CN205315051U - Terminal surface graphite sealing device and aviation air turbine starter - Google Patents
Terminal surface graphite sealing device and aviation air turbine starter Download PDFInfo
- Publication number
- CN205315051U CN205315051U CN201620025707.2U CN201620025707U CN205315051U CN 205315051 U CN205315051 U CN 205315051U CN 201620025707 U CN201620025707 U CN 201620025707U CN 205315051 U CN205315051 U CN 205315051U
- Authority
- CN
- China
- Prior art keywords
- housing
- graphite
- face
- sealing
- seal device
- 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
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 79
- 229910002804 graphite Inorganic materials 0.000 title claims abstract description 79
- 239000010439 graphite Substances 0.000 title claims abstract description 79
- 238000007789 sealing Methods 0.000 title claims abstract description 50
- 239000007858 starting material Substances 0.000 title claims abstract description 14
- 230000006835 compression Effects 0.000 claims abstract description 34
- 238000007906 compression Methods 0.000 claims abstract description 34
- 230000005540 biological transmission Effects 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 claims description 22
- 230000007246 mechanism Effects 0.000 claims description 5
- 230000000694 effects Effects 0.000 abstract description 14
- 230000008901 benefit Effects 0.000 abstract description 6
- 239000010687 lubricating oil Substances 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 4
- 239000005060 rubber Substances 0.000 description 4
- 230000001360 synchronised effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 239000013536 elastomeric material Substances 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 230000003245 working effect Effects 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 230000033558 biomineral tissue development Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920003051 synthetic elastomer Polymers 0.000 description 1
- 239000005061 synthetic rubber Substances 0.000 description 1
Landscapes
- Sealing Devices (AREA)
Abstract
The utility model discloses a terminal surface graphite sealing device and aviation air turbine starter, this terminal surface graphite sealing device include: the casing, this casing is equipped with first mounting groove along an axial terminal surface, and the graphite annulus interference is installed in first mounting groove, the casing is equipped with a plurality of mounting holes that are used for installing compression spring along axial another terminal surface, and a plurality of mounting holes arrange evenly along the circumference of casing that one side of casing is through installing the bearing frame baffle of replacing the bearing bore in the compression spring of mounting hole, and the cover is equipped with the relative sealed runway that sets up with the graphite annulus on the transmission shaft, and sealed runway is connected with the transmission shaft linkage, the graphite annulus through a plurality of compression spring apply in the effort of casing compress tightly on sealed runway and sealed runway between constitute the primary seal interface. Its simple structure, leakproofness are good, and have long service life's advantage, and compression spring's elasticity can remove to sealed runway heading the graphite annulus and play compensation, assurance terminal surface graphite sealing device's sealed effect.
Description
Technical field
The utility model relates to sealing device for rotary shaft field, especially, it relates to a kind of end face graphite seal device. In addition, the utility model also relates to a kind of aviation air turbine starter comprising above-mentioned end face graphite seal device.
Background technology
Its performance, reliability, life-span and maintenance are had great effect by the sealing of aviation air turbine starter, and the fault and the accident that cause due to sealing problem happen occasionally. Along with aviation air turbine starter performance improves, turibine rotor rotating speed strengthens, and operating pressure, working temperature raise so that the working conditions of sealing is day by day severe, and the validity and reliability of sealing becomes more and more important.
Existing aviation air turbine starter main bearing babbitting jig chamber sealing device for rotary shaft is a kind of synthetic rubber lip shape seal device, is normally made up of rubbery outer cover, metallic framework, primary seal lip, dust-proof secondary lip, tight hoop spring. During work, by tightly binding round, reactive force is passed between primary seal lip and turning axle housing by spring, and mineralization pressure forms dynamic radial seal, and the laminating on rubbery outer cover and surface, bearing chamber is used for auxiliary seal and realizes its sealing function. It is air outside annular seal space, it is lubricating oil-the air mixture a little less than ambient atmospheric pressure in annular seal space, by means of chamber outer air through primary seal interface and auxiliary seal interface to a small amount of leakage in chamber, prevent the lubricating oil in chamber to external leakage.
By tightly binding round, reactive force is passed between primary seal lip and turning axle existing rubber lip shape seal device by spring, and mineralization pressure forms circumference dynamic seal, and the primary seal lip of elastomeric material cannot bear higher operating line speed. Primary seal face is linear contact lay, cannot suppress the fragmentary leakage of lubricating oil, and sealing property is good not. And after rubber lip shape seal device occurs to continue abrasion, due to the reasons in structure of primary seal lip, when, after sealing surface wear, sealing lip easily lost efficacy, sealing property is deteriorated, and the general life-span is not long. Elastomeric material can not at high temperature work, and the lasting friction between the elastomeric material of primary seal lip and turning axle can improve its working temperature further, and therefore, the working temperature of rubber lip shape seal device is lower.
Practical novel content
The utility model provides a kind of end face graphite seal device and aviation air turbine starter, exists cannot bear higher operating line speed, poor sealing, working temperature is low and work-ing life is short technical problem to solve existing rubber lip shape seal device.
The technical solution adopted in the utility model is as follows:
According to an aspect of the present utility model, it is provided that a kind of end face graphite seal device, for the bearing chamber of transmission shaft of obturaging, end face graphite seal device comprises:
Housing, this housing end face vertically is provided with the first installation groove for installing graphite annulus, and graphite annulus interference is installed in the first installation groove;
Housing other end vertically is provided with the multiple open holess for installing compression spring, multiple open holes is evenly arranged along the circumference of housing, the bearing support baffle plate in bearing chamber is supported in the side of housing through being installed on the compression spring of open holes, being arranged with the sealing runway being oppositely arranged with graphite annulus on transmission shaft, sealing runway and transmission shaft are connected;
Graphite annulus through multiple compression spring apply in the reactive force of housing be pressed in sealing runway on and and sealing runway between form primary seal interface.
Further, the periphery wall of housing is provided with the 2nd installation groove for installing sealing-ring, is tightly connected through sealing-ring between the bearing support in housing and bearing chamber.
Further, the axial width of the 2nd installation groove is greater than the external diameter of sealing-ring, and the radial height of the 2nd installation groove is less than the external diameter of sealing-ring.
Further, the rotation-preventing mechanism for preventing housing circumference from rotating it is provided with between the bearing support baffle plate in housing and bearing chamber.
Further, rotation-preventing mechanism comprises the anti-rotation boss being positioned on housing to arrange on the end face of open holes, corresponding on bearing support baffle plate is provided with the opening mating to limit housing circumference with anti-rotation boss and rotating.
Further, the radial position of multiple open holes on housing is equal, and the open holes on two relative side on housing, the first installation groove misplace layout in the radial direction of housing.
Further, the quantity of open holes is eight, and the circumference along housing is evenly arranged.
Further, the cross section vertically of graphite annulus is step surface.
According to another aspect of the present utility model, a kind of aviation air turbine starter is also provided, above-mentioned end face graphite seal device is set in the main bearing babbitting jig chamber of this aviation air turbine starter.
The utility model has following useful effect:
The utility model end face graphite seal device, by being circumferentially evenly arranged multiple open holes at housing end face vertically, and the compression spring through being installed in open holes supports the bearing support baffle plate in bearing chamber, and housing is arranging the opposing end surface interference edge dress graphite annulus of open holes, to keep synchronous static or move axially with housing; Compression spring through housing effect to graphite annulus, make to form primary seal interface between graphite annulus and sealing runway, owing to compression spring does not act directly on graphite annulus, while ensureing sealing effect, graphite annulus can not be damaged, and compression spring is applicable to the high environment of temperature, has the advantage of long service life, graphite annulus is moved play compensating action to sealing runway direction by the spring energy of compression spring, ensures the sealing effect of end face graphite seal device.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage. Below with reference to accompanying drawings, the utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing of a part forming the application is used to provide of the present utility model it is further understood that schematic description and description of the present utility model is for explaining the utility model, does not form improper restriction of the present utility model. In the accompanying drawings:
Fig. 1 is the one-piece construction schematic diagram of the utility model preferred embodiment end face graphite seal device;
Fig. 2 is the diagrammatic cross-section of Fig. 1 along A-A;
Fig. 3 is the installation structural representation of the utility model preferred embodiment end face graphite seal device.
Description of reference numerals:
1, housing; 11, the first installation groove; 12, the 2nd installation groove; 13, open holes; 14, anti-rotation boss;
2, graphite annulus;
3, compression spring;
4, sealing-ring;
5, bearing support;
6, bearing support baffle plate;
7, runway is sealed.
Embodiment
It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually. Below with reference to the accompanying drawings and come the utility model is described in detail in conjunction with the embodiments.
Preferred embodiment of the present utility model provides a kind of end face graphite seal device, for the bearing chamber of transmission shaft of obturaging, referring to figs. 1 through Fig. 3, the present embodiment end face graphite seal device comprises: housing 1, this housing 1 end face vertically is provided with the first installation groove 11 for installing graphite annulus 2, and graphite annulus 2 interference is installed in the first installation groove 11; Housing 1 other end vertically is provided with the multiple open holess 13 for installing compression spring 3, multiple open holes 13 is evenly arranged along the circumference of housing 1, the bearing support baffle plate 6 in bearing chamber is supported in the side of housing 1 through being installed on the compression spring 3 of open holes 13, being arranged with the sealing runway 7 being oppositely arranged with graphite annulus 2 on transmission shaft, sealing runway 7 is connected with transmission shaft; Graphite annulus 2 through multiple compression spring 3 apply in the reactive force of housing 1 be pressed in sealing runway 7 on and and sealing runway 7 between form primary seal interface.
The present embodiment is by being circumferentially evenly arranged multiple open holes 13 at housing 1 end face vertically, and the compression spring 3 through being installed in open holes 13 supports the bearing support baffle plate 6 in bearing chamber, and housing 1 is arranging the opposing end surface interference edge dress graphite annulus 2 of open holes 13, so that graphite annulus 2 keeps synchronous static or move axially with housing 1; Compression spring 3 acts on to graphite annulus 2 through housing 1, make to form primary seal interface between graphite annulus 2 and sealing runway 7, owing to compression spring 3 does not act directly on graphite annulus 2, while ensureing sealing effect, graphite annulus 2 can not be damaged, and compression spring 3 is applicable to the high environment of temperature, has the advantage of long service life, graphite annulus 2 is moved play compensating action to sealing runway 7 direction by the spring energy of compression spring 3, ensures the sealing effect of end face graphite seal device.
In the present embodiment, with reference to Fig. 1, the quantity of open holes 13 is eight, and the circumference along housing 1 is evenly arranged. Adopt that the compression spring 3 of eight same models, specification and stability factor is uniform to be installed in the open holes 13 of housing 1. In the present embodiment, by bearing support baffle plate 6 and sealing runway 7, tightness system is fixed on bearing support 5, wherein, sealing runway 7 rotates together along with transmission shaft, eight compression springs 3 are located between housing 1 and bearing support baffle plate 6, graphite annulus 2 is compressed to sealing runway 7 direction by compression spring 3 by housing 1 so that form primary seal interface between graphite annulus 2 and sealing runway.
Preferably, the periphery wall of housing 1 is provided with the 2nd installation groove 12 for installing sealing-ring 4, is tightly connected through sealing-ring 4 between the bearing support 5 in housing 1 and bearing chamber. It is located in the 2nd installation groove 12 with reference to Fig. 2 and Fig. 3, O RunddichtringO, to form auxiliary seal face between housing 1 and bearing chamber. The present embodiment realizes the sealing to lubricating oil in bearing chamber by primary seal interface and auxiliary seal face.It it is the air having certain pressure coming from air turbo outside bearing chamber, it is the lubricating oil a little less than barometric point-air-oil-mixture medium gas in chamber, by means of chamber outer air through primary seal interface and auxiliary seal interface to a small amount of leakage in chamber, prevent the lubricating oil in chamber to external leakage.
Preferably, in the present embodiment, the axial width of the 2nd installation groove 12 is greater than the external diameter of sealing-ring 4, and the radial height of the 2nd installation groove 12 is less than the external diameter of sealing-ring 4, thus meet sealing-ring 4 miles of relative movement vertically on housing 1, avoid sealing-ring 4 to block and destroy.
Preferably, the rotation-preventing mechanism for preventing housing 1 circumference from rotating it is provided with between the bearing support baffle plate 6 in housing 1 and bearing chamber. In the present embodiment, housing 1 is provided with two anti-rotation boss 14, two anti-rotation boss 14 are positioned on the end face arranging open holes 13 on housing 1, on bearing support baffle plate 6, corresponding being provided with mates with anti-rotation boss 14 to limit the circumferential opening rotated of housing 1, is inserted by anti-rotation boss 14 and realizes circumferential fixing in the opening of bearing support baffle plate 6. In the present embodiment, sealing runway 7 is sheathed on transmission shaft, and interference is installed to ensure the synchronous rotary with transmission shaft.
In the present embodiment, it may be preferred that the radial position of multiple open holes 13 on housing 1 is equal, and on housing 1, the open holes 13, first on two relative side is installed groove 11 and is misplaced in the radial direction of housing 1 layout. This structure makes open holes 13 can avoid graphite annulus 2, increases the degree of depth of open holes 13, reduces the axial size of tightness system. The present embodiment adopts that the compression spring 3 of 8 same models, specification, stability factor is uniform to be installed in the open holes 13 of housing 1, it does not have be applied directly on graphite annulus 2, can not be damaged by graphite annulus 2 in guarantee sealing effect simultaneously. And compression spring 3 compacting is highly low, required installation space is little, due in the open holes 13 being installed on housing 1, make whole tightness system length in the axial direction very short after installing, compact construction, moreover it is possible to reduce the vibration of graphite annulus 2 and axially alter, extend the work-ing life of tightness system.
In order to improve the work-ing life of end face graphite seal device further, it may be preferred that the structure design of the present embodiment graphite annulus 2 and sealing runway 7 contact part is the structure formation of step type, and namely the cross section vertically of graphite annulus 2 is step surface. So that after abrasion occurs in graphite annulus 2, moving to sealing runway 7 direction and play the effect of compensation by graphite annulus 2 under spring force, keep the sealing effect of face seals.
According to another aspect of the present utility model, a kind of aviation air turbine starter is also provided, the end face graphite seal device of above-described embodiment is set in the main bearing babbitting jig chamber of this aviation air turbine starter.
Can learn from above description, the present embodiment is by being circumferentially evenly arranged multiple open holes at housing end face vertically, and the compression spring through being installed in open holes supports the bearing support baffle plate in bearing chamber, and housing is arranging the opposing end surface interference edge dress graphite annulus of open holes, to keep synchronous static or move axially with housing; Compression spring through housing effect to graphite annulus, make to form primary seal interface between graphite annulus and sealing runway, owing to compression spring does not act directly on graphite annulus, while ensureing sealing effect, graphite annulus can not be damaged, and compression spring is applicable to the high environment of temperature, has the advantage of long service life, graphite annulus is moved play compensating action to sealing runway direction by the spring energy of compression spring, ensures the sealing effect of end face graphite seal device.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment of doing, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (9)
1. an end face graphite seal device, for the bearing chamber of transmission shaft of obturaging, it is characterised in that, described end face graphite seal device comprises:
Housing (1), described housing (1) end face vertically is provided with the first installation groove (11) for installing graphite annulus (2), and described graphite annulus (2) interference is installed in described first installation groove (11);
Described housing (1) other end vertically is provided with the multiple open holess (13) for installing compression spring (3), described multiple open holes (13) is evenly arranged along the circumference of described housing (1), the bearing support baffle plate (6) in described bearing chamber is supported in the side of described housing (1) through being installed on the compression spring (3) of described open holes (13), being arranged with the sealing runway (7) being oppositely arranged with described graphite annulus (2) on transmission shaft, described sealing runway (7) and described transmission shaft are connected;
Described graphite annulus (2) through multiple described compression spring (3) apply in the reactive force of described housing (1) be pressed in described sealing runway (7) upper and and described sealing runway (7) between form primary seal interface.
2. end face graphite seal device according to claim 1, it is characterised in that,
The periphery wall of described housing (1) is provided with the 2nd installation groove (12) for installing sealing-ring (4), is tightly connected through described sealing-ring (4) between the bearing support (5) in described housing (1) and described bearing chamber.
3. end face graphite seal device according to claim 2, it is characterised in that,
The axial width of described 2nd installation groove (12) is greater than the external diameter of described sealing-ring (4), and the radial height of described 2nd installation groove (12) is less than the external diameter of described sealing-ring (4).
4. end face graphite seal device according to claim 1, it is characterised in that,
The rotation-preventing mechanism for preventing described housing (1) circumference from rotating it is provided with between the bearing support baffle plate (6) in described housing (1) and described bearing chamber.
5. end face graphite seal device according to claim 4, it is characterised in that,
Described rotation-preventing mechanism comprises and is positioned on described housing (1) the anti-rotation boss (14) arranging on the end face of described open holes (13), and described bearing support baffle plate (6) is upper corresponding is provided with opening mate to limit described housing (1) circumference rotation with described anti-rotation boss (14).
6. end face graphite seal device according to claim 1, it is characterised in that,
The radial position of described multiple open holes (13) on described housing (1) is equal, and described housing (1) goes up the described open holes (13) on two relative side, described first installation groove (11) misplaces layout in the radial direction of described housing (1).
7. end face graphite seal device according to claim 6, it is characterised in that,
The quantity of described open holes (13) is eight, and the circumference along described housing (1) is evenly arranged.
8. according to the arbitrary described end face graphite seal device of claim 1 to 7, it is characterised in that,
The cross section vertically of described graphite annulus (2) is step surface.
9. an aviation air turbine starter, it is characterised in that, in the main bearing babbitting jig chamber of described aviation air turbine starter arrange as arbitrary in claim 1 to 8 as described in end face graphite seal device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620025707.2U CN205315051U (en) | 2016-01-12 | 2016-01-12 | Terminal surface graphite sealing device and aviation air turbine starter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620025707.2U CN205315051U (en) | 2016-01-12 | 2016-01-12 | Terminal surface graphite sealing device and aviation air turbine starter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205315051U true CN205315051U (en) | 2016-06-15 |
Family
ID=56202302
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620025707.2U Active CN205315051U (en) | 2016-01-12 | 2016-01-12 | Terminal surface graphite sealing device and aviation air turbine starter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205315051U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105972216A (en) * | 2016-07-22 | 2016-09-28 | 中国航空动力机械研究所 | Circumferential graphite sealing device |
| CN109538760A (en) * | 2019-01-18 | 2019-03-29 | 南通大通宝富风机有限公司 | A kind of double isolation carbon ring sealing structures of magnetic suspension vapor compressor |
| CN112431787A (en) * | 2020-10-27 | 2021-03-02 | 哈尔滨广瀚燃气轮机有限公司 | Graphite seal for lubricating oil cavity of gas compressor |
-
2016
- 2016-01-12 CN CN201620025707.2U patent/CN205315051U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105972216A (en) * | 2016-07-22 | 2016-09-28 | 中国航空动力机械研究所 | Circumferential graphite sealing device |
| CN109538760A (en) * | 2019-01-18 | 2019-03-29 | 南通大通宝富风机有限公司 | A kind of double isolation carbon ring sealing structures of magnetic suspension vapor compressor |
| CN109538760B (en) * | 2019-01-18 | 2023-12-08 | 南通大通宝富风机有限公司 | Double-isolation carbon ring sealing structure of magnetic suspension vapor compressor |
| CN112431787A (en) * | 2020-10-27 | 2021-03-02 | 哈尔滨广瀚燃气轮机有限公司 | Graphite seal for lubricating oil cavity of gas compressor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205315051U (en) | Terminal surface graphite sealing device and aviation air turbine starter | |
| CN204828313U (en) | Bearing seal device suitable for high rotational speed floating axle | |
| CN105626870A (en) | Rotary sealing structure with bidirectional sealing function | |
| CN204349744U (en) | Phase asynchronous sealed electric-motor | |
| EP2116738B1 (en) | Sealing arrangement | |
| CN106402166B (en) | Double-row spherical roller bearing double-lip sealing structure and wind driven generator | |
| CN104019238A (en) | Comb tooth shaped elasticity self-adaptive sealing structure | |
| CN204127321U (en) | A kind of mechanical seal device | |
| CN108591464A (en) | A kind of gas insulation switch cabinet sealing structure | |
| CN102889387A (en) | Graphite oil seal device | |
| CN210290749U (en) | Large-scale transmission slip ring based on end face dynamic seal | |
| CN107504185B (en) | Improve the fabricated structure of flooding system lubrication Sealing Performance of Oil Seal | |
| CN209196128U (en) | The horizontal machine of rake type dryer seals | |
| CN204438751U (en) | For the sealing device of malleation rotary kiln | |
| CN110206889B (en) | Large-scale transmission slip ring based on end face dynamic seal | |
| CN207864592U (en) | Sealing structure for retarder transmission axle shaft end | |
| CN205678251U (en) | Hot blast regulation Circular ventilation door axle head composite sealing assembly | |
| CN203488271U (en) | Integrated natural gas engine cylinder head cover assembly | |
| CN208474333U (en) | A kind of Bearning mechanism | |
| CN205896174U (en) | Combination formula graphite gaskets with dilatation joint | |
| CN219932951U (en) | Rotary shaft sealing element | |
| CN219119796U (en) | Axle hub oil seal | |
| CN203604648U (en) | Half packaging type mechanical seal structure | |
| CN104006084B (en) | A kind of sealing rotary axis system of the multidirectional carrying for Laser Radar Scanning tilting mirror | |
| CN205714664U (en) | A kind of full-oil-free lubrication sealing type piston structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: Zhong Guo Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: Zhong Guo |