CN110744070B - Method for machining molded surface of flame tube of ultrathin-wall aircraft engine - Google Patents
Method for machining molded surface of flame tube of ultrathin-wall aircraft engine Download PDFInfo
- Publication number
- CN110744070B CN110744070B CN201911129510.8A CN201911129510A CN110744070B CN 110744070 B CN110744070 B CN 110744070B CN 201911129510 A CN201911129510 A CN 201911129510A CN 110744070 B CN110744070 B CN 110744070B
- Authority
- CN
- China
- Prior art keywords
- turning
- profile
- processing
- flame tube
- feed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turning (AREA)
Abstract
The invention discloses a method for processing a flame tube profile of an ultrathin-wall aircraft engine, which comprises the steps of processing the profile and processing a deep narrow groove on the profile, and the processing is carried out according to the following procedures: the method comprises the steps of flame tube blank → rough turning molded surface → stress relief heat treatment → semi-finish turning inner and outer molded surfaces, allowance is left → stress relief heat treatment → turning datum → finish turning outer molded surface → turning deep narrow groove → finally finish turning inner molded surface, wherein numerical control programming turning is adopted in the rough turning surface, and macro-program circular turning is adopted in the deep and narrow groove turning process to remove chips in time. The invention can effectively solve the problems of serious profile deformation, uneven wall thickness and burn caused by unreasonable cutting parameters on the surfaces of the cutter and the workpiece easily occurring in the flame tube profile processing, and improves the processing quality and the processing efficiency.
Description
Technical Field
The invention relates to the field of automatic machining, and mainly aims at a machining method of ultrathin-wall folded grooves of inner and outer rings of a flame tube of an engine.
Background
The inner ring and the outer ring of the flame tube of the aero-engine are machined by adopting GH3044 ring forgings, the material removal allowance is large, the machined profiles of the inner ring and the outer ring are complex, the size of a part is easy to change due to the adjustment of the feeding amount in the machining process, and machining errors are brought to the characteristic sizes of the groove and the wall surface of the ring body.
At present, in the size control of the inner ring and the outer ring of the mechanical processing of the flame tube, the small feeding amount is mainly adopted, the size of the molded surface of a part is ensured by a method of manually removing scrap iron, the processing method has low efficiency, the size of the molded surface of the part is seriously deformed, and the key size can not be completely ensured.
Disclosure of Invention
In order to solve the processing problems of the profile size and the deep narrow groove in the mechanical processing of the inner ring and the outer ring of the flame tube, the invention provides the processing method of the profile of the flame tube of the ultrathin-wall aircraft engine, which ensures that the profile size and the groove size of the flame tube meet the requirements, reduces the size error, reduces the processing deformation of the flame tube and improves the processing efficiency.
According to the invention, a set of complete processing technique is designed according to the characteristics of the part, and meanwhile, the drilling circulating feed mode is applied to the turning of a numerical control lathe.
The technical scheme of the invention is realized as follows:
a method for processing a flame tube profile of an ultra-thin-wall aircraft engine comprises the steps of processing the profile and processing a deep narrow groove on the profile, and the processing is carried out according to the following procedures: the flame tube blank → the rough turning molded surface → the stress relief heat treatment → the semi-finish turning inner and outer molded surfaces, the allowance is left → the stress relief heat treatment → the turning datum → the finish turning outer molded surface → the deep turning narrow groove → the final finish turning inner molded surface.
Further, the rough lathe is machined by a numerical control lathe when in shape, and the outer molded surface is turned according to a preset feed path.
Further, the feed path comprises a plurality of broken line segments, and adjacent broken line segments are connected through an arc.
Further, a universal alloy turning tool is adopted when the outer profile is turned; adopting a spherical alloy turning tool when the inner and outer surfaces are semi-finish turned; and a spherical alloy turning tool is adopted when the inner and outer profiles are finish turned.
Further, when the deep narrow groove is turned, turning is carried out on the numerically controlled lathe according to the condition that the cutter retracts after feeding once, the retracting amount is smaller than the feeding amount, and the cutter retracts to remove chips from the deep narrow groove when the accumulated feeding amount reaches a set value. The concept of this method is similar to deep hole circulation drilling. Due to direct turning, the generated scrap iron can extrude the wall of the part in a deep and narrow groove similar to a blind hole, so that the width dimension of the groove is inconsistent. Meanwhile, as the scrap iron cannot be discharged, the heat of turning cannot be discharged along with the scrap iron, so that the abrasion of the cutter is accelerated, and the depth and the size of the groove cannot be guaranteed. Therefore, the machining method of advancing, retreating, advancing and retreating is adopted, the iron scraps can be taken out when the cutter is retreated, and the problems are solved.
Preferably, the cutter feeding amount and the cutter retracting amount are equal each time. Of course, the amount of tool advance and the amount of tool retreat may be different for each time.
Further, the accumulated feed amount is smaller than the groove depth of the deep and narrow groove, and when the depth of the deep and narrow groove is large or the performance of the cutter cannot meet the requirement of one-time processing, a mode of withdrawing the cutter for multiple times for chip removal can be considered.
Furthermore, the accumulated feed amount is equal to the depth of the deep and narrow groove, and when the depth of the deep and narrow groove is small or the performance of the cutter can meet the requirement of one-time processing, a one-time chip removal mode can be directly adopted.
Furthermore, the numerical control lathe is programmed by a macroprogram during processing, the programming comprises the following variables,
starting point X-axis coordinate # 1;
a tool start point Z-axis coordinate # 2;
the included angle between the groove and the axial direction is # 3;
initial depth of cut # 4;
the tool retracting distance is # 5;
total depth of cut # 6;
feed end point X axis coordinate # 11;
feed end point Z axis coordinate # 12;
tool retracting end point X-axis coordinate # 21;
tool retracting endpoint Z axis coordinate # 22;
and the variables #1, #2, #3, #4, #5, #11, #12, #21, #22 satisfy the following relationships:
#11＝#1-2*#4*SIN[#3]；
#12＝#2-#4*COS[#3]；
#21＝#11+2*#5*SIN[#3]；
#22＝#12+#5*COS[#3]。
further, the macro program programming also comprises setting circulation and judgment, wherein in each feed, a constant value is accumulated in the variable initial feed depth #4 to serve as a feed amount, the final value of the variable is compared with the value of the variable total cutting depth #6, when the accumulated final value of the variable initial feed depth #4 is smaller than the value of the variable total cutting depth #6, the cutter continues to feed and retract according to the variables #11, #12, #21 and #22, and when the accumulated final value of the variable initial feed depth #4 is larger than or equal to the value of the variable total cutting depth #6, the cutter exits from the deep narrow groove.
Compared with the prior art, the method and the cutting parameters can effectively solve the problems that the profile is seriously deformed and the wall thickness is uneven easily in the flame tube profile processing and the surface of the cutter and the workpiece is burnt due to unreasonable cutting parameters. The invention provides a programming idea of a rough turning molded surface, obtains complete molded surface data while obtaining the rough turning molded surface, and provides a measuring reference for subsequent turning reference and finish turning. In the aspect of groove machining, the numerical control circular drilling mode is applied to turning by initiatively utilizing a macro program, so that the problems of unqualified groove width dimension, extrusion damage of scrap iron on the surface of a deep groove, damage of the scrap iron to a cutter and the like caused by incapability of discharging the scrap iron in deep and narrow groove machining are solved, and the machining efficiency and the machining qualified rate of parts are greatly improved.
Drawings
FIG. 1 is a G code simulation tool path trajectory;
fig. 2 is a schematic view of rough turning of the outer profile.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
In this embodiment, the method for processing the profile of the flame tube mainly includes the following 3 aspects:
1. in the process of processing the inner ring and the outer ring of the flame tube, a process route of blank → a rough turning profile (comprising two parts of the rough turning profile and the inner profile) → stress removing heat treatment → a semi-finished inner profile and an outer profile (a single edge is left, the single edge means that a processing margin is left in the radius dimension) → stress removing heat treatment → turning reference → a finished outer profile → a re-turning deep narrow groove → finally a finished inner profile is adopted. When the surface of the flame tube is a rough vehicle, a plurality of broken line segments are processed by adopting a G01 instruction to form the molded surface of the flame tube, each broken line segment consists of two straight line segments, and adjacent broken line segments are connected by processing arcs through a G03 instruction to form a high-order curve.
2. A universal alloy turning tool is used when the outer surface of the die is roughly turned; semi-finish turning is carried out, wherein the inner and outer shapes of the semi-finish turning are arc curved surfaces, and a spherical alloy turning tool with the width of 6mm is used for processing; and a spherical alloy lathe tool with the width of 4mm is used for finish turning the inner and outer shapes. The cutting speed vc is 30-70 m/min, the cutting depth ap is 3.4mm, and the feeding fn is 0.2 mm/r.
3. The macro-programming is used for programming a circular feed mode similar to that of a deep hole drill, so that the method can be applied to the turning of a numerical control lathe.
As shown in fig. 1 and 2, the path of the torch profile machining feed is shown. As the outer molded surface is used as a measuring reference surface, complete molded surface data are needed to accurately process the molded surface size of the part in finish machining.
During processing, firstly according to a planned process flow: blank → rough turning mold face → stress relief heat treatment → semi-finish turning (leaving 3mm margin on the side) → stress relief heat treatment → turning reference → finish turning exterior face → turning deep narrow groove → finally finish turning interior face to plan. Using a universal alloy turning tool in the rough turning shape; semi-finish turning is carried out by using a spherical alloy turning tool with the width of 6 mm; and a spherical alloy lathe tool with the width of 4mm is used for finish turning the inner and outer shapes. And setting machine tool parameters according to the cutting speed vc of 30-70 m/min, the cutting depth ap of 3.4mm and the feeding fn of 0.2 mm/r. When the blank profile is roughly turned, the following numerical control program is used for processing.
Program for numerically controlling the turning of the profile of the flame tube (where XXX is the X-axis and Z-axis coordinate values determined according to the dimensions of the flame tube, the program code corresponds to the feed path in fig. 1 and 2, and XXX is the program name):
％
(NAME-XXX)
G40 G18 G90
G00 Xxxx Zxxx
Xxxx
Xxxx
Zxxx
S30 M03
G01 Xxxx F.1
Zxxx
Xxxx Zxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
Xxxx Zxxx
G03 Xxxx Zxxx Kxxx
G01 Xxxx Zxxx
Xxxx Zxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
Xxxx Zxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
Xxxx Zxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
G02 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
Xxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Xxxx Zxxx
G03 Xxxx Zxxx Ixxx Kxxx
G01 Zxxx
Xxxx
G02 Xxxx Zxxx Ixxx Kxxx F1.
M30
％
considering the part material as GH3044, the tool is narrower at 2.5mm, and the total cutting depth of the deep and narrow grooves is 6.5 mm. If the simple single oblique line is walked for lathing, the scrap iron can not be discharged, and the cutter is easy to damage and break, the surface of the deep and narrow groove is extruded and damaged, the groove width is unqualified, and the like. Therefore, a mode that the cutter retreats to the outside of the groove for chip removal when the feed is 0.1mm, the withdrawal is 0.05mm and the total feed is 0.5mm or a mode that the cutter retreats to the outside of the groove for chip removal when the feed is 0.1mm, the withdrawal is 0.05mm and the total feed is equal to 6.5mm is adopted. The following turning numerical control program can be used for solving the problem of damage of scrap iron to the tool and parts during deep and narrow groove processing.
The following is a macro procedure used for turning the deep and narrow grooves of the flame tube (the programming idea of the macro procedure is similar to the feed mode of a deep-hole circulating drill, and a one-time chip removal mode is enumerated here):
Claims (5)
1. the method for processing the flame tube profile of the ultrathin-wall aircraft engine comprises the steps of processing the profile and processing a deep narrow groove on the profile, and is characterized by comprising the following steps of: the process comprises the steps of flame tube blank → rough turning molded surface → stress relief heat treatment → semi-finish turning inner and outer molded surfaces, allowance is left → stress relief heat treatment → turning reference → finish turning outer molded surface → turning deep narrow groove → finally finish turning inner molded surface;
the rough lathe is machined when the profile is machined by a numerical control lathe, the outer profile is turned according to a preset feed path, the feed path comprises a plurality of broken line segments, adjacent broken line segments are connected through an arc, the rough turning profile is obtained, and meanwhile, complete profile data are obtained, so that a measurement reference is provided for subsequent turning reference and finish turning;
when the deep narrow groove is lathed, the numerical control lathe is lathed according to the condition that the cutter moves back once every time the cutter moves back, the tool retracting amount is smaller than the tool moving amount, and the cutter moves back from the deep narrow groove to remove chips when the accumulated tool moving amount reaches a set value;
the numerical control lathe is programmed by a macroprogram during processing, the programming comprises the following variables,
starting point X-axis coordinate # 1;
a tool start point Z-axis coordinate # 2;
the included angle between the groove and the axial direction is # 3;
initial depth of cut # 4;
the tool retracting distance is # 5;
total depth of cut # 6;
feed end point X axis coordinate # 11;
feed end point Z axis coordinate # 12;
tool retracting end point X-axis coordinate # 21;
tool retracting endpoint Z axis coordinate # 22;
and the variables #1, #2, #3, #4, #5, #11, #12, #21, #22 satisfy the following relationships:
#11=#1-2*#4*SIN[#3]；
#12=#2-#4*COS[#3]；
#21=#11+2*#5*SIN[#3]；
#22=#12+#5*COS[#3]；
feeding is instructed through G01, and retracting is instructed through G01;
and setting circulation and judgment, wherein in each feed, the variable initial feed depth #4 accumulates a fixed value to be used as a feed amount, the final value of the variable is compared with the value of the variable total cutting depth #6, when the final value accumulated by the variable initial feed depth #4 is less than the value of the variable total cutting depth #6, the cutter continues to feed and retract according to the variables #11, #12, #21, #22, and when the final value accumulated by the variable initial feed depth #4 is more than or equal to the value of the variable total cutting depth #6, the cutter exits from the deep and narrow groove.
2. The method for machining the profile of the ultrathin-wall aircraft engine flame tube of claim 1, characterized by comprising the following steps: a universal alloy turning tool is adopted when the outer profile is turned;
adopting a spherical alloy turning tool when the inner and outer surfaces are semi-finish turned;
and a spherical alloy turning tool is adopted when the inner and outer profiles are finish turned.
3. The method for machining the profile of the ultrathin-wall aircraft engine flame tube of claim 1, characterized by comprising the following steps: the cutter feeding amount and the cutter retracting amount are equal each time.
4. The method for machining the profile of the ultrathin-wall aircraft engine flame tube of claim 1, characterized by comprising the following steps: the accumulated feed amount is less than the groove depth of the deep and narrow groove.
5. The method for machining the profile of the ultrathin-wall aircraft engine flame tube of claim 1, characterized by comprising the following steps: the accumulated feed amount is equal to the groove depth of the deep and narrow groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911129510.8A CN110744070B (en) | 2019-11-18 | 2019-11-18 | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911129510.8A CN110744070B (en) | 2019-11-18 | 2019-11-18 | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110744070A CN110744070A (en) | 2020-02-04 |
| CN110744070B true CN110744070B (en) | 2021-01-22 |
Family
ID=69283611
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911129510.8A Active CN110744070B (en) | 2019-11-18 | 2019-11-18 | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110744070B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112191864A (en) * | 2020-09-29 | 2021-01-08 | 中国航发动力股份有限公司 | Machining method for blade installation annular groove |
| CN112894266A (en) * | 2020-12-18 | 2021-06-04 | 四川德兰航宇科技发展有限责任公司 | Machining method of ring forging with complex special-shaped cross section |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104028782A (en) * | 2014-06-06 | 2014-09-10 | 中国南方航空工业(集团)有限公司 | Lathe machining method for end face deep narrow groove in aerial engine crankcase |
| CN104097041B (en) * | 2014-06-30 | 2017-06-09 | 中国南方航空工业(集团)有限公司 | The processing method of cylinder class thin-wall part |
| CN204227466U (en) * | 2014-09-26 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber burner inner liner wall cooling structure |
| CN106623987B (en) * | 2016-12-27 | 2018-07-20 | 中国南方航空工业(集团)有限公司 | The deep narrow slot precision machining method of burner inner liner thin-walled parts |
| DE102017212575A1 (en) * | 2017-07-21 | 2019-01-24 | Siemens Aktiengesellschaft | Method for increasing the power of a gas turbine |
| CN108381122B (en) * | 2018-02-11 | 2019-11-05 | 广汉天空动力机械有限责任公司 | A kind of process using annular forging piece processing burner inner liner floating wall tile fragment |
| CN109702488B (en) * | 2019-01-17 | 2020-06-23 | 哈尔滨工业大学 | Machining method of slender thin-wall aluminum-based composite pipe with uniform wall thickness |
| CN110039269B (en) * | 2019-05-30 | 2021-03-23 | 上海第一机床厂有限公司 | Manufacturing method of thin-wall deep-hole sealing shell of driving mechanism |
| CN110102988B (en) * | 2019-06-20 | 2020-12-29 | 苏州市意可机电有限公司 | Machining process of large-diameter thin-wall part |
-
2019
- 2019-11-18 CN CN201911129510.8A patent/CN110744070B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110744070A (en) | 2020-02-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110744070B (en) | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine | |
| JP2013505141A (en) | Tools with blanks and cooling channels | |
| CN110678285B (en) | Method for producing a toothed workpiece, and control program, tool and gear cutting machine suitable for this purpose | |
| US10926344B2 (en) | Taper reamer | |
| KR101332729B1 (en) | Modular drilling tool and method for the production thereof | |
| JP5010911B2 (en) | Extrusion die manufacturing method and electric discharge machining electrode used therefor | |
| CN110842047A (en) | Extrusion die machining method | |
| US9999959B2 (en) | Support pad for a drill head and method for designing and manufacturing a support pad | |
| Pasko et al. | High speed machining (HSM)–the effective way of modern cutting | |
| CN104646973A (en) | Processing method of multi-thread worm | |
| CN106623474B (en) | A kind of inside and outside extrusion die for carrying spiral fin proximate matter of pipe | |
| CN108000081A (en) | A kind of high speed CNC deep hole processing methods | |
| CN111683773B (en) | Turning method and turning tool for CNC lathe | |
| CN115971891A (en) | Method for processing large-size hole | |
| CN110744071A (en) | Method for machining deep and narrow groove with angle | |
| CN113424118A (en) | Method for generating control command data for controlling a CNC lathe | |
| CN107234285B (en) | Formed milling cutter and manufacturing method thereof | |
| CN206435582U (en) | A kind of inside and outside extrusion die for carrying spiral fin section bar of pipe | |
| CN109623277B (en) | Method for processing inner profile of high-Mach-number throat of shock tunnel | |
| RU2702214C1 (en) | Method of deep hole machining in tubular billet | |
| RU2814129C1 (en) | Method of milling thread with cutter | |
| JPH06254720A (en) | Machining method for screw | |
| JP2001310207A (en) | Boring method and boring tool | |
| JP6499117B2 (en) | Female thread machining tool | |
| CN114228064B (en) | Point pouring gate machining method, point pouring gate machining equipment and mold with point pouring gate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |