out on the other half of the bolt holes. By means of the method, the location degree and the size precision of the combined machined holes are improved, and powerful guarantee is provided for engine repairing.

Description

A kind of method that processing of rotor alloy disc component holes and rib degree are got rid of
Technical field
The invention belongs to technical field of engine overhaul, particularly relate to a kind of processing of rotor alloy disc component holes and the method for rib degree eliminating.
Background technology
High-pressure compressor rotor is engine operation essential core parts, when engine is overhauled, because part replacement is powder alloy material and assembling unit structure impact thereof, causes high-pressure compressor rotor to combine in fraising and occurs some novel technical problems.Wherein turnbuckle hole rib degree fault is run into one novel technical barrier during high-pressure compressor rotor is repaired, mainly due to high-pressure compressor rotor turnbuckle hole original tape or add that work is improper causes turnbuckle hole rib degree and axiality difference problem.After being replaced by powder alloy material, combination fraising, on the basis of original process, improves the cutter material adding work.But due to the impact of high-pressure compressor rotor architectural characteristic, change cutter material and cannot get rid of turnbuckle hole rib degree and axiality difference problem in high-pressure compressor rotor combination fraising repairing.Therefore, linguistic term is carried out on the basis of original repairing technology, solve further high-pressure compressor rotor because of the combination fraising changed new material and cause and add the new technique difficult problem that work produces.
Summary of the invention
For the technical problem of above-mentioned existence, get rid of new material high-pressure compressor rotor combination fraising and repair the turnbuckle hole rib degree problem produced in front or repair procedures, the invention provides a kind of method that processing of rotor alloy disc component holes and rib degree are got rid of, add technical requirement after work to ensure that the aperture axiality of turnbuckle hole aperture size and dish at different levels meets.Improve high-pressure compressor rotor assembling repair quality better, improve the security of engine use, reliability.
The object of the invention is to be achieved through the following technical solutions:
The processing of a kind of rotor alloy disc of the present invention component holes and rib degree method for removing, comprise the steps:
(1) single-deck bolt hole position degree is corrected:
On radial drilling machine, the application part combination that to match with former rotor disk assembles, be as the criterion with former rotor disk bolt hole, located by location thimble one hole one on radial drilling machine, adopt φ 10 milling cutter that the turnbuckle hole of renewal part is machined to φ 10 from φ 9.5, concentric with the aperture of former rotor disk bolt hole;
(2) single-deck bolt hole reaming:
Adopt Roughing and fine machining reamer respectively by the turnbuckle hole reaming of renewal part to the 0.2mm being less than former rotor disk diameter of bolt hole;
(3) reaming fine finishining is combined:
The part combination assembling that renewal part and adjacent both sides are matched, located by bushing plate one hole one, namely spacer bolt hole is located by plug; Adopt Roughing and fine machining reamer by the turnbuckle hole machined of renewal part to identical with former rotor disk bolt hole aperture, and ensure alignment;
(4) adopt location mandril to be assembled by sub-assembly, then adopt Roughing and fine machining reamer to carry out combination fraising;
(5) after combination assembling, install turnbuckle in spacer bolt hole, second half bolt hole carries out the step eliminating rib degree technique.
Further, when the rib degree that described elimination rib degree technique occurs in rotor disk aperture rib degree or reaming procedure or axiality difference, adopt the grouping of sped structure reaming knife to get rid of aperture rib degree, adopt Roughing and fine machining reamer to carry out fine finishining after getting rid of rib degree again and ensure aperture size.
Further, described sped structure reaming knife one end is helicitic texture, and the other end is and bushing plate fit structure, and helicitic texture external diameter is identical with aperture to be processed, and the polished rod diameter of middle part connecting thread end is less than major diameter of thread.
Further, described sped structure reaming knife helicitic texture skin is provided with TiAlN coating.Beneficial effect of the present invention is:
1. the present invention is by improving technique method, and improves combination reaming knife structure, effectively gets rid of combination fraising rib degree fault, and improves Combined machining hole location and dimensional accuracy.Improve assembling and the work quality of engine high-pressure compressor rotor.Thus improve the reliability of engine use, can the technical fields such as engine overhaul be widely used in.
2. the present invention efficiently solves the repair work of multiple stage engine high-pressure compressor rotor rib degree fault, and further increases high-pressure compressor rotor combination fraising precision, and determines rib degree fault repair method, and the repairing for engine provides favourable guarantee.
3. the present invention's application solves in engine overhaul, and the new technique difficult problem run into, improves engine high-pressure compressor rotor and similar parts service technique level thereof further.Successfully eliminated the high-pressure compressor rotor of original tape rib degree fault in multiple stage turnbuckle hole in engine overhaul process by the new-type cutter of Improvement process and development, for engine overhaul provides favourable technical guarantee, and save a large amount of repair cost.
Accompanying drawing explanation
Fig. 1 is the high pressure rotor partial structurtes schematic diagram that the present invention need change.
Fig. 2 (a) (b) is high pressure rotor combination assembling and single-deck bolt hole position degree bearing calibration schematic diagram.
Fig. 3 is combination reaming schematic diagram.
Fig. 4 is rotor assembling plug location schematic diagram.
Fig. 5 is sped structure reaming knife schematic diagram.
In figure: I. fraising position, II. working position, 1. plug, 2. bushing plate, 3. renewal part, 4. former rotor disk, 5. helicitic texture, 6. polished rod, 7. locate thimble.
Detailed description of the invention
Describe the present invention below in conjunction with drawings and Examples.
Embodiment: as Figure 1-Figure 5, the processing of a kind of rotor alloy disc of the present invention component holes and rib degree method for removing, comprise the steps:
(1) single-deck bolt hole position degree is corrected, as shown in Fig. 2 (a):
On radial drilling machine, the application part combination that to match with former rotor disk assembles, be as the criterion with former rotor disk bolt hole, located by location thimble 7 one hole one on radial drilling machine, adopt φ 10 milling cutter that the turnbuckle hole of renewal part is machined to φ 10 from φ 9.5, concentric with the aperture of former rotor disk bolt hole;
(2) single-deck bolt hole reaming:
Adopt Roughing and fine machining reamer respectively by the turnbuckle hole reaming of renewal part to the 0.2mm being less than former rotor disk diameter of bolt hole;
(3) reaming fine finishining is combined:
As shown in Fig. 2 (b), the part combination assembling that renewal part and adjacent both sides are matched, located by bushing plate one hole one, namely spacer bolt hole is located by plug, described plug is ladder plug, external diameter respectively with former rotor disk and renewal part apertures; As shown in Figure 3, adopt Roughing and fine machining reamer by the turnbuckle hole machined of renewal part to identical with former rotor disk bolt hole aperture, and ensure alignment;
(4) adopt location mandril to be assembled by sub-assembly, then adopt Roughing and fine machining reamer to carry out combination fraising, as shown in Figure 3, Figure 4;
(5) after combination assembling, install turnbuckle in spacer bolt hole, second half bolt hole carries out the step eliminating rib degree technique.
When the rib degree that described elimination rib degree technique occurs in rotor disk aperture rib degree or reaming procedure or axiality difference, adopt the grouping of sped structure reaming knife to get rid of aperture rib degree, adopt Roughing and fine machining reamer to carry out fine finishining after getting rid of rib degree again and ensure aperture size.
As shown in Figure 5, described sped structure reaming knife one end is helicitic texture, and the other end is and bushing plate fit structure, and helicitic texture external diameter is identical with aperture to be processed, and the polished rod diameter of middle part connecting thread end is less than major diameter of thread.Described sped structure reaming knife helicitic texture skin is provided with TiAlN (TiAlNi) coating.

Claims (4)

1. the processing of rotor alloy disc component holes and a rib degree method for removing, is characterized in that: comprise the steps:
(1) single-deck bolt hole position degree is corrected:
On radial drilling machine, the application part combination that to match with former rotor disk assembles, be as the criterion with former rotor disk bolt hole, located by location thimble one hole one on radial drilling machine, adopt φ 10 milling cutter that the turnbuckle hole of renewal part is machined to φ 10 from φ 9.5, concentric with the aperture of former rotor disk bolt hole;
(2) single-deck bolt hole reaming:
Adopt Roughing and fine machining reamer respectively by the turnbuckle hole reaming of renewal part to the 0.2mm being less than former rotor disk diameter of bolt hole;
(3) reaming fine finishining is combined:
The part combination assembling that renewal part and adjacent both sides are matched, located by bushing plate one hole one, namely spacer bolt hole is located by plug; Adopt Roughing and fine machining reamer by the turnbuckle hole machined of renewal part to identical with former rotor disk bolt hole aperture, and ensure alignment;
(4) adopt location mandril to be assembled by sub-assembly, then adopt Roughing and fine machining reamer to carry out combination fraising;
(5) after combination assembling, install turnbuckle in spacer bolt hole, second half bolt hole carries out the step eliminating rib degree technique.
2. the method got rid of of the processing of rotor alloy disc component holes and rib degree according to claim 1, it is characterized in that: when the rib degree that described elimination rib degree technique occurs in rotor disk aperture rib degree or reaming procedure or axiality difference, adopt the grouping of sped structure reaming knife to get rid of aperture rib degree, adopt Roughing and fine machining reamer to carry out fine finishining after getting rid of rib degree again and ensure aperture size.
3. the method got rid of of the processing of rotor alloy disc component holes and rib degree according to claim 1, it is characterized in that: described sped structure reaming knife one end is helicitic texture, the other end is and bushing plate fit structure, helicitic texture external diameter is identical with aperture to be processed, and the polished rod diameter of middle part connecting thread end is less than major diameter of thread.
4. the method got rid of of the processing of rotor alloy disc component holes and rib degree according to claim 1, is characterized in that: described sped structure reaming knife helicitic texture skin is provided with TiAlN coating.
CN201510817680.0A 2015-11-23 2015-11-23 The method that a kind of processing of rotor alloy disc component holes and rib degree exclude Active CN105414889B (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106825654A (en) * 2016-11-25 2017-06-13 沈阳黎明航空发动机(集团)有限责任公司 A kind of rotor stack is changed and mends processing method
CN112476090A (en) * 2020-10-22 2021-03-12 山东道普安制动材料有限公司 Method for machining bolt holes of carbon-ceramic brake disc

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CN101733479A (en) * 2009-12-04 2010-06-16 沈阳黎明航空发动机(集团)有限责任公司 Single-disk reaming method of high-pressure rotor labyrinth disk
CN102501046A (en) * 2011-10-21 2012-06-20 哈尔滨汽轮机厂有限责任公司 Machining method of step end face balance hole
CN103272949A (en) * 2013-06-14 2013-09-04 沈阳飞机工业(集团)有限公司 Machining method for female die with stepped holes
CN103551855A (en) * 2013-11-14 2014-02-05 上海中船三井造船柴油机有限公司 Method and device for simultaneous drilling and reaming processing of crankshaft and flywheel of marine low-speed diesel engine

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Publication number Priority date Publication date Assignee Title
CN101733479A (en) * 2009-12-04 2010-06-16 沈阳黎明航空发动机(集团)有限责任公司 Single-disk reaming method of high-pressure rotor labyrinth disk
CN102501046A (en) * 2011-10-21 2012-06-20 哈尔滨汽轮机厂有限责任公司 Machining method of step end face balance hole
CN103272949A (en) * 2013-06-14 2013-09-04 沈阳飞机工业(集团)有限公司 Machining method for female die with stepped holes
CN103551855A (en) * 2013-11-14 2014-02-05 上海中船三井造船柴油机有限公司 Method and device for simultaneous drilling and reaming processing of crankshaft and flywheel of marine low-speed diesel engine

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106825654A (en) * 2016-11-25 2017-06-13 沈阳黎明航空发动机(集团)有限责任公司 A kind of rotor stack is changed and mends processing method
CN106825654B (en) * 2016-11-25 2019-07-05 中国航发沈阳黎明航空发动机有限责任公司 A kind of rotor stack replacement benefit processing method
CN112476090A (en) * 2020-10-22 2021-03-12 山东道普安制动材料有限公司 Method for machining bolt holes of carbon-ceramic brake disc

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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company

Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City