CN117884839A - Processing method of splash guard of aeroengine combustion chamber - Google Patents
Processing method of splash guard of aeroengine combustion chamber Download PDFInfo
- Publication number
- CN117884839A CN117884839A CN202211223359.6A CN202211223359A CN117884839A CN 117884839 A CN117884839 A CN 117884839A CN 202211223359 A CN202211223359 A CN 202211223359A CN 117884839 A CN117884839 A CN 117884839A
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- Prior art keywords
- splash guard
- blank
- ring
- machining
- cut
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 21
- 238000003672 processing method Methods 0.000 title claims abstract description 10
- 238000005520 cutting process Methods 0.000 claims abstract description 27
- 238000003754 machining Methods 0.000 claims abstract description 23
- 238000000034 method Methods 0.000 claims abstract description 20
- 210000004209 hair Anatomy 0.000 claims abstract description 15
- 238000007514 turning Methods 0.000 claims description 9
- 238000004519 manufacturing process Methods 0.000 claims description 8
- 238000005498 polishing Methods 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 description 5
- 238000000465 moulding Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000003801 milling Methods 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000005219 brazing Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 210000002268 wool Anatomy 0.000 description 1
Classifications
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
The invention discloses a processing method of a splash guard of an aero-engine combustion chamber, which relates to the field of aero-engine combustion chambers and comprises the following steps: s1, configuring a blank, and processing the blank into a splash guard blank; wherein the splash guard Mao Jian is a circumferentially uniform annular member; s2, cutting the splash guard hair piece into a plurality of splash guard single sheets; s3, machining an inner hole on each splash guard single piece, and machining an annular structure surrounding the inner hole on the rear side of each splash guard single piece. According to the invention, the whole blank is processed into the annular splash guard blank with uniform circumference, and then the splash guard blank is cut into a plurality of splash guard singlechips, so that the splash guard singlechips are formed at one time, and the invention has the advantages of time saving, convenient process and better utilization of equipment resources.
Description
Technical Field
The invention relates to the field of aero-engine combustion chambers, in particular to a processing method of a splash guard of an aero-engine combustion chamber.
Background
The splash guard of the combustion chamber is an important component part of the head switching section assembly in the flame tube of the combustion chamber, and is directly contacted with flame in the combustion chamber to bear high-temperature fuel gas.
At present, most of aero-engine combustion chambers adopt annular structures, and the combustion chambers adopt single-ring-cavity short annular structure types. The combustion chamber comprises a casing, a nozzle, a flame tube and other components, wherein the head component of the flame tube is formed by brazing a head switching section and a plurality of splash plates and is used for connecting an inner ring and an outer ring of the flame tube with an inner cap cover and an outer cap cover and simultaneously used for installing a main swirler. The splash baffles are circumferentially arranged, a certain interval is kept between two circumferentially adjacent splash baffles, and expansion and rubbing are prevented under the working state of the engine.
The splash guard is in a structure that the upper end face and the lower end face are in central symmetry around the central axis of the whole combustion chamber, and the central hole and the rear end excircle are in a central symmetry structure around the axis of the central hole of the single splash guard. Therefore, the splash guard is processed by adopting bar milling, wire cutting is performed on the left side and the right side of the bar, and finally, the processing is performed by the technological process of turning the center hole and the outer circle. The processing technology has the advantages that equipment resources are not well utilized, and the technology is relatively complex due to milling, so that the occupied labor resources are more.
Disclosure of Invention
The invention aims to overcome the defects of relatively complex processing technology and more occupied human resources of a combustion chamber splash guard in the prior art, and provides a processing method of the aeroengine combustion chamber splash guard, which is time-saving, convenient and fast in technology and better in equipment resource utilization.
The invention solves the technical problems by the following technical scheme:
the invention provides a processing method of a splash guard of a combustion chamber of an aeroengine, which comprises the following steps:
s1, configuring a blank, and processing the blank into a splash guard blank;
wherein the splash guard Mao Jian is a circumferentially uniform annular member;
s2, cutting the splash guard hair piece into a plurality of splash guard single sheets;
s3, machining an inner hole on each splash guard single piece, and machining an annular structure surrounding the inner hole on the rear side of each splash guard single piece.
In the scheme, the whole blank is processed into the annular splash guard blank piece with uniform circumferential direction, and the splash guard blank piece is cut into a plurality of splash guard single pieces, so that the splash guard single pieces can be obtained by carrying out integral molding processing on one blank rather than molding processing on single bar one by one in comparison with a mode of milling processing on the blank of each splash guard single piece, thereby better using equipment resources, cutters and the like, and saving processing time and labor cost; in the scheme, when the annular structure and the inner hole of each cut splash guard single chip are processed, a large amount of leftover materials are cut when the blank piece is processed into the splash guard blank piece in the previous step, so that the processing allowance in the step is less, and the process is simple; in addition, because the splash guard single sheets need to be circumferentially arranged on the head of the flame tube, a plurality of splash guard single sheets are obtained by cutting the same splash guard wool piece in the scheme, the consistency and the finished product qualification rate of the splash guard single sheets are favorably maintained, and meanwhile, the splash guard single sheets can be better arranged along the same circumference.
Preferably, the blank is a ring rolled piece, and in step S1, the blank is machined into the splash guard blank by turning.
In the scheme, the blank is a ring rolling piece so as to be convenient to process into an annular splash guard blank; meanwhile, the blank is annular, so that the blank can be machined in a turning mode, the roundness of the outer ring of the machined splash guard blank is good, the cut splash guard single chip is good in yield, and meanwhile the lathe is directly used for turning the whole blank, so that the technology is mature, the process is simple, and the machining efficiency is high.
Preferably, in step S2, each of the splash plates is identical.
In this scheme, through evenly cutting into a plurality of same splash guard monoliths with splash guard hair spare for the standardization of splash guard monoliths is better, and the interchangeability is better, also makes things convenient for the ration cutting of splash guard hair spare simultaneously.
Preferably, in step S2, the splash guard is cut by wire cutting.
In this scheme, adopt wire-electrode cutting's mode cutting splash guard hair spare, the cutting accuracy is high, and cutting efficiency is high, and is difficult for producing the dust.
Preferably, the splash guard monolithic includes a first flange, a second flange, and a central portion connected between the first flange and the second flange, the thickness of the central portion is greater than the thickness of the first flange and the thickness of the second flange, in step S3, the inner hole is machined in the central portion, and the outer periphery of the rear side of the central portion is machined into the annular structure.
In the scheme, the splash guard single chip is connected with the outer ring of the flame tube and the head switching section through the first flanging and the second flanging, and the central part is used for blocking fuel oil and avoiding local high-temperature ablation caused by the fact that atomized fuel oil splashes to the wall surface of the flame tube; after the inner hole is machined in the central portion, the peripheral edge of the rear side of the central portion is machined into an outer circle, so that an annular structure surrounding the inner hole is formed on the rear side of the central portion, and the requirements of a splash guard single chip are met.
Preferably, in step S3, an inner hole is provided on the splash guard monolithic by means of machining.
In the scheme, the inner hole is machined in a turning mode, and the method has the advantages of being convenient in process, high in efficiency and good in roundness of the inner hole.
Preferably, in step S3, a portion of the splash guard monolithic located outside the edge of the inner hole is turned into the annular structure by turning.
In the scheme, the annular structure is machined in a turning mode, and the method has the advantages of being convenient in process, high in efficiency, good in roundness of the outer circle of the annular structure and the like.
Preferably, the splash guard hair piece comprises a first ring piece, a center ring and a second ring piece, wherein the center ring is connected between the first ring piece and the second ring piece; in step S2, after the splash guard hair piece is cut, the first ring piece is cut into a plurality of first flanges, the second ring piece is cut into the second flanges, and the center ring is cut into a plurality of center parts.
In the scheme, a first ring piece, a center ring and a second ring piece are firstly machined on a blank, and then the machined splash guard blank piece is cut, and the first ring piece, the second ring piece and the center ring are annular, so that machining by using a lathe or other equipment is facilitated; the splash guard rough piece is cut after being processed, and the first flanging, the second flanging and the center portion of each splash guard single piece do not need to be molded one by one, so that the processing efficiency and the processing precision are improved.
Preferably, the processing method further comprises the following steps:
s4, polishing the splash guard single chip.
In this scheme, splash guard monolithic is accomplished after car hole and outside annular structure, polishes splash guard monolithic, and the deburring promotes the assembly performance of splash guard monolithic.
Preferably, in step S2, the splash guard hair pieces are cut into 20 splash guard monoliths.
The invention has the positive progress effects that:
according to the invention, the whole blank is processed into the splash guard blank, and then the splash guard blank is cut into a plurality of splash guard singlechips, so that the splash guard singlechips can be obtained by integrally molding one blank without molding single bar materials one by one, and the processing efficiency is improved; the invention can process the blank by using the lathe, thereby better using equipment resources, cutters and the like and saving processing time and labor cost.
Drawings
Fig. 1 is a schematic perspective view of a finished splash guard monolith according to an embodiment of the present invention.
Fig. 2 is a schematic cross-sectional view of a finished splash guard of an embodiment of the present invention.
Fig. 3 is a schematic perspective view of a blank according to an embodiment of the invention.
Fig. 4 is a schematic perspective view of a splash guard according to an embodiment of the present invention.
Fig. 5 is a schematic cross-sectional view of a splash guard according to an embodiment of the present invention.
Fig. 6 is a schematic view of a cut structure of a splash guard according to an embodiment of the present invention.
Fig. 7 is a schematic view of a cut splash guard monolith according to an embodiment of the present invention
Fig. 8 is a schematic cross-sectional view of a cut splash guard monolith according to an embodiment of the present invention
Fig. 9 is a process diagram of a method for manufacturing a splash guard according to an embodiment of the present invention.
Reference numerals illustrate:
blank 100
Splash guard hairpiece 200
First ring 210
Center ring 220
Second ring member 230
Splash guard monolith 300
First flange 310
Center portion 320
Second flange 330
Inner bore 340
Annular structure 350
Detailed Description
The invention is further illustrated by means of examples which follow, without thereby restricting the scope of the invention thereto.
The splash guard includes a plurality of splash guard monoliths 300, the plurality of splash guard monoliths 300 being evenly spaced along the circumference of the burner head, thereby forming an annular splash guard at the burner head to block atomized fuel from splashing to cause localized ablation in the burner.
Referring to fig. 1 and 2, splash plate monolith 300 includes a first flange 310, a second flange 330, and a central portion 320 immediately between first flange 310 and second flange 330. The first flange 310 is used for connecting with the head adapter section of the flame tube, the second flange 330 is used for connecting with the outer ring of the flame tube, and the central part 320 is used for blocking fuel.
Wherein, the opposite sides of the splash guard single sheet 300 are inclined to each other, so that the width of the splash guard single sheet 300 is gradually increased, that is, the width of the first flange 310 is smaller than the width of the central portion 320, and the width of the central portion 320 is smaller than the width of the second flange 330, so that the splash guard single sheet 300 is fan-shaped, and a plurality of splash guard single sheets 300 can be spliced to form a truncated cone-shaped splash guard when being circumferentially arranged along the head of the flame tube.
The thickness of the central portion 320 is greater than the thickness of the first flange 310 and the thickness of the second flange 330. The central portion 320 is formed with an inner hole 340 penetrating both front and rear sides of the central portion 320, and a ring structure 350 surrounding the inner hole 340 is formed at a rear side of the central portion 320. When used herein, the front direction refers to the direction in which splash guard monolith 300 faces the axis of the combustion can, and the rear direction refers to the direction in which splash guard monolith 300 faces away from the axis of the combustion can.
The embodiment discloses a processing method of a splash guard of a combustion chamber of an aeroengine, and the processing method comprises the following steps in combination with fig. 1-9:
s1, configuring a blank 100, and processing the blank 100 into a splash guard blank 200;
wherein, the splash guard 200 is a ring-shaped member with uniform circumference, so as to facilitate the subsequent cutting and other processing of the splash guard 200; the blank 100 is a ring rolled piece to facilitate the acquisition of stock and processing of the blank 100 into an annular splash guard blank 200.
Step S1 comprises the steps of:
s11, fixing the blank 100 on a lathe, and starting the lathe;
s12, controlling a lathe to feed and cut the blank 100, and cutting the blank 100 into the annular splash guard blank 200.
And S13, closing the lathe, and withdrawing the splash guard 200 from the lathe.
Wherein, splash guard hair piece 200 includes a first ring 210, a center ring 220, and a second ring 230 having the same axis, center ring 220 is connected between first ring 210 and second ring 230, and the diameter of first ring 210 is smaller than the diameter of center ring 220, and the diameter of center ring 220 is smaller than the diameter of second ring 230. The entire splash guard 200 is centrosymmetric, so that the lathe can be used to directly perform rotary cutting. Among cutting tools for various metals, lathes are the most widely used type, about 50% of the total number of lathes, and are the most widely machined equipment for machine manufacturing. The lathe is adopted for machining, so that the device is saved, the process is convenient, the operation is convenient, the machining efficiency is high, the machining roundness is good, and the like.
Moreover, in other embodiments, other suitable machining methods may be used to cut the blank 100 to obtain the desired splash guard 200.
S2, cutting the splash guard 200 into a plurality of splash guard singlets 300;
placing the splash guard 200 on a cutting machine, and cutting the splash guard 200 into a plurality of fan-shaped splash guard monoliths 300; the first ring member 210 is cut into a plurality of first rims 310, the second ring member 230 is cut into a plurality of second rims 330, and the center ring 220 is cut into a plurality of center portions 320.
Compared with the mode of machining and forming the first flanging 310, the second flanging 330 and the central part 320 on each splash guard single chip 300, in the scheme, only one blank 100 is required to be rotated to cut the first ring 210, the second ring 230 and the central ring 220, and then the whole cutting is carried out to obtain a plurality of splash guard single chips 300, so that equipment resources, cutters and the like are better used, and the machining time and the labor cost are saved; furthermore, since the splash guard monoliths 300 need to be circumferentially arranged at the head of the flame tube, a plurality of splash guard monoliths 300 obtained by cutting the same splash guard 200 in this case can be more preferably arranged along the same circumference.
The cutting mode of the splash guard 200 can be selected according to the requirement, and the wire cutting mode is selected to cut the splash guard 200 in this embodiment, so that the cutting accuracy is high, the cutting efficiency is high, and dust is not easy to generate.
In this embodiment, the splash guard hair pieces 200 are evenly and equally cut, so that the shape and the size of each splash guard single piece 300 are the same, the standardization of the splash guard single pieces 300 is better, the interchangeability is better, and the quantitative cutting of the splash guard hair pieces 200 is also facilitated.
In this embodiment, the splash guard 200 is cut into 20 splash guard singlets 300 to meet the needs of the flame tube.
Furthermore, in other embodiments, splash plate hair piece 200 may be cut into other numbers and other shapes, as desired.
S3, machining an inner hole 340 on each splash guard single plate 300, and machining an annular structure 350 surrounding the inner hole 340 on the rear side of each splash guard single plate 300.
Wherein, the inner hole 340 can be first turned on the splash guard single chip 300, and then the annular structure 350 is turned by taking the center of the inner hole 340 as a reference; the annular structure 350 may be turned on the periphery of the rear side of the central portion 320, and then the inner hole 340 may be turned with the center of the annular structure 350 as a reference.
In this embodiment, the inner bore 340 and annular structure 350 of splash guard monolith 300 are machined; the splash guard monolith 300 is fixed on a lathe, and an inner hole 340 penetrating through the central portion 320 is formed on the central portion 320; the outer circumference of the rear side of the central portion 320 is rounded such that the outer circumference of the central portion 320 forms an annular structure 350 surrounding the inner bore 340 and coaxial with the inner bore 340. Since the thickness of the center portion 320 is greater than the thickness of the first flange 310 and the thickness of the second flange 330, it is convenient to turn the outer circumference of the center portion 320.
In this embodiment, the inner hole 340 and the annular member 350 of the splash guard monolithic 300 are machined by turning, which has the advantages of convenient process, high efficiency and good roundness of the inner hole 340. In other embodiments, the inner aperture 340 and annular member 350 of splash plate monolith 300 may also be machined in other suitable ways.
When the annular structure 350 and the inner hole 340 are processed on each cut splash guard single chip 300, a large amount of leftover materials are cut when the blank 100 is processed into the splash guard blank 200 in the previous step, so that the processing allowance is small in the step, and the process is simple.
S4, polishing the splash guard single chip 300.
After splash guard 300 completes machining inner hole 340 and outer annular structure 350, splash guard 300 is polished to remove burrs, improving the assembly performance of splash guard 300.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (10)
1. The processing method of the splash guard of the combustion chamber of the aeroengine is characterized by comprising the following steps of:
s1, configuring a blank, and processing the blank into a splash guard blank;
wherein the splash guard Mao Jian is a circumferentially uniform annular member;
s2, cutting the splash guard hair piece into a plurality of splash guard single sheets;
s3, machining an inner hole on each splash guard single piece, and machining an annular structure surrounding the inner hole on the rear side of each splash guard single piece.
2. A method of machining an aircraft engine combustor splash guard as claimed in claim 1, wherein the blank is a ring rolled piece, and in step S1 the blank is machined into the splash guard blank by turning.
3. A method of manufacturing an aircraft engine combustor splash guard as claimed in claim 1, wherein in step S2 each of said splash guard monoliths is identical.
4. A method of manufacturing an aircraft engine combustor splash guard as claimed in claim 1, wherein in step S2, the splash guard blanks are cut by wire cutting.
5. A method of manufacturing an aircraft engine combustor splash guard as claimed in claim 1, wherein the splash guard monolith comprises a first flange, a second flange and a central portion connected between the first flange and the second flange, the central portion having a thickness greater than the thickness of the first flange and the thickness of the second flange, and wherein in step S3 the inner bore is machined in the central portion and the periphery of the rear side of the central portion is machined into the annular configuration.
6. Method for machining an aircraft engine combustion chamber splash guard according to claim 1 or 5, characterized in that in step S3 an inner hole is provided in the splash guard monolith by means of machining.
7. A method of machining an aircraft engine combustor splash guard as claimed in claim 6, wherein in step S3, the portion of the splash guard monolithic beyond the rim of the bore is turned into the annular configuration by machining.
8. A method of manufacturing an aircraft engine combustor splash guard as in claim 5, wherein the splash guard hair piece comprises a first ring member, a center ring, and a second ring member, the center ring being connected between the first ring member and the second ring member; in step S2, after the splash guard hair piece is cut, the first ring piece is cut into a plurality of first flanges, the second ring piece is cut into the second flanges, and the center ring is cut into a plurality of center parts.
9. A method of manufacturing an aircraft engine combustor splash plate as in claim 1, wherein the method further comprises the steps of:
s4, polishing the splash guard single chip.
10. A method of manufacturing an aircraft engine combustor splash guard as claimed in claim 1, wherein in step S2 the splash guard hairpiece is cut into 20 splash guard singlets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211223359.6A CN117884839A (en) | 2022-10-08 | 2022-10-08 | Processing method of splash guard of aeroengine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211223359.6A CN117884839A (en) | 2022-10-08 | 2022-10-08 | Processing method of splash guard of aeroengine combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117884839A true CN117884839A (en) | 2024-04-16 |
Family
ID=90645334
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211223359.6A Pending CN117884839A (en) | 2022-10-08 | 2022-10-08 | Processing method of splash guard of aeroengine combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117884839A (en) |
-
2022
- 2022-10-08 CN CN202211223359.6A patent/CN117884839A/en active Pending
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