CN103586513A - Method for processing precision holes in mounting edges of airplane turbine casing - Google Patents

Method for processing precision holes in mounting edges of airplane turbine casing Download PDF

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Publication number
CN103586513A
CN103586513A CN201310560491.0A CN201310560491A CN103586513A CN 103586513 A CN103586513 A CN 103586513A CN 201310560491 A CN201310560491 A CN 201310560491A CN 103586513 A CN103586513 A CN 103586513A
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CN
China
Prior art keywords
mounting edge
precision
hole
precision hole
circle
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CN201310560491.0A
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Chinese (zh)
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CN103586513B (en
Inventor
邓春珍
周成
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中国南方航空工业(集团)有限公司
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Priority to CN201310560491.0A priority Critical patent/CN103586513B/en
Publication of CN103586513A publication Critical patent/CN103586513A/en
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Abstract

A method for processing precision holes in mounting edges of an airplane turbine casing comprises steps as follows: end faces of a first mounting edge and a second mounting edge are ground; a horizontally arranged first clamp is arranged on a numerical control milling machine, first locating pins are arranged on the first clamp, and determinate first center coordinates of centers of the first locating pins are calculated; three precision holes are roughly processed in the second mounting edge according to the first center coordinates; and the location degrees of the roughly processed precision holes are measured, the numerical control milling machine is adjusted, and the precision holes are finely processed. According to the provided method for processing the precision holes in the mounting edges of the airplane turbine casing, problems about machine tool equipment precision and clamp manufacture precision are solved.

Description

A kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge
Technical field
The present invention relates to a kind of processing method of aero-engine part, especially a kind of processing method of PRECISION HOLE of the turbine casing mounting edge for aero-engine.
Background technology
Because the casing class part of aero-engine belongs to typical thin walled welds part, generally comprise casing wall and be welded in the mounting edge at casing wall two ends, casing wall is sheet metal component, minimum wall thickness (MINI W.) is 0.8mm.
Fig. 1 is a kind of cross-sectional schematic of the turbine casing for aero-engine, because of described turbine casing wall thickness too small, therefore in Fig. 1, omit hatching, Fig. 2 is the schematic top plan view of the turbine casing shown in Fig. 1, shown in Fig. 1-2, the first mounting edge 12 and the second mounting edge 13 that described turbine casing 1 comprises a taper type casing wall 11 and is welded on respectively described casing wall 11 two ends, Fig. 3 is the perspective view of the turbine casing shown in Fig. 2, Fig. 3 is mainly for representing the overall structure of described turbine casing 1, other structures on PRECISION HOLE on described the first mounting edge 12 and described the second mounting edge 13 and described casing wall 11 in Fig. 3, have been omitted.
On the mounting edge of casing class part, all need processing precise hole, these PRECISION HOLE are for location and connecting object part.The mutual alignment degree in the hole that the self-position degree in hole and different mounting edge are corresponding requires all very high, such as position degree requires to be not more than 0.05 in free state.For the PRECISION HOLE on single mounting edge, the PRECISION HOLE on described the first mounting edge 12 for example, because of its can be on Digit Control Machine Tool once processing put in place, therefore than being easier to ensure the PRECISION HOLE self-position degree on described the first mounting edge 12.But as Figure 1-3, because described casing wall 11 is very thin, and more than the height of described turbine casing 1 can reach 300mm, therefore the PRECISION HOLE on the first mounting edge 12 is processed and is put in place, need to carry out hole to described the second mounting edge 13 and add man-hour, part very easily produces distortion.In addition the position degree due to the PRECISION HOLE to corresponding on above-mentioned different mounting edges requires very high, namely the PRECISION HOLE self-position degree on described the second mounting edge 13 with and require very high with the mutual alignment degree of corresponding PRECISION HOLE on described the first mounting edge 12, therefore jig Design, the accuracy of manufacture are required very highly, and require lathe also to there is quite high precision.
Conventional machining method must be used high-accuracy numerical control borer, needs the fixture that a set of precision is very high simultaneously, and quite high to the required precision of the locating surface of casing part own and locating hole, and the precision that relies on lathe and fixture completely guarantees part crudy.Owing to being subject to the restriction of existing machine tool accuracy and fixture machining accuracy, the operation qualification rate of existing casing part is lower, is difficult to surpass 70%.
Therefore key point of the present invention is how under existing machine tool condition, the processing method of PRECISION HOLE to be improved, thereby promotes operation qualification rate.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge, to reduce or to avoid problem noted earlier.
For solving the problems of the technologies described above, the invention provides a kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge, the first mounting edge and the second mounting edge that described turbine casing comprises a taper type casing wall and is welded on respectively described casing wall two ends, periphery along described the first mounting edge and described the second mounting edge has respectively at least three PRECISION HOLE, the PRECISION HOLE of described the first mounting edge is processed and is put in place, three PRECISION HOLE of described the first mounting edge are locating hole, and described processing method comprises the steps:
A, to described the first mounting edge and described the second mounting edge end surface grinding; The first fixture of a horizontal positioned is provided on CNC milling machine, the described locating hole of corresponding described the first mounting edge of described the first fixture is provided with three the first alignment pins, and described the first fixture is provided with for the end face laminating with described the first mounting edge first by face;
B, utilize described CNC milling machine to carry out respectively centering to three described the first alignment pins, and by described CNC milling machine, obtain respectively the centre coordinate of three described the first alignment pins, calculate the first central coordinate of circle of the determined circle in center of three described the first alignment pins;
C, described turbine casing is positioned on described the first fixture, make described the first alignment pin insert described locating hole, make described the first mounting edge end face and described first by face laminating, on described CNC milling machine, according to described the first central coordinate of circle in step B, described the second mounting edge is carried out to three described PRECISION HOLE roughing;
D, position degree to rough machined three described PRECISION HOLE in step C carries out three-dimensional coordinates measurement, if it is qualified to measure, directly rough machined three described PRECISION HOLE in step C are finish-machined to final size, if measure defective, the 3rd central coordinate of circle of the determined circle in center of the second central coordinate of circle of the determined circle in center of rough machined three described PRECISION HOLE in step C and three described locating holes is compared, according to the difference of gained, described CNC milling machine is adjusted, afterwards, rough machined three described PRECISION HOLE in step C are finish-machined to final size.
Preferably, if the periphery of described the second mounting edge has three above PRECISION HOLE, in step D, when rough machined three described PRECISION HOLE are finish-machined to final size in to step C, process other the PRECISION HOLE on described the second mounting edge.
Preferably, in steps A, utilize described CNC milling machine main shaft self to move described first Milling Process of carrying out 0.02mm by face.
The invention provides a kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge, it has overcome the impact of machine tool precision and jig Design difficulty, the accuracy of manufacture, can utilize existing machine tool to process qualified parts, operation qualification rate can reach more than 99%.
Accompanying drawing explanation
The following drawings is only intended to the present invention to schematically illustrate and explain, not delimit the scope of the invention.Wherein,
Fig. 1 is a kind of cross-sectional schematic of the turbine casing for aero-engine;
Fig. 2 is the schematic top plan view of the turbine casing shown in Fig. 1;
Fig. 3 is the perspective view of the turbine casing shown in Fig. 2;
Fig. 4 is according to the schematic top plan view of the fixture using in the processing method of the PRECISION HOLE of a kind of airplane turbine casing mounting edge in a specific embodiment of the present invention;
Fig. 5 is the perspective view of the fixture shown in Fig. 4;
Fig. 6 is the B-B cross-sectional schematic of the use state of the fixture shown in Fig. 4;
Fig. 7 is A place enlarged diagram in Fig. 6;
Fig. 8 is the cross-sectional schematic of Fig. 7 center platen;
Fig. 9 is the schematic top plan view of the pressing plate shown in Fig. 8.
The specific embodiment
For technical characterictic of the present invention, object and effect being had more clearly, understand, now contrast accompanying drawing explanation the specific embodiment of the present invention.Wherein, identical parts adopt identical label.
Take the processing method of described turbine casing 1 PRECISION HOLE of a kind of airplane turbine casing mounting edge provided by the invention as example illustrates of describing in background technology below.
Fig. 4 is according to the schematic top plan view of the fixture using in the processing method of the PRECISION HOLE of a kind of airplane turbine casing mounting edge in a specific embodiment of the present invention; Fig. 5 is the perspective view of the fixture shown in Fig. 4; Fig. 6 is the B-B cross-sectional schematic of the use state of the fixture shown in Fig. 4; Fig. 7 is A place enlarged diagram in Fig. 6; Fig. 8 is the cross-sectional schematic of Fig. 7 center platen; Fig. 9 is the schematic top plan view of the pressing plate shown in Fig. 8.Shown in Fig. 1-2,4-9, the invention provides a kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge, the first mounting edge 12 and the second mounting edge 13 that described turbine casing 1 comprises a taper type casing wall 11 and is welded on respectively described casing wall two ends, periphery along described the first mounting edge 12 and described the second mounting edge 13 has respectively at least three PRECISION HOLE, the PRECISION HOLE of described the first mounting edge 12 is processed and is put in place, three PRECISION HOLE of described the first mounting edge 12 are locating hole 121, and described processing method comprises the steps:
A, to described the first mounting edge 12 and described the second mounting edge 13 end surface grindings; The first fixture 2 of a horizontal positioned is provided in CNC milling machine (not shown), the described locating hole 121 of corresponding described the first mounting edges 12 of described the first fixture 2 is provided with three the first alignment pins 211, and described the first fixture 2 is provided with for the end face laminating with described the first mounting edge 12 first by face 212;
To described the first mounting edge 12 and described the second mounting edge 13 end surface grindings, be in order to ensure flatness and the fineness of end face, avoid due to described the first mounting edge 12 and described the second mounting edge 13 end faces injustice, cause machining deformation, affect following process precision, after grinding, described turbine casing 1 is positioned on described the first fixture 2 with free state, described the first mounting edge 12 is fitted by face 212 with described first, then to described the first mounting edge 12, exert pressure, itself and described first are fitted tightly by face 212, at described the second mounting edge 13 end faces, using amesdial to play table measures, need to guarantee that the variable quantity of amesdial reading when compressing and unclamping is in 0.005mm.
Shown in Fig. 4-7, the invention provides a kind of the first fixture 2 for fixing described turbine casing 1, it has a body 21 for being connected with described Digit Control Machine Tool, on described body 21, be provided with first round boss 22, on described the first round boss 22, be provided with second round boss 23, the upper surface of described the second round boss 23 is described first and leans on face 212, described the second round boss 23 is provided with three extensions 210 that extend laterally, on described extension 210, be provided with described the first alignment pin 211, the diameter d of described the second round boss 23 is less than the inside diameter of described the first mounting edge 12, when described the first alignment pin 211 inserts described locating hole 121, the end face of described the first mounting edge 12 is only fitted with the upper surface of described extension 210, only that is to say and by face 212, be positioned at the part laminating on described extension 210 with described first, like this, just can be when ensureing that described the first fixture 2 provides enough support strength, reduce end face and described first contact area by face 212 of described the first mounting edge 12, also just can reduce end face and described first compression distortion that may bring by the surface irregularity of face 212 due to described the first mounting edge 12
When three described the first alignment pins 211 insert respectively three described locating holes 121, utilize 3 modes of crossing location can realize the stable position to described turbine casing 1.
B, utilize described CNC milling machine to carry out respectively centering to three described the first alignment pins 211, and by described CNC milling machine, obtain respectively the centre coordinate of three described the first alignment pins 211, calculate the first central coordinate of circle of three described the first determined circles in alignment pin 211 center;
Utilize described CNC milling machine can obtain respectively the centre coordinate of three described the first alignment pins 211, then can utilize on computers the software engineerings such as CAD or MasterCAM to draw the data of the first central coordinate of circle of three described the first determined circles in alignment pin 211 center.
C, described turbine casing 1 is positioned on described the first fixture 2, described the first alignment pin 211 is inserted to described locating hole 121, make described the first mounting edge 12 end faces and described first by face 212 laminating, on described CNC milling machine, according to described the first central coordinate of circle in step B, described the second mounting edge 13 is carried out to three described PRECISION HOLE roughing;
Shown in Fig. 6-9, in order to ensure described turbine casing 1 stablizing in process, described the first fixture 2 can further include the pressing plate 24 described the first mounting edge 12 being clamped in described the first alignment pin 211 positions, described pressing plate 24 has a U-shaped head, described first mounting edge 12 of described locating hole 121 both sides closely can be clamped by face 212 with described first like this.
D, position degree to rough machined three described PRECISION HOLE in step C carries out three-dimensional coordinates measurement, if it is qualified to measure, directly rough machined three described PRECISION HOLE in step C are finish-machined to final size, if measure defective, the 3rd central coordinate of circle of the second central coordinate of circle of the determined circle in center of rough machined three described PRECISION HOLE in step C and three determined circles in described locating hole 121 center is compared, according to the difference of gained, described CNC milling machine is adjusted, afterwards, rough machined three described PRECISION HOLE in step C are finish-machined to final size,
When in to step C, the position degree of rough machined three described PRECISION HOLE is measured, described turbine casing 1 can be taken off from described the first positioning fixture 2, utilize three-coordinates measuring machine to measure, thereby obtain the second central coordinate of circle of the determined circle in center of rough machined three described PRECISION HOLE in step C, can also obtain the 3rd central coordinate of circle measurement of three determined circles in described locating hole 121 center simultaneously.
After utilizing 3 modes of excessively locating to described turbine casing 1 stable position, if described the first alignment pin 211 can meet the demands with Working position degree and the precision of described locating hole 121, described the first central coordinate of circle is also located in the 3rd central coordinate of circle of three determined circles in described locating hole 121 center.Therefore,, if the position degree of rough machined three described PRECISION HOLE meets designing requirement in step C, can further to described PRECISION HOLE hole, be finish-machined to final size;
But the restriction due to existing lathe and clamp precision, described the first alignment pin 211 is all difficult to be protected with Working position degree and the precision of described locating hole 121, therefore, when in step C, the position degree of rough machined three described PRECISION HOLE does not meet designing requirement, also just need to again to the machined parameters of described CNC milling machine (that is to say the numerical value of the program of the described CNC milling machine of input), adjust, this is also the problem that the present invention further will solve.That is to say, the present invention is by comparing the 3rd central coordinate of circle of described the second central coordinate of circle and three determined circles in described locating hole 121 center, according to the difference of gained, offset coordinates data namely, machined parameters to described CNC milling machine is adjusted, afterwards, described CNC milling machine just can be according to the parameter after adjusting, that is to say the machining center mating with the 3rd central coordinate of circle of three determined circles in described locating hole 121 center, rough machined three described PRECISION HOLE in step C are finish-machined to final size, so just completed the processing of the PRECISION HOLE on described the second mounting edge 13.Also just can effectively ensure the relative position degree of PRECISION HOLE on described the second mounting edge 13 and PRECISION HOLE on corresponding described the first mounting edge 12.
In a preferred embodiment, when the periphery of described the second mounting edge 13 has more than three PRECISION HOLE, in step D, rough machined three described PRECISION HOLE in step C are finish-machined to final size simultaneously, process other the PRECISION HOLE on described the second mounting edge 13.
In a preferred embodiment, in steps A, utilize described CNC milling machine main shaft self to move described first Milling Process of carrying out 0.02mm by face 212.Can guarantee so described CNC milling machine main axle moving and described first absolute vertical by face, thus self precision deficiency and the impact that follow-up processing is brought of the possible accuracy of manufacture deficiency of described the first fixture 2 that can overcome that described CNC milling machine may exist.
The invention provides a kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge, the impact that it has overcome machine tool precision and the fixture accuracy of manufacture, can utilize existing machine tool to process qualified parts, and operation qualification rate can reach more than 99%.
Although it will be appreciated by those skilled in the art that the present invention is described according to the mode of a plurality of embodiment, not each embodiment only comprises an independently technical scheme.For the purpose of in description, so narration is only used to know; those skilled in the art should make description as a wholely to be understood, and regard technical scheme related in each embodiment as the mode that can mutually be combined into different embodiment understand protection scope of the present invention.
The foregoing is only the schematic specific embodiment of the present invention, not in order to limit scope of the present invention.Any those skilled in the art, not departing from equivalent variations, modification and the combination of doing under the prerequisite of design of the present invention and principle, all should belong to the scope of protection of the invention.

Claims (3)

1. the processing method of the PRECISION HOLE of an airplane turbine casing mounting edge, the first mounting edge and the second mounting edge that described turbine casing comprises a taper type casing wall and is welded on respectively described casing wall two ends, periphery along described the first mounting edge and described the second mounting edge has respectively at least three PRECISION HOLE, the PRECISION HOLE of described the first mounting edge is processed and is put in place, three PRECISION HOLE of described the first mounting edge are as locating hole, and described processing method comprises the steps:
A, to described the first mounting edge and described the second mounting edge end surface grinding; The first fixture of a horizontal positioned is provided on CNC milling machine, the described locating hole of corresponding described the first mounting edge of described the first fixture is provided with three the first alignment pins, and described the first fixture is provided with for the end face laminating with described the first mounting edge first by face;
B, utilize described CNC milling machine to carry out respectively centering to three described the first alignment pins, and by described CNC milling machine, obtain respectively the centre coordinate of three described the first alignment pins, calculate the first central coordinate of circle of the determined circle in center of three described the first alignment pins;
C, described turbine casing is positioned on described the first fixture, make described the first alignment pin insert described locating hole, make described the first mounting edge end face and described first by face laminating, on described CNC milling machine, according to described the first central coordinate of circle in step B, described the second mounting edge is carried out to three described PRECISION HOLE roughing;
D, position degree to rough machined three described PRECISION HOLE in step C carries out three-dimensional coordinates measurement, if it is qualified to measure, directly rough machined three described PRECISION HOLE in step C are finish-machined to final size, if measure defective, the 3rd central coordinate of circle of the determined circle in center of the second central coordinate of circle of the determined circle in center of rough machined three described PRECISION HOLE in step C and three described locating holes is compared, according to the difference of gained, described CNC milling machine is adjusted, afterwards, rough machined three described PRECISION HOLE in step C are finish-machined to final size.
2. method according to claim 1, it is characterized in that, if the periphery of described the second mounting edge has three above PRECISION HOLE, in step D, when rough machined three described PRECISION HOLE are finish-machined to final size in to step C, process other the PRECISION HOLE on described the second mounting edge.
3. method according to claim 1, is characterized in that, in steps A, utilizes described CNC milling machine main shaft self to move described first Milling Process of carrying out 0.02mm by face.
CN201310560491.0A 2013-11-12 2013-11-12 A kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge CN103586513B (en)

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104259574A (en) * 2014-07-28 2015-01-07 中航湖南通用航空发动机有限公司 Method for machining precision hole in thin-wall casing type part
CN105290737A (en) * 2015-11-20 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 Machining method for casing casting part
CN105345402A (en) * 2015-11-19 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Anti-deformation machining method for milling round hole and lace of casing part
CN105345472A (en) * 2015-11-20 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Non-orthogonal structure cartridge receiver machining method and clamp
CN106493503A (en) * 2016-11-25 2017-03-15 沈阳黎明航空发动机(集团)有限责任公司 A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity
CN109352194A (en) * 2018-12-06 2019-02-19 中国航发贵州黎阳航空动力有限公司 A kind of welding method of accumulator package
CN112024750A (en) * 2020-11-05 2020-12-04 中国航发沈阳黎明航空发动机有限责任公司 Double-layer thin-wall sheet metal casing shape correction and heat treatment setting clamp and method

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CN101767218A (en) * 2008-12-30 2010-07-07 沈阳黎明航空发动机(集团)有限责任公司 Five-axis plunge milling method of aeroengine crankcase
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CN101767218A (en) * 2008-12-30 2010-07-07 沈阳黎明航空发动机(集团)有限责任公司 Five-axis plunge milling method of aeroengine crankcase
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CN104259574A (en) * 2014-07-28 2015-01-07 中航湖南通用航空发动机有限公司 Method for machining precision hole in thin-wall casing type part
CN104259574B (en) * 2014-07-28 2016-08-24 中航湖南通用航空发动机有限公司 A kind of Thin-Wall Outer Casing class machine parts'precise hole forming method
CN105345402A (en) * 2015-11-19 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Anti-deformation machining method for milling round hole and lace of casing part
CN105345402B (en) * 2015-11-19 2017-12-01 沈阳黎明航空发动机(集团)有限责任公司 A kind of distortion-free processing method of casing part Milling Machining circular hole and lace
CN105290737A (en) * 2015-11-20 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 Machining method for casing casting part
CN105345472A (en) * 2015-11-20 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Non-orthogonal structure cartridge receiver machining method and clamp
CN105345472B (en) * 2015-11-20 2017-06-09 沈阳黎明航空发动机(集团)有限责任公司 A kind of non-orthogonal configuration casing processing method and fixture
CN106493503A (en) * 2016-11-25 2017-03-15 沈阳黎明航空发动机(集团)有限责任公司 A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity
CN106493503B (en) * 2016-11-25 2019-02-12 沈阳黎明航空发动机(集团)有限责任公司 A kind of rear housing precision bolt hole Combined machining process repaired to the longevity
CN109352194A (en) * 2018-12-06 2019-02-19 中国航发贵州黎阳航空动力有限公司 A kind of welding method of accumulator package
CN109352194B (en) * 2018-12-06 2021-01-22 中国航发贵州黎阳航空动力有限公司 Welding method of pressure accumulator assembly
CN112024750A (en) * 2020-11-05 2020-12-04 中国航发沈阳黎明航空发动机有限责任公司 Double-layer thin-wall sheet metal casing shape correction and heat treatment setting clamp and method
CN112024750B (en) * 2020-11-05 2021-01-08 中国航发沈阳黎明航空发动机有限责任公司 Double-layer thin-wall sheet metal casing shape correction and heat treatment setting clamp and method

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Patentee after: China Hangfa South Industrial Co. Ltd.

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Patentee before: China Southern Airlines Industry (Group) Co., Ltd.