CN106736332A - A kind of High Pressure Turbine Rotor combination is with the numerical-control processing method for boring tapered hole - Google Patents
A kind of High Pressure Turbine Rotor combination is with the numerical-control processing method for boring tapered hole Download PDFInfo
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- CN106736332A CN106736332A CN201611209154.7A CN201611209154A CN106736332A CN 106736332 A CN106736332 A CN 106736332A CN 201611209154 A CN201611209154 A CN 201611209154A CN 106736332 A CN106736332 A CN 106736332A
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- Prior art keywords
- tapered hole
- taper
- hole
- roughing
- pressure turbine
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P17/00—Metal-working operations, not covered by a single other subclass or another group in this subclass
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- Mechanical Engineering (AREA)
- Milling Processes (AREA)
Abstract
The invention discloses a kind of High Pressure Turbine Rotor combination with bore tapered hole numerical-control processing method, including tapered hole roughing, finishing and coloring apolegamy taper bolt.The present invention is by controlling roughing surplus, the abrasion change in process of taper bottoming reamer is followed the trail of, ensure that combination, with part is bored in the matching requirements of each part of process, the taper and each sectional dimension of the tapered hole is ensured by controlling the overall process of whole taper hole machined.
Description
Technical field
The invention belongs to Computerized Numerical Control processing technology field, particularly processing method of the combination with tapered hole is bored.
Background technology
Combination is actually rare in field of machining with burr-drill degree hole machined, especially the deep taper after 3 component assemblies
Hole processes with boring, and 3 part material situations are inconsistent, and under conditions of hole machined precision is also high, difficulty of processing is very big.
In the manufacture of aero-engine part, just there is this processing needs, and the precision of the tapered hole processed with conventional method is not high,
Vibration fault that is bad with the cooperation of taper bolt and causing engine.At present, it is domestic also inaccurate on high hardness material
The deep systematic research of tapered hole processing method and elaboration.
As shown in figure 1, certain engine components is made up of 3 parts, wherein part 1 is labyrinth of obturaging, and part 2 is high pressure whirlpool
Wheel disc, part 3 is high-pressure turbine rear shaft neck, and three materials of part are the different high temperature alloy of the trade mark；After 4 match somebody with somebody brill for combination
Tapered hole, the hole taper is 1: 50, and depth is 61mm.Wherein, part 1, part 2, part 3 are exactly by 8 cones in assembling process
Degree hole 4 connects and feels relieved, and as seen from Figure 1, when reamer is processed from top to down, the stroke that cutter forward part is passed by is most
Greatly, abrasion most serious.
Based on above-mentioned process requirements and there is problem, by analyzing the design feature and processing difficulties of part, from part dress
The control of folder, cutter, processing method, detection method and process is set about, and puts forth effort to solve the technical barrier, so as to solve this
The technical bottleneck herein that h type engine h development process runs into.
The content of the invention
The technical problem to be solved in the present invention is：A kind of High Pressure Turbine Rotor combination is provided with the digital control processing for boring tapered hole
Method, it is reliable and stable, solve the problems, such as that combination is not high with burr-drill degree hole precision.
The present invention is realized by following scheme：
A kind of High Pressure Turbine Rotor combination is comprised the following steps with the numerical-control processing method for boring tapered hole：
1., clamping parts, the inner circle and end face run-out of inspection part 1 should meet technological requirement to step；
Step 2., roughing tapered hole：Roughing is carried out with 1: 50 taper profile milling cutter, by controlling knife depth under Z axis
To control the surplus in each section of tapered hole, roughing is completed when each section surplus is less than or equal to 0.1mm；
3. step, finishes tapered hole：Finished with 1: 50 shaping taper reamer, Z axis knife depth under roughing
On descend 2mm to measure the absolute value of the residual difference of maximum cross-section and smallest cross-sectional again, when absolute value is more than 0.015mm, change one
3. 1: 50 new shaping taper reamer is carried out above step again；When absolute value is less than 0.015mm, continue to process；
4. step, completes taper hole machined：Step is iterated through 3. to the control of cutter taper in process, Zhi Daosuo
Untill having the size qualification in section；
5. step, matches mounting process taper bolt：After first tapered hole is machined, bored by colouring apolegamy technique
Degree bolt is installed in the tapered hole, and stained area is not less than 60%；
6. step, bores the relative another tapered hole of first tapered hole：Repeat step 3.~5., complete the tapered hole and add
Work；
7. step, bores remaining tapered hole：Repeat step 2.~4., complete the processing of remaining tapered hole.
The step 2. in, milling cutter is whole hard alloy；800 revs/min of speed of mainshaft during processing, feed for 20 millimeters/
Point.
The step 3. in, shaping taper reamer be whole hard alloy；600 revs/min of speed of mainshaft during processing, feed and are
10 millis m/min.
The places different from other tapered holes are processed are that present invention combination uses feedback machine with the numerical control method for boring tapered hole
Reason control effectively to process, efficiently solves the tool wear caused by material trademark difference in process
Inconsistence problems, so as to ensure the taper of tapered hole by controlling shaping taper reamer taper；Matched by this color inspection and bored
There is relative play in process between part to eliminate in degree bolt.
Compared with prior art, existing process technology is for allowance without effectively control, and the present invention is 2. right by step
Roughing surplus is strictly controlled, the degree of wear of 3 parts for cutter when reducing finishing, it is ensured that knife in process
The taper excursion of tool is controllable without causing the overproof of product；Existing process technology is for shaping taper bottoming reamer processed
Cause taper situation of change without tracking because of abrasion in journey, 3., 4. step has then been carried out entirely to the taper for being molded taper bottoming reamer
Process tracking, it is to avoid because shaping taper bottoming reamer produces different effects because 3 part materials are not exclusively the same for tool wear
The taper of the forming cutter cutter is really influenceed, indirect control has lived the taper and sectional dimension of tapered hole.Existing process technology pair
Installation taper bolt non-coloring apolegamy after hole is drilled is required, it is impossible to ensure that play does not occur between 3 parts, step is 5. right
It is distinctly claimed in taper bolt coloring proposition, meets the assembling positioning requirements between part, will not between part so as to ensure that
There is the play of relative position.Improved more than, the present invention controls roughing surplus, followed the trail of taper bottoming reamer in processing
During abrasion change, combination is ensure that with matching requirements of the part in each part of process are bored, by the whole cone of control
The overall process of hole machined is spent to ensure the taper and each sectional dimension of the tapered hole.
Brief description of the drawings
Fig. 1 is engine high pressure turbine rotor assembling schematic diagram；
Fig. 2 is engine high pressure turbine rotor work flow and feedback mechanism figure.
Specific embodiment
The present invention is described in further details below in conjunction with the accompanying drawings：
As shown in figure 1, the engine high pressure turbine rotor is made up of 3 parts, wherein part 1 is obturage labyrinth, part 2
It is high-pressure turbine disk, part 3 is high-pressure turbine rear shaft neck, and three materials of part are the different high temperature alloy of the trade mark；4 is combination
With the tapered hole after brill, the hole taper is 1: 50, and depth is 61mm, and part 1, part 2 and part 3 are exactly wherein in assembling process
Connected by 8 tapered holes 4 and felt relieved, as seen from Figure 1, when reamer is processed from top to down, cutter forward part is passed by
Stroke it is maximum, most serious of wearing and tearing, in order to solve the problem, need to be tracked to the degree of wear during tool sharpening, this
Invention establishes feedback mechanism, controls process；Feedback mechanism is as shown in Figure 2.
For the part in Fig. 1, the present invention is processed that (following Z axis refer to tapered hole depth direction using following methods
Or reamer direction of feed)：
(1) clamping parts：Technological procedure concerned process steps requirement clamping parts and each bounce of inspection by High Pressure Turbine Rotor
Should be qualified, that is, check that the obturage inner circle and end face run-out of labyrinth of part 1 should meet technological requirement, mainly control taper hole position
Degree of putting and perpendicularity.
(2) roughing tapered hole：Roughing is carried out with 1: 50 taper milling cutter, material of cutting-tool is whole hard alloy；Processing
When 800 revs/min of the speed of mainshaft, feed be 20 milli m/min, this machined parameters be conducive to reduce relieving amount；By controlling Z during processing
Knife depth controls the surplus in each section of tapered hole under axle, when each section surplus is less than or equal to 0.1mm roughing
Complete.
(3) tapered hole is finished：Finished with 1: 50 shaping taper reamer, shaping taper reamer is that overall hard is closed
Gold；600 revs/min of speed of mainshaft during processing, it is 10 millis m/min to feed, and this machined parameters is conducive to control hole surface roughness；Plus
Man-hour, Z axis descend 2mm to measure the absolute value of maximum cross-section and the residual difference of smallest cross-sectional again in knife depth under roughing, when exhausted
During to value more than 0.015mm, illustrate that the forming cutter taper is unqualified, now, it should change a new forming cutter and enter again
Row above step (3)；If absolute value is less than 0.015mm, illustrate that the forming cutter cutter taper is qualified, processing can be continued.Z axis
Lower 2mm refers to descend 2mm again in knife depth under roughing Z axis, is not the 2mm under section.This is the with feedback mechanism
One step, roughing has completed the every lower 1mm of Z axis, and aperture can become the big balance of 0.1mm in 0.02mm apertures, under Z axis after 2mm, aperture
Surplus only remains 0.06mm, therefore 2mm is more reasonable under Z axis.It is not more than 0.015mm on absolute value, 0.015mm exactly apertures
Tolerance.
(4) taper hole machined is completed：Control of the step (3) to cutter taper in process is iterated through, until all
Untill the size qualification in section.
(5) mounting process taper bolt is matched：After first tapered hole is machined, by colouring apolegamy technological coning spiral shell
Bolt is installed in the tapered hole, and stained area is not less than 60%, by installing first taper bolt in hole, prevents processing follow-up
There is relative play during hole between 3 parts.Taper bolt refers mainly to interference or gap with the degree of cooperation of tapered hole, this
The contact area of taper bolt and tapered hole is primarily referred to as in invention.
(6) whether the relative another hole of first tapered hole (here refer to relatively on a diameter line) is bored：Weight
Multiple step (2)~(5), complete the hole machined.
(7) remaining 6 tapered holes (random selection drilling sequences) are bored：Repeat step (2)~(4), complete remaining 7 cones
Spend the processing in hole.
(8) process finishing, unloads part and fixture.
As shown in Fig. 2 being High Pressure Turbine Rotor work flow and feedback mechanism figure, it can be seen that above-mentioned processing method is main
Feature is the introduction of feedback mechanism, wherein cause that allowance more rationalizes for the control of roughing surplus, so as to reduce
For the abrasion of molding cutter in finishing passes；In finishing passes, shaping taper is known by the detection to surplus
Bottoming reamer abrasion condition in process, adjusts in time according to abrasion condition, it is ensured that at maximum diameter of hole and minimum-value aperture
Surplus difference absolute value in the margin of tolerance, controlled by controlling the aperture at maximum diameter of hole and at minimum-value aperture whole
The taper in hole.
Claims (3)
1. a kind of High Pressure Turbine Rotor combination is with the numerical-control processing method for boring tapered hole, it is characterised in that comprise the following steps：
1., clamping parts, the inner circle and end face run-out of inspection part 1 should meet technological requirement to step；
Step 2., roughing tapered hole：Roughing is carried out with 1: 50 taper profile milling cutter, is controlled by controlling under Z axis knife depth
The surplus in each section of tapered hole processed, roughing is completed when each section surplus is less than or equal to 0.1mm；
3. step, finishes tapered hole：With 1: 50 shaping taper reamer finished, Z axis in knife depth under roughing again
Lower 2mm measurement maximum cross-sections and the absolute value of the residual difference of smallest cross-sectional, when absolute value is more than 0.015mm, change one new
1: 50 shaping taper reamer carry out above step 3. again；When absolute value is less than 0.015mm, continue to process；
4. step, completes taper hole machined：Step is iterated through 3. to the control of cutter taper in process, until all sections
Untill the size qualification in face；
5. step, matches mounting process taper bolt：After first tapered hole is machined, by colouring apolegamy technological coning spiral shell
Bolt is installed in the tapered hole, and stained area is not less than 60%；
6. step, bores the relative another tapered hole of first tapered hole：Repeat step 3.~5., complete the taper hole machined；
7. step, bores remaining tapered hole：Repeat step 2.~4., complete the processing of remaining tapered hole.
2. a kind of High Pressure Turbine Rotor combination according to claim 1 is with the numerical-control processing method for boring tapered hole, its feature
It is：The step 2. in, milling cutter is whole hard alloy；800 revs/min of speed of mainshaft during processing, it is 20 millis m/min to feed.
3. a kind of High Pressure Turbine Rotor combination according to claim 1 is with the numerical-control processing method for boring tapered hole, its feature
It is：The step 3. in, shaping taper reamer be whole hard alloy；600 revs/min of speed of mainshaft during processing, it is 10 to feed
Milli m/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611209154.7A CN106736332B (en) | 2016-12-23 | 2016-12-23 | A kind of numerical-control processing method of the High Pressure Turbine Rotor combination with brill tapered hole |
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|---|---|---|---|
| CN201611209154.7A CN106736332B (en) | 2016-12-23 | 2016-12-23 | A kind of numerical-control processing method of the High Pressure Turbine Rotor combination with brill tapered hole |
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| CN106736332A true CN106736332A (en) | 2017-05-31 |
| CN106736332B CN106736332B (en) | 2018-11-27 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108057997A (en) * | 2017-12-21 | 2018-05-22 | 重庆航天职业技术学院 | A kind of extension box side turbine hole forming method of minicar gearbox |
| CN109268473A (en) * | 2018-11-26 | 2019-01-25 | 中国航发南方工业有限公司 | The method for processing and assembling of dish axle connection structure and dish axle connection structure |
| CN111331446A (en) * | 2020-03-20 | 2020-06-26 | 中国航发哈尔滨东安发动机有限公司 | Method for controlling grinding deformation of outer diameter of guide cylinder of automatic inclinator of helicopter |
| CN114893253A (en) * | 2022-04-08 | 2022-08-12 | 中国航发沈阳发动机研究所 | Reliable rotor connecting structure and method for high-temperature component |
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| CN101799354A (en) * | 2010-02-09 | 2010-08-11 | 西安交通大学 | Method for testing assembly performance of rotor of aircraft engine |
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| US8197162B2 (en) * | 2006-12-19 | 2012-06-12 | Airbus Operations Limited | Method and system for making holes in composite materials |
| CN101799354A (en) * | 2010-02-09 | 2010-08-11 | 西安交通大学 | Method for testing assembly performance of rotor of aircraft engine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108057997A (en) * | 2017-12-21 | 2018-05-22 | 重庆航天职业技术学院 | A kind of extension box side turbine hole forming method of minicar gearbox |
| CN108057997B (en) * | 2017-12-21 | 2019-09-20 | 重庆航天职业技术学院 | A kind of extension box side turbine hole forming method of minicar gearbox |
| CN109268473A (en) * | 2018-11-26 | 2019-01-25 | 中国航发南方工业有限公司 | The method for processing and assembling of dish axle connection structure and dish axle connection structure |
| CN111331446A (en) * | 2020-03-20 | 2020-06-26 | 中国航发哈尔滨东安发动机有限公司 | Method for controlling grinding deformation of outer diameter of guide cylinder of automatic inclinator of helicopter |
| CN114893253A (en) * | 2022-04-08 | 2022-08-12 | 中国航发沈阳发动机研究所 | Reliable rotor connecting structure and method for high-temperature component |
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| CN106736332B (en) | 2018-11-27 |
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Address after: 550014 No. 1111 Liyang Road, Baiyun District, Guiyang City, Guizhou Province Patentee after: Chinese Hangfa Guizhou Liyang aero Power Co. Ltd. Address before: 561102 Baiyun Town, Pingba County, Anshun City, Guizhou Province Patentee before: Guizhou Liyang Aerospace Power Co., Ltd. |
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