CN205714291U - The turbine multi-stage rotor parts of aero-engine and aero-engine - Google Patents
The turbine multi-stage rotor parts of aero-engine and aero-engine Download PDFInfo
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- CN205714291U CN205714291U CN201620545080.3U CN201620545080U CN205714291U CN 205714291 U CN205714291 U CN 205714291U CN 201620545080 U CN201620545080 U CN 201620545080U CN 205714291 U CN205714291 U CN 205714291U
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- wheel disc
- connecting hole
- aero
- engine
- bolt
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Abstract
The utility model discloses turbine multi-stage rotor parts and the aero-engine of a kind of aero-engine.The turbine multi-stage rotor parts of aero-engine, rotating shaft and multistage wheel disc, rotating shaft offer multiple axial arranged along rotating shaft and for bolted axle connecting hole, circumferentially distributed along rotating shaft of multiple axle connecting holes；Offer multiple axial arranged along multistage wheel disc and for bolted wheel disc connecting hole on multistage wheel disc, circumferentially distributed along multistage wheel disc of multiple wheel disc connecting holes；Axle connecting hole and wheel disc connecting hole one_to_one corresponding and coaxially lay, the first nose end of axle connecting hole docks with the first nose end of wheel disc connecting hole；First nose end of axle connecting hole and/or the first nose end of wheel disc connecting hole are provided for when bolt connects guiding bolt enter and realize the circular cone face that bolt is coaxial with connecting hole.Bolt can be facilitated to coordinate with the connection of connecting hole, also be able to guarantee simultaneously and be bolted to position, thus improve connection precision and connective stability.
Description
Technical field
This utility model relates to aero-engine technical field of structures, especially, relates to the turbine of a kind of aero-engine
Multi-stage rotor parts.Additionally, this utility model further relates to a kind of turbine multi-stage rotor parts including above-mentioned aero-engine
Aero-engine.
Background technology
In aero-engine, the rotor part of turbine is the acting parts of electromotor, owing to amount of work is big, typically along axle
The requirement of electromotor output work is met to design multi-stage rotor.Owing to the temperature of turbine part is high, pressure is high, rotating speed is high, because of
Matching relationship between this part is particularly important, it is to be ensured that part does not loosens.
And the rotor part of the turbine of existing aero-engine uses isometrical through hole and bolt to carry out secure fit even
Connect, long owing to installing stroke, occur as soon as radial deflection the most when mounted, now high by temperature, pressure high, rotating speed is high
After effect, connecting portion is easy to occur to connect the unstability loosening and connecting matching relationship, easily cause follow-up with one
Series of security questions.
Utility model content
This utility model provides turbine multi-stage rotor parts and the aero-engine of a kind of aero-engine, existing to solve
There is the rotor part of the turbine of aero-engine, easily cause radial deflection during assembling, in use owing to being chronically at
Temperature is high, pressure is high, rotating speed high condition, is susceptible to connect the technical problem loosening and connecting matching relationship unstability.
According to an aspect of the present utility model, it is provided that the turbine multi-stage rotor parts of a kind of aero-engine, rotating shaft with
And multistage wheel disc, rotating shaft offer multiple axial arranged along rotating shaft and for bolted axle connecting hole, multiple axles connect
Circumferentially distributed along rotating shaft of hole；Offer multiple axial arranged along multistage wheel disc and for bolted wheel disc on multistage wheel disc
Connecting hole, circumferentially distributed along multistage wheel disc of multiple wheel disc connecting holes；Axle connecting hole and wheel disc connecting hole one_to_one corresponding and coaxial
Laying, the first nose end of axle connecting hole docks with the first nose end of wheel disc connecting hole；First nose end of axle connecting hole and/or wheel disc
First nose end of connecting hole is provided for when bolt connects guiding bolt enter and realize the circular cone that bolt is coaxial with connecting hole
Face.
Further, the second nose end of axle connecting hole and/or the second nose end of wheel disc connecting hole are also configured as circular cone face.
Further, multistage wheel disc employing first order wheel disc axially overlaps with second level wheel disc and is connected；Wheel disc connecting hole bag
Include the first connecting hole being opened on first order wheel disc and the second connecting hole being opened on the wheel disc of the second level, the first connecting hole
Through with the second connecting hole and coaxial.
Further, the bolt upstream end of the first connecting hole and the second connecting hole is disposed as circular cone face.
Further, multistage wheel disc uses first order wheel disc, second level wheel disc and third level wheel disc axially to overlap connection；Wheel
Dish connecting hole includes the first connecting hole being opened on first order wheel disc, be opened on the wheel disc of the second level the second connecting hole and
The 3rd connecting hole being opened on third level wheel disc；Only have the first connecting hole through with the second connecting hole and coaxial, constitute short axle
Hole；First connecting hole, the second connecting hole and the 3rd connecting hole are through and coaxial, constitute long axis hole.
Further, short axis hole and long axis hole are along the circumferentially-spaced arrangement of multistage wheel disc.
Further, the bolt upstream end of the first connecting hole, the second connecting hole and the 3rd connecting hole is disposed as taper seat
Hole.
Further, between first order wheel disc and second level wheel disc, the lag bolt by being assemblied in short axis hole is affixed, the
One-level wheel disc, second level wheel disc and third level wheel disc are affixed by the stay bolt being assemblied in long axis hole；Lag bolt and long spiral shell
Bolt is along the circumferential interphase distribution of multistage wheel disc.
Further, the tapering of circular cone face is 1:30～60；Roughness≤0.8 of circular cone face.
According to another aspect of the present utility model, additionally provide a kind of aero-engine, including above-mentioned aero-engine
Turbine rotor parts.
This utility model has the advantages that
The turbine multi-stage rotor parts of this utility model aero-engine, use the combinative structure shape of rotating shaft and many step cones
Formula；In rotating shaft and multistage wheel disc, offer circumferentially distributed connecting hole respectively, and use rotating shaft and multistage wheel disc one_to_one corresponding
Version, with ensure connect stability；By the nose end of axle connecting hole with wheel disc connecting hole contact site is set to
Circular cone face, circular cone face is gradually reduced by the approach axis radial dimension of bolt, oblique by this gradually changeable being gradually reduced
Face guides bolt enter and make bolt and connecting hole tend to coaxial, it is possible to facilitate bolt to coordinate with the connection of connecting hole, the most also
Ensure that and be bolted to position, thus improve connection precision and connective stability, effectively prevent from being chronically at temperature height, pressure
Loosen connecting under power height, rotating speed high condition and the problem of connection unstability.
In addition to objects, features and advantages described above, this utility model also has other purpose, feature and excellent
Point.Below with reference to figure, this utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing of the part constituting the application is used for providing being further appreciated by of the present utility model, of the present utility model
Schematic description and description is used for explaining this utility model, is not intended that improper restriction of the present utility model.At accompanying drawing
In:
Fig. 1 is the structural representation of the turbine multi-stage rotor parts of the aero-engine of this utility model preferred embodiment；
Fig. 2 is the structural representation of the long axis hole of this utility model preferred embodiment；
Fig. 3 is the structural representation of the short axis hole of this utility model preferred embodiment；
Fig. 4 is the structural representation of the multistage wheel disc of this utility model preferred embodiment.
Marginal data:
1, rotating shaft；2, multistage wheel disc；201, first order wheel disc；2011, the first connecting hole；202, second level wheel disc；2021、
Second connecting hole；203, third level wheel disc；2031, the 3rd connecting hole；3, axle connecting hole；4, wheel disc connecting hole；5, circular cone face；
6, short axis hole；7, long axis hole；8, lag bolt；9, stay bolt.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail, but this utility model can be by following
The multitude of different ways limiting and covering is implemented.
Fig. 1 is the structural representation of the turbine multi-stage rotor parts of the aero-engine of this utility model preferred embodiment；
Fig. 2 is the structural representation of the long axis hole of this utility model preferred embodiment；Fig. 3 is the short axle of this utility model preferred embodiment
The structural representation in hole；Fig. 4 is the structural representation of the multistage wheel disc of this utility model preferred embodiment.
As depicted in figs. 1 and 2, the turbine multi-stage rotor parts of the aero-engine of the present embodiment, rotating shaft 1 and many step cones
Dish 2, rotating shaft 1 offers multiple axial arranged along rotating shaft 1 and for bolted axle connecting hole 3, multiple axle connecting hole 3 edges
Rotating shaft 1 circumferentially distributed；Offer multiple axial arranged along multistage wheel disc 2 and for bolted wheel disc on multistage wheel disc 2
Connecting hole 4, multiple wheel disc connecting holes 4 are circumferentially distributed along multistage wheel disc 2；Axle connecting hole 3 and wheel disc connecting hole 4 one_to_one corresponding and
Coaxial laying, the first nose end of axle connecting hole 3 docks with the first nose end of wheel disc connecting hole 4；First nose end of axle connecting hole 3
And/or the first nose end of wheel disc connecting hole 4 is provided for when bolt connects guiding bolt to enter and realize bolt and connecting hole
Coaxial circular cone face 5.The turbine multi-stage rotor parts of aero-engine, use the combinative structure form of rotating shaft 1 and many step cones；
In rotating shaft 1 and multistage wheel disc 2, offer circumferentially distributed connecting hole respectively, and use rotating shaft 1 and multistage wheel disc 2 one_to_one corresponding
Version, with ensure connect stability；By the nose end of axle connecting hole 3 with wheel disc connecting hole 4 contact site is arranged
For circular cone face 5, circular cone face 5 is gradually reduced by the approach axis radial dimension of bolt, by this gradual change being gradually reduced
Property inclined-plane guide bolt enter and make bolt and connecting hole tend to coaxial, it is possible to facilitate bolt to coordinate with the connection of connecting hole, together
Time also be able to guarantee and be bolted to position, thus improve connection precision and connective stability, effectively prevent from being chronically at temperature
Loosen connecting under height, pressure height, rotating speed high condition and the problem of connection unstability.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the second nose end of axle connecting hole 3 and/or the of wheel disc connecting hole 4
Two nose ends are also configured as circular cone face 5.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, multistage wheel disc 2 uses first order wheel disc 201 and second level wheel disc
202 axially overlap connection.Wheel disc connecting hole 4 includes the first connecting hole 2011 being opened on first order wheel disc 201 and offers
The second connecting hole 2021 on second level wheel disc 202.First connecting hole 2011 is through and coaxial with the second connecting hole 2021.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the bolt of the first connecting hole 2011 and the second connecting hole 2021 enters
Enter end and be disposed as circular cone face 5.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, multistage wheel disc 2 uses first order wheel disc 201, second level wheel disc
202 and third level wheel disc 203 axially overlap connection.Wheel disc connecting hole 4 includes the first connection being opened on first order wheel disc 201
Hole 2011, the second connecting hole 2021 being opened on second level wheel disc 202 and the 3rd company being opened on third level wheel disc 203
Connect hole 2031.Only have the first connecting hole 2011 through and coaxial with the second connecting hole 2021, constitute short axis hole 6.First connecting hole
2011, the second connecting hole 2021 and the 3rd connecting hole 2031 are through and coaxial, constitute long axis hole 7.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, in the present embodiment, short axis hole 6 and long axis hole 7 are along between the circumference of multistage wheel disc 2
Every arrangement.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, in the present embodiment, first connecting hole the 2011, second connecting hole 2021 and the 3rd
The bolt upstream end of connecting hole 2031 is disposed as circular cone face 5.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, by dress between first order wheel disc 201 and second level wheel disc 202
The lag bolt 8 being assigned in short axis hole 6 is affixed.First order wheel disc 201, second level wheel disc 202 and third level wheel disc 203 are by dress
The stay bolt 9 being assigned in long axis hole 7 is affixed.Lag bolt 8 and stay bolt 9 are along the circumferential interphase distribution of multistage wheel disc 2.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the tapering of circular cone face 5 is 1:30～60.Circular cone face 5 thick
Rugosity≤0.8.The tapering making circular cone face 5 is between 1:30 to 1:60, thus preferably realizes guiding and the function of self-locking.
The aero-engine of the present embodiment, including the turbine rotor parts of above-mentioned aero-engine.
During enforcement, it is provided that the taper seat centering assembling structure of a kind of engine rotor assemblies, to solve multi-stage rotor dress
Join problem.The turbine rotor of the present invention has three grades, including rotating shaft 1, first order wheel disc 201, second level wheel disc 202, third level wheel
Dish 203.Five lag bolts 8 connect first order wheel disc 201, second level wheel disc 202 and rotating shaft 1.Five stay bolts 9 connect the first order
Wheel disc 201, second level wheel disc 202, third level wheel disc 203 and rotating shaft 1.First order wheel disc 201, second level wheel disc 202 and rotating shaft 1
Along the circumferential direction being evenly equipped with ten circular cone faces 5, third level wheel disc 203 is along the circumferential direction evenly equipped with five circular cone faces 5.Rotating shaft
Being connected with ten bolts between 1 with wheel disc, bolt is felt relieved with the employing taper seat that coordinates of rotating shaft 1, wheel disc.
First order wheel disc 201, second level wheel disc 202 and rotating shaft 1 are along the circumferential direction evenly equipped with ten circular cone faces 5, long spiral shell
Bolt 9, lag bolt 8 are uniformly distributed and are assemblied in these ten circular cone faces 5.Third level wheel disc 203 is along the circumferential direction evenly equipped with five
Individual circular cone face 5, is only equipped with five root length bolts 9.
Rotating shaft 1, first order wheel disc 201, second level wheel disc 202, the center of bolt hole of third level wheel disc 203 are Φ
100mm-Φ200mm.Preferably, the center of bolt hole is Φ 160mm.In bolt hole center, add with axle left side for starting point
Each and every one taper hole of work ten, taper hole initial diameter is Φ 15.8mm (+0.020mm), and tapering is 1:48.Long taper hole is through to rotating shaft 1 He
First order wheel disc 201, second level wheel disc 202, third level wheel disc 203, as shown in Figure 2.Short taper hole is through to rotating shaft 1 and the first order
Wheel disc 201, second level wheel disc 202, the roughness of taper hole is not higher than 0.8, as shown in Figure 3.
Five lag bolts 8 and five root length bolts 9 are taper seat with wheel disc, the taper hole registration interface designs of rotating shaft 1, taper seat
Initial diameter is Φ 15.77mm (+0.04mm～+0.01mm), 0.03mm less than the initial diameter of wheel disc, rotating shaft 1, to ensure spiral shell
Bolt can be encased in dish axle.The taper seat tapering of bolt is 1:48, with wheel disc, rotating shaft 1 tapering as, taper seat coarse
Degree not higher than 0.4, can guarantee that identical taper seat coordinates.Determine that the centering of dish axle can by the fit system of this taper seat
Lean on.
Ensure when processing and assembling:
(1) each taper hole ensures a feed man-hour adding, and can not have step in hole, and size is once formed；
(2) processing guarantee dish, the roughness of axial cone hole are not higher than 0.8, and the roughness of the bolt circle conical surface is not higher than 0.4.With
After ensureing bolts assemblies, the fit quality of taper seat and taper hole is high, and centering is reliable；
(3), after bolts assemblies is tightened, need to check that bolt end face and axial end have the gap of 0.5～1.0, to guarantee bolt
The taper seat in taper seat and hole is in the state that tightness coordinates.
The turbine multi-stage rotor parts of aero-engine of the present invention have a following beneficial effect:
(1) present invention is coordinated by taper seat, and adjective-centre structure is reliable and stable；
(2) present invention can protect qualified for the taper hole dimensioned of three wheel discs and a board shaft during time processing
Demonstrate,prove the concordance of fit dimension between different part；
(3) assemble qualified rotor assembly, work need to be balanced, it is ensured that assembly descends smooth running in working order,
Vibrate little.
Enforcement step:
(1) first order wheel disc 201, second level wheel disc 202 and rotating shaft 1 are connected with five lag bolts 8, and check bolt
End face and axial end gap, and carry out balancing work；
(2) third level wheel disc 203 and five root length bolts 9 are connected with said modules, and check bolt end face and axle head
Gap, face, and again carry out the balancing work of whole assembly.
The foregoing is only preferred embodiment of the present utility model, be not limited to this utility model, for this
For the technical staff in field, this utility model can have various modifications and variations.All in spirit of the present utility model and principle
Within, any modification, equivalent substitution and improvement etc. made, within should be included in protection domain of the present utility model.
Claims (10)
1. turbine multi-stage rotor parts for aero-engine, rotating shaft (1) and multistage wheel disc (2),
It is characterized in that,
Offer multiple axial arranged along described rotating shaft (1) in described rotating shaft (1) and be used for bolted axle connecting hole (3),
Circumferentially distributed along described rotating shaft (1) of multiple described axle connecting holes (3)；
Offer multiple axial arranged along described multistage wheel disc (2) on described multistage wheel disc (2) and be used for bolted wheel disc
Connecting hole (4), circumferentially distributed along described multistage wheel disc (2) of multiple described wheel disc connecting holes (4)；
Described axle connecting hole (3) and described wheel disc connecting hole (4) one_to_one corresponding and coaxially lay, the of described axle connecting hole (3)
One nose end docks with the first nose end of described wheel disc connecting hole (4)；
First nose end of described axle connecting hole (3) and/or the first nose end of described wheel disc connecting hole (4) are provided for bolt even
Bolt is guided to enter and realize circular cone face (5) that bolt is coaxial with connecting hole when connecing.
The turbine multi-stage rotor parts of aero-engine the most according to claim 1, it is characterised in that
Second nose end of described axle connecting hole (3) and/or the second nose end of described wheel disc connecting hole (4) are also configured as circular cone face
(5)。
The turbine multi-stage rotor parts of aero-engine the most according to claim 2, it is characterised in that
Described multistage wheel disc (2) employing first order wheel disc (201) axially overlaps with second level wheel disc (202) and is connected；
Described wheel disc connecting hole (4) includes the first connecting hole (2011) being opened on described first order wheel disc (201) and opens
The second connecting hole (2021) being located on described second level wheel disc (202),
Described first connecting hole (2011) is through and coaxial with described second connecting hole (2021).
The turbine multi-stage rotor parts of aero-engine the most according to claim 3, it is characterised in that
The bolt upstream end of described first connecting hole (2011) and described second connecting hole (2021) is disposed as circular cone face
(5)。
The turbine multi-stage rotor parts of aero-engine the most according to claim 2, it is characterised in that
Described multistage wheel disc (2) uses first order wheel disc (201), second level wheel disc (202) and third level wheel disc (203) axially to fold
Close and connect；
Described wheel disc connecting hole (4) includes the first connecting hole (2011) being opened on described first order wheel disc (201), is opened in
The second connecting hole (2021) on described second level wheel disc (202) and be opened in the 3rd on described third level wheel disc (203)
Connecting hole (2031)；
Only have described first connecting hole (2011) through and coaxial with described second connecting hole (2021), constitute short axis hole (6)；
Described first connecting hole (2011), described second connecting hole (2021) and described 3rd connecting hole (2031) are through and same
Axle, constitutes long axis hole (7).
The turbine multi-stage rotor parts of aero-engine the most according to claim 5, it is characterised in that
Described short axis hole (6) and described long axis hole (7) are along the circumferentially-spaced arrangement of described multistage wheel disc (2).
The turbine multi-stage rotor parts of aero-engine the most according to claim 5, it is characterised in that
The bolt of described first connecting hole (2011), described second connecting hole (2021) and described 3rd connecting hole (2031) enters
End is disposed as circular cone face (5).
The turbine multi-stage rotor parts of aero-engine the most according to claim 7, it is characterised in that
Between described first order wheel disc (201) and described second level wheel disc (202) short by be assemblied in described short axis hole (6)
Bolt (8) is affixed,
Described first order wheel disc (201), described second level wheel disc (202) and described third level wheel disc (203) are by being assemblied in
Stay bolt (9) in described long axis hole (7) is affixed；
Described lag bolt (8) and described stay bolt (9) are along the circumferential interphase distribution of described multistage wheel disc (2).
The turbine multi-stage rotor parts of aero-engine the most according to any one of claim 1 to 8, it is characterised in that
The tapering of described circular cone face (5) is 1:30～60；
Roughness≤0.8 of described circular cone face (5).
10. an aero-engine, it is characterised in that
Turbine multi-stage rotor parts including the aero-engine according to any one of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620545080.3U CN205714291U (en) | 2016-06-07 | 2016-06-07 | The turbine multi-stage rotor parts of aero-engine and aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620545080.3U CN205714291U (en) | 2016-06-07 | 2016-06-07 | The turbine multi-stage rotor parts of aero-engine and aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205714291U true CN205714291U (en) | 2016-11-23 |
Family
ID=57301150
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620545080.3U Active CN205714291U (en) | 2016-06-07 | 2016-06-07 | The turbine multi-stage rotor parts of aero-engine and aero-engine |
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| CN (1) | CN205714291U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113795A (en) * | 2018-10-23 | 2019-01-01 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine rotor leaf dish |
| CN109268473A (en) * | 2018-11-26 | 2019-01-25 | 中国航发南方工业有限公司 | The method for processing and assembling of dish axle connection structure and dish axle connection structure |
| CN110132556A (en) * | 2019-04-30 | 2019-08-16 | 中国航发湖南动力机械研究所 | Modularization turbine test part and its test method |
| CN111485954A (en) * | 2020-04-16 | 2020-08-04 | 中国航发沈阳发动机研究所 | Rotor wheel disc assembling structure and assembling method thereof |
| CN111485955A (en) * | 2020-04-16 | 2020-08-04 | 中国航发沈阳发动机研究所 | Rotor disk assembly structure |
| CN114893253A (en) * | 2022-04-08 | 2022-08-12 | 中国航发沈阳发动机研究所 | Reliable rotor connecting structure and method for high-temperature component |
-
2016
- 2016-06-07 CN CN201620545080.3U patent/CN205714291U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113795A (en) * | 2018-10-23 | 2019-01-01 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine rotor leaf dish |
| CN109268473A (en) * | 2018-11-26 | 2019-01-25 | 中国航发南方工业有限公司 | The method for processing and assembling of dish axle connection structure and dish axle connection structure |
| CN110132556A (en) * | 2019-04-30 | 2019-08-16 | 中国航发湖南动力机械研究所 | Modularization turbine test part and its test method |
| CN110132556B (en) * | 2019-04-30 | 2021-11-12 | 中国航发湖南动力机械研究所 | Modular turbine test piece and test method thereof |
| CN111485954A (en) * | 2020-04-16 | 2020-08-04 | 中国航发沈阳发动机研究所 | Rotor wheel disc assembling structure and assembling method thereof |
| CN111485955A (en) * | 2020-04-16 | 2020-08-04 | 中国航发沈阳发动机研究所 | Rotor disk assembly structure |
| CN111485954B (en) * | 2020-04-16 | 2022-09-30 | 中国航发沈阳发动机研究所 | Rotor wheel disc assembling structure and assembling method thereof |
| CN114893253A (en) * | 2022-04-08 | 2022-08-12 | 中国航发沈阳发动机研究所 | Reliable rotor connecting structure and method for high-temperature component |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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| CP01 | Change in the name or title of a patent holder |
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. |