CN105252028A - Cutter used for tapered section of small-dimension nozzle - Google Patents
Cutter used for tapered section of small-dimension nozzle Download PDFInfo
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- CN105252028A CN105252028A CN201510757910.9A CN201510757910A CN105252028A CN 105252028 A CN105252028 A CN 105252028A CN 201510757910 A CN201510757910 A CN 201510757910A CN 105252028 A CN105252028 A CN 105252028A
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- Prior art keywords
- cutter
- tool
- tip
- section
- angle
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- 238000003754 machining Methods 0.000 claims abstract description 43
- 239000007921 spray Substances 0.000 claims abstract description 11
- 230000007704 transition Effects 0.000 claims description 19
- 238000005520 cutting process Methods 0.000 claims description 14
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 abstract description 23
- 229910052742 iron Inorganic materials 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 4
- 239000000110 cooling liquid Substances 0.000 abstract description 3
- 238000007599 discharging Methods 0.000 abstract 1
- 238000012545 processing Methods 0.000 description 12
- 238000000034 method Methods 0.000 description 5
- 238000000227 grinding Methods 0.000 description 4
- 241001391944 Commicarpus scandens Species 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000010923 batch production Methods 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000001816 cooling 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
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B27/00—Tools for turning or boring machines; Tools of a similar kind in general; Accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2215/00—Details of workpieces
- B23B2215/04—Aircraft components
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Auxiliary Devices For Machine Tools (AREA)
Abstract
The invention discloses a cutter used for a tapered section of a small-dimension nozzle. The cutter is used for machining an oil spray hole of a variable-section nozzle of a centrifugal spray nozzle of an aero-engine and an inner cavity molded surface of the tapered section connected with the oil spray hole. The cutter consists of a cutter bar, a cutter body and a cutter tip, wherein the cutter tip is positioned at the tail end of the cutter body; the cutter body is positioned between the cutter tip and the cutter bar; and a projection surface of the cutter body is positioned inside a protection surface of the cutter bar and biased at one side of the center of the projection surface of the cutter bar. The cutter disclosed by the invention adopts the eccentric cutter body structure, so that a greater space channel is provided for discharging scrap iron and conveying a cooling liquid, a greater thickness can be obtained, cutter rigidity can be improved, machining quality is easily guaranteed, machining service life is prolonged by 5-10 times in comparison with the service life of the cutter in the prior art, volume production needs can be basically met, and machining cost and a rejection rate are reduced.
Description
Technical Field
The invention relates to a cutter for precision machining, in particular to a cutter for precision machining of a small-size nozzle of an aircraft engine, and particularly relates to a cutter for a conical section of a small-size nozzle.
Background
The nozzle of the centrifugal nozzle of the aircraft engine is structurally characterized in that the molded surface of an inner cavity is a variable cross section, the variable cross section is connected with a micro-size oil injection hole, the size precision is high, high technical requirements are mutually met between various molded surfaces, between an excircle and an end surface, multiple procedures such as turning, milling, grinding, clamping, grinding and polishing in the conventional machining process are difficult to machine, especially, the nozzle is small in size, the sizes of a positioning surface and a clamping surface of a part are small, the part is difficult to clamp, the size and the technical conditions of the part are difficult to guarantee for multiple times of clamping, and the part is very easy to scrap. In addition, the surface quality requirement of the oil spray hole and the inner cavity molded surface is high, the surface roughness is generally 0.4-0.2, and the surface quality can be seriously influenced by the micro cutter which has poor rigidity and generates a vibration cutter. And the quality of the surface quality directly influences the performance parameters of the flow test of the centrifugal nozzle. In the traditional method, the roughness is ensured by manually grinding the inner cavity, and the manual grinding has high operation level for workers, low processing efficiency, large workload and difficult control of size and technical conditions. Moreover, because of the complicated and small size of the internal profile structure of the nozzle, scrap iron is not easy to discharge, and a slight drag hook, scratch, burr and notch directly influence the spraying angle and the fuel unevenness of the centrifugal nozzle. Therefore, it is necessary to provide an improved machining process and design a tool with a special shape structure to improve the machining efficiency and ensure the product quality.
Disclosure of Invention
The technical problem underlying the present invention is to provide a tool for a small-sized spout with a conical section, in order to reduce or avoid the aforementioned problems.
In order to solve the technical problem, the invention provides a cutter for a conical section of a small-size nozzle, wherein the cutter is used for machining an oil injection hole of a variable-section nozzle of a centrifugal nozzle of an aircraft engine and an inner cavity profile of the conical section connected with the oil injection hole, the minimum section diameter of the oil injection hole is A, the maximum section diameter of the conical section is B, a transition arc with the radius of R is arranged between the oil injection hole and the conical section, and the cutter comprises a cutter bar, a cutter body and a cutter point, wherein the cutter point is positioned at the tail end of the cutter body, the cutter body is positioned between the cutter point and the cutter bar, and the projection plane of the cutter body is positioned in the projection plane of the cutter bar and is offset from one side of the center of the projection plane of the cutter bar.
Preferably, the cross section of the cutter body has an upper arc surface and a lower arc surface, and the arc radiuses of the upper arc surface and the lower arc surface are the same.
Preferably, the arc radius of the upper cambered surface and the lower cambered surface is 1.5 mm.
Preferably, the tool tip has a tool tip rake angle and a tool tip relief angle, the tool tip rake angle is an angle at which the tool tip is tilted forward in the machining direction of the tool tip, the tool tip relief angle is an angle at which the tool tip is tilted backward away from the machining direction of the tool tip, the tool tip rake angle is 5 °, and the tool tip relief angle is 15 °.
Preferably, the tip has a principal deviation angle of 15 ° from vertical and a wedge angle of 15 ° from horizontal in its longitudinal direction.
Preferably, the maximum thickness of the tip is less than or equal to the diameter a.
Preferably, a first transition conical surface is arranged between the tool nose and the tool body, and the maximum taper angle of the first transition conical surface is smaller than or equal to the taper angle of the conical section.
Preferably, a second transition conical surface is arranged between the cutter body and the cutter rod, and the maximum taper angle of the second transition conical surface is 40 degrees.
Preferably, the machining direction of the tool is from the smallest cross section of the oil spray hole with the diameter of A along the transition circular arc with the radius of R to the largest cross section of the conical cross section with the diameter of B.
Preferably, the tip of the tool is downward when the tool is machining.
The cutter adopts the cutter body structure which is eccentrically arranged, so that a larger space channel is provided for scrap iron discharge and cooling liquid conveying, a larger cutter body thickness can be obtained, the rigidity of the cutter is improved, the processing quality is easy to ensure, the processing service life is 5-10 times that of the prior art, the requirements of batch production can be basically met, and the processing cost and the rejection rate are reduced.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 shows a cross-sectional view of an aircraft engine centrifugal nozzle according to an embodiment of the invention;
FIG. 2 shows a cross-sectional view of an aircraft engine centrifugal nozzle according to another embodiment of the invention;
FIG. 3 is a schematic illustration of a tool according to an embodiment of the present invention as applied to the machining of the centrifugal nozzle of the aircraft engine of FIG. 1;
FIG. 4 shows a left side axial projection view of the tool of FIG. 3;
fig. 5 shows a schematic machining of a body of a tool according to an embodiment of the invention;
FIG. 6 shows an enlarged perspective view of a portion of the tip of FIG. 4;
fig. 7 shows an enlarged view of a portion of the tip of fig. 3.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As mentioned in the background section, the present invention relates to a tool for the conical section of small-sized nozzle orifices for precision machining of nozzle orifices of variable section for centrifugal nozzles of aircraft engines, and the present invention provides an improved tool because the tools used in the prior art are particularly easy to break, and scrap iron is not easy to discharge, the scrap rate is high, and it is essentially impossible to apply the tool to mass production.
In particular, the improved tool according to the invention is particularly suitable for machining the profile of the inner cavity of a nozzle orifice 1 and a conical section 2 connected to the nozzle orifice 1 of a centrifugal nozzle for an aircraft engine of the type shown in fig. 1 and 2, wherein fig. 1 shows a sectional view of a centrifugal nozzle for an aircraft engine according to one embodiment of the invention and fig. 2 shows a sectional view of a centrifugal nozzle for an aircraft engine according to another embodiment of the invention.
The aircraft engine centrifugal nozzle in fig. 1-2 has in common a variable-section nozzle orifice 1 and a conical section 2 connected to the nozzle orifice 1, the nozzle orifice 1 having a minimum cross-sectional diameter a, the conical section 2 having a maximum cross-sectional diameter B, and a transition arc 3 having a radius R between the nozzle orifice 1 and the conical section 2. In a specific embodiment, the diameter a ranges from 0.1 to 1mm and the diameter B ranges from 2 to 4mm, and one skilled in the art can imagine that the size of the whole area of the part to be machined is very small, and the conventional art tool is very difficult to reach the area, even if it can be reached, the tool in the normal state is basically in a concentric structure, similar to a thin needle, the rigidity of the tool is not good during machining, the tool is easy to break and shake during machining, and one tool can only machine 1 to 2 parts generally, so that the cost performance is low and the tool is basically impossible to be applied to mass production.
Based on the characteristics of the part to be machined, the invention provides an improved design of the tool 100, fig. 3 is a schematic diagram illustrating the tool 100 according to an embodiment of the invention applied to machining the aircraft engine centrifugal nozzle shown in fig. 1, and fig. 4 is a left-side axial projection view of the tool 100 shown in fig. 3, which is not shown in fig. 4 for clarity.
As shown in fig. 3-4, the cutting tool 100 comprises a tool shank 11, a tool body 12, and a cutting tip 13, wherein the cutting tip 13 is located at the end of the tool body 12, the tool body 12 is located between the cutting tip 13 and the tool shank 11, and the projection plane of the tool body 12 is located inside the projection plane of the tool shank 11 and is offset to one side of the center of the projection plane of the tool shank 11. That is, different from the conventional concentric cutter, the eccentric cutter body structure is adopted, so that a larger space channel is provided for scrap iron discharge and coolant conveying, a larger cutter body thickness can be obtained, the rigidity of the cutter body 12 is improved, the processing quality is easy to ensure, 10 parts can be processed by one cutter, the processing life can be prolonged by 5-10 times compared with the prior art, the requirement of batch production can be basically met, and the processing cost and the rejection rate are reduced. In detail, if the cutter body 12 is concentrically constructed, the cutter body can be formed with a very thin section and has a very small rigidity in order to make room for sufficient discharge of iron chips and conveyance of coolant. As is obvious from figure 3, the cutter body 12 with the eccentric structure is adopted, the lower part of the cutter body 12 can leave out the lower space of the whole aperture, a larger space channel is provided for scrap iron discharge and cooling liquid conveying, and the cutter is not easy to break due to scrap iron blockage and high-temperature incapability of cooling. It can also be seen from fig. 3 that the upper structure of the cutter body 12 substantially fills most of the upper space of the bore, greatly increasing the stiffness of the cutter body 12, and thus greatly increasing the life of the cutter body and even the entire cutter.
To facilitate the machining of the cutter body 12 having the eccentric structure, fig. 5 is a schematic view showing the machining of the cutter body of the cutter according to an embodiment of the present invention, and as shown in fig. 5, the cross-section of the cutter body 12 has an upper arc surface 112 and a lower arc surface 113, and the arc radii of the upper arc surface 112 and the lower arc surface 113 are the same. In one embodiment, the arc radius of the upper arc surface 112 and the lower arc surface 113 is 1.5 mm. Namely, during machining, two intersected circular machining surfaces are adopted for machining, for example, an upper arc surface 112 is turned by the circular machining surface with the diameter of 1.5mm, then the circular machining surface with the diameter of 1.5mm can be translated for a certain distance, and a lower arc surface 113 is also turned by the circular machining surface with the diameter of 1.5mm, so that the machining and positioning are particularly convenient, the method is particularly suitable for producing the wearing parts which need to be replaced only by using 10 times, and the production cost of the cutter is greatly reduced.
The detailed structure of the cutter will be described with reference to a partially enlarged view of the cutter. Fig. 6 is an enlarged perspective view of a portion of the tip of fig. 4, and as shown in fig. 6, the cutting tip 13 has a cutting tip rake angle 132 and a cutting tip relief angle 133, the cutting tip rake angle 132 is an angle that the cutting tip 13 is tilted forward in the machining direction, the cutting tip relief angle 133 is an angle that the cutting tip 13 is tilted backward away from the machining direction, and in one embodiment, the cutting tip rake angle 132 is 5 ° and the cutting tip relief angle 133 is 15 °. The front angle 132 of the tool nose is set to be forward-inclined by 5 degrees, so that the wear resistance of the tool can be improved, the rear angle 133 of the tool nose is set to be 15 degrees, so that scrap iron can be conveniently discharged, and the scrap iron is prevented from blocking a scratched processing surface.
In fact, the invention provides a great improvement from the machining process, namely, the machining direction of the cutter 100 is that the cutter 100 is fed from the minimum section with the diameter A of the oil injection hole 1 to the maximum section with the diameter B of the conical section 2 along the transition circular arc 3 with the radius R during the machining process, namely, reverse hook boring is carried out from inside to outside, and in order to adapt to the machining process of the reverse hook boring, in a specific embodiment, the cutter point 13 is downward when the cutter 100 is machined, so that the eccentric rigidity of the cutter back part is utilized, and the service life of the cutter is prolonged. That is, the conventional technology processes hole-shaped parts from outside to inside, but for the processing of the small-size nozzle orifice taper section, because the size is too small and the requirement on the precision of the profile is high, the iron filings generated by the outside-to-inside processing scratch the processed profile, and the fine scratches of the inner cavity of the nozzle-like parts affect the performance parameters of the assembly fuel nozzle, such as flow rate, flow direction, unevenness and the like, so the inner profile must not be scratched at all. Therefore, the invention adopts the reverse hook boring process, and the scrap iron generated by processing is discharged outwards to contact with the profile which is not processed yet, thereby overcoming the defects of the prior art and improving the processing precision and the yield.
Figure 7 shows an enlarged view of a portion of the tip of figure 3. as shown in figure 7, the tip 13 has a principal angle 136 in its longitudinal direction of 15 from vertical and a wedge angle 137 from horizontal of 15. The same angles are chosen for the lead angle 136 and the wedge angle 137 to facilitate machining of the tool, thereby reducing the cost of machining the tool. In another embodiment, the maximum thickness of the tip 13 is less than or equal to the diameter a. Because the minimum section of the oil spray hole 1 is provided with a machining allowance, and due to the existence of the main deflection angle 136, the maximum thickness position of the cutter point 13 and the minimum section of the oil spray hole 1 with the diameter A are horizontally staggered by a certain distance, so that the interference cannot be caused even if the sizes of the cutter point and the minimum section are the same, the set maximum thickness of the cutter point 13 basically achieves the maximum rigidity thickness under the condition of no interference, and the structural life of the cutter point is prolonged.
In a specific embodiment, a first transition taper surface 125 is provided between the tip 13 and the tool body 12, and the maximum taper angle of the first transition taper surface 125 is equal to or less than the taper angle of the tapered section 2. That is, as shown in fig. 7, the first transition taper surface 125 has a taper angle, and in order to avoid interference with the tool, the maximum taper angle is set to be equal to or smaller than the taper angle of the tapered section 2.
In another embodiment, a second transition taper 115 is provided between the tool body 12 and the tool holder 11, the second transition taper 115 having a maximum taper angle of 40 °. The structural design of the present embodiment is also to avoid interference of the tool during machining.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (10)
1. A cutter for a tapered section of a small-size nozzle is disclosed, wherein the cutter (100) is used for machining an oil spray hole (1) of a variable-section nozzle of an aircraft engine centrifugal nozzle and an inner cavity profile of a tapered section (2) connected with the oil spray hole (1), the minimum section diameter of the oil spray hole (1) is A, the maximum section diameter of the conical section (2) is B, a transition circular arc (3) with the radius of R is arranged between the oil spray hole (1) and the conical section (2), it is characterized in that the cutter (100) consists of a cutter bar (11), a cutter body (12) and a cutter point (13), wherein the tool nose (13) is positioned at the tail end of the tool body (12), the tool body (12) is positioned between the tool nose (13) and the tool bar (11), and the projection plane of the cutter body (12) is positioned inside the projection plane of the cutter rod (11) and is offset to one side of the center of the projection plane of the cutter rod (11).
2. The cutting tool as set forth in claim 1, characterized in that the cross section of the tool body (12) has an upper arc surface (112) and a lower arc surface (113), and the arc radii of the upper arc surface (112) and the lower arc surface (113) are the same.
3. Tool according to claim 2, characterized in, that the arc radius of the upper arc surface (112) and the lower arc surface (113) is 1.5 mm.
4. The tool according to claim 1, wherein the tip (13) has a tip rake angle (132) and a tip relief angle (133), the tip rake angle (132) being an angle at which the tip (13) tips forward in the machine direction, the tip relief angle (133) being an angle at which the tip (13) tips backward away from the machine direction, wherein the tip rake angle (132) is 5 ° and the tip relief angle (133) is 15 °.
5. Tool according to claim 1, characterized in that the tip (13) has a principal deviation angle (136) of 15 ° from vertical and a wedge angle (137) of 15 ° from horizontal in its longitudinal direction.
6. Tool according to claim 5, characterized in that the maximum thickness of the tip (13) is less than or equal to the diameter A.
7. Tool according to claim 1, characterized in, that a first transition taper (125) is provided between the tip (13) and the body (12), the maximum taper angle of the first transition taper (125) being equal to or less than the taper angle of the tapered cross-section (2).
8. The tool according to claim 1, characterized in that a second transition cone (115) is arranged between the tool body (12) and the tool shank (11), the second transition cone (115) having a maximum cone angle of 40 °.
9. The tool according to claim 1, characterized in that the machining direction of the tool (100) is fed from the smallest cross section of the injection hole (1) with diameter a along the transition arc (3) with radius R to the largest cross section of the conical cross section (2) with diameter B.
10. The tool according to claim 9, wherein the tip (13) is downward when the tool (100) is machining.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510757910.9A CN105252028B (en) | 2015-11-10 | 2015-11-10 | Cutter for small size spout tapered cross-section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510757910.9A CN105252028B (en) | 2015-11-10 | 2015-11-10 | Cutter for small size spout tapered cross-section |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105252028A true CN105252028A (en) | 2016-01-20 |
| CN105252028B CN105252028B (en) | 2018-03-09 |
Family
ID=55092123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510757910.9A Active CN105252028B (en) | 2015-11-10 | 2015-11-10 | Cutter for small size spout tapered cross-section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105252028B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106513723A (en) * | 2016-11-25 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Deep cavity turning cutter of curved surface structure and use method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5848862A (en) * | 1997-06-24 | 1998-12-15 | Antoun; Gregory S. | Boring bar with reverse mounted insert |
| CN200963686Y (en) * | 2006-11-09 | 2007-10-24 | 济南一机床集团有限公司 | Adjustable boring cutter device |
| CN201659296U (en) * | 2009-11-10 | 2010-12-01 | 天津市威斯曼光学仪器有限公司 | Splitting multi-stage multi-cutter spacing adjustable indexable boring cutter |
| CN201760617U (en) * | 2010-08-06 | 2011-03-16 | 威士精密工具(上海)有限公司 | CBN pore boring and milling cutter |
| CN102441682A (en) * | 2010-10-10 | 2012-05-09 | 孙生强 | Bidirectional side tool and process method thereof |
| CN102672215A (en) * | 2012-05-22 | 2012-09-19 | 珠海格力电器股份有限公司 | Pipe orifice trimming tool and tool bit thereof |
-
2015
- 2015-11-10 CN CN201510757910.9A patent/CN105252028B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5848862A (en) * | 1997-06-24 | 1998-12-15 | Antoun; Gregory S. | Boring bar with reverse mounted insert |
| CN200963686Y (en) * | 2006-11-09 | 2007-10-24 | 济南一机床集团有限公司 | Adjustable boring cutter device |
| CN201659296U (en) * | 2009-11-10 | 2010-12-01 | 天津市威斯曼光学仪器有限公司 | Splitting multi-stage multi-cutter spacing adjustable indexable boring cutter |
| CN201760617U (en) * | 2010-08-06 | 2011-03-16 | 威士精密工具(上海)有限公司 | CBN pore boring and milling cutter |
| CN102441682A (en) * | 2010-10-10 | 2012-05-09 | 孙生强 | Bidirectional side tool and process method thereof |
| CN102672215A (en) * | 2012-05-22 | 2012-09-19 | 珠海格力电器股份有限公司 | Pipe orifice trimming tool and tool bit thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106513723A (en) * | 2016-11-25 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Deep cavity turning cutter of curved surface structure and use method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105252028B (en) | 2018-03-09 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |