CN1955440A - Three-D sequential effect maximization method for multi-stage turbomachine - Google Patents
Three-D sequential effect maximization method for multi-stage turbomachine Download PDFInfo
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- CN1955440A CN1955440A CN 200610058445 CN200610058445A CN1955440A CN 1955440 A CN1955440 A CN 1955440A CN 200610058445 CN200610058445 CN 200610058445 CN 200610058445 A CN200610058445 A CN 200610058445A CN 1955440 A CN1955440 A CN 1955440A
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Abstract
A method for maximizing the 3D time sequence effect of multi-stage impeller engine includes such steps as accurately simulating the transient flowing field time at multiple time sequence positions, analyzing the distribution of time average efficiency at each time sequence position in a time sequence period, linking the maximal time sequence effect points of each characteristic cross-section, determining the target edge profile match combination, accurately simulating the 3D transient flow time for each group of edge profile match combinations, finding out the result of time average effect, drawing a contour line of each group of edge profile match combination by using SH and ST as variables, choosing the highest point of time average effect, and re-integrating to generate vane.
Description
Technical field
The present invention relates to multistage turbine, particularly a kind of three-D sequential maximizing the benefits method that is used for multistage turbine.
Background technique
Known multistage turbine is the vitals of field extensive uses such as Aeronautics and Astronautics, navigation, the energy, chemical industry, as shown in Figure 1, a plurality of blade rows by wheel hub 1, casing 2 and the segment distance of being separated by that contained thereof constitute, and wherein blade comprises the rotating vane 3 that rotates around axle 9 and is fixed on stator blade 4 on the casing 2.As shown in Figure 2, all blades are folded along long-pending superimposing thread 6 exhibition vector products by primitive leaf grating 5 and are formed, the forefront of primitive leaf grating 5 and rear portion are by long-pending folded blade inlet edge 7 and the trailing edge 8 of forming, as shown in Figure 1, 2, Working medium gas via the above-mentioned passage that contains commentaries on classics, stator blade after pressure obtain to promote (gas compressor) or reduce (turbine).Practical multistage turbine should satisfy particular requirement such as structural strength, have the high performance characteristics of efficiency of energy utilization.
Since the invention multistage turbine, people are making great efforts to seek the technology that can continue to improve the multi-stage impeller engine efficiency always, about the research of time a kind of effort that comes to this.As two row's rotating vanes 3 or stator blade 4 among Fig. 1-3 are static relatively blades, circumferentially are the direction of blade shroud around axle 9 runnings, direction shown in arrow among Fig. 3 12.Sequential is the phenomenon that along circumferential relative position the turbine pneumatic efficiency is exerted an influence between static relatively blade.Fig. 2 has illustrated rotating vane 3 (or stator blade 4) to arrange with the sequential that constitutes with different circumferential relative installation between rotating vane 3 (or stator blade 4) thereafter, for convenient narration, hereinafter referred to as three-D sequential; Fig. 3 has illustrated rotating vane 3 (or stator blade 4) and arranging in the sequential of two-dimentional aspect in primitive blade profile 5 on the cross section of certain exhibition between rotating vane 3 (or stator blade 4) thereafter, be convenient narration, hereinafter referred to as two-dimentional sequential, open up to the cross section herein and be meant the cross section that a certain curve rotating shaft 9 revolutions are cut, 9 turn round the cross section of being cut around the shaft such as a certain curve 10 among Fig. 1-2.As shown in Figure 1, three-D sequential can be regarded as the exhibition of unlimited a plurality of two-dimentional sequential to 11 long-pending folding.In nearly more than ten years, research about time is very abundant, as document 1: " Huber; F.W.; Johnson; P.D.; Sharma; O.P., et al., PerformanceImprovement through Indexing of Turbine Airfoils, Part 1-ExperimentalInvestigation, ASME paper 95-GT-27,1995 "; document 2: " Dorney, D.J., Sharma, O.P., A Study of Turbine Performance Increases Through Airfoil Clocking, AIAApaper 96-2816,1996 "; document 3: " axial spacing is to the research of time influence, Yan court, Ji Lucheng, Chen Jiang, Xu Jianzhong, Engineering Thermophysics journal, 2004.25 (2) " in disclosed technology; these prior aries have obtained about best sequential effect; the achievement of position and other influence factor; for example, have been found that when upstream leaf last person mark is got to static relatively leaf row leading edge; sequential can obtain the peak efficiency increment, in the document 2 to two-dimentional sequential research just the highest minimum efficiency difference of discovery can reach more than 2 percentage points.Yet, the practical application sequential (is a three-D sequential in multistage turbine, only needing when mounted the static relatively leaf row of rotation relatively) time but pinpoints the problems: the three-D sequential benefit is always low than two-dimentional sequential benefit, such as document 4: " Arnone; A.; Marconcini; M.; Scotti DelGreco; A., et al., Numerical Investigation of Three-dimensional ClockingEffects in a Low Pressure Turbine, ASME paper GT2003-38414,2003. " disclosed in.Some researchers are considering that this may the exhibition vector product is folded to improve by regulating, but " rigid rotating installation blade " fettered this improvement in tradition " three-D sequential " notion, moreover still do not have effective ways can instruct exhibition to regulating each cross section so that three-D sequential efficiency earning maximum.
People wish, based on document 5: disclosed edge line matching technique in " Ji Lucheng, Chen Jiang; Yan court, the edge line matching theory and the method for turbine design, Engineering Thermophysics journal; 2005.26 (1) ", can have a kind of in the Blade Design process method of maximization three-D sequential efficiency earning.
Summary of the invention
Can not at utmost bring into play the problem that two-dimentional sequential manifests big benefit when the objective of the invention is to overcome engineering practical application (three-dimensional) time, a kind of three-D sequential maximizing the benefits method that is used for multistage turbine is provided.
For achieving the above object, the present invention takes following technological scheme.
A kind of three-D sequential maximizing the benefits method that is used for multistage turbine comprises:
1) multistage turbine being carried out the unsteady flow field time in a plurality of sequential position accurately simulates;
2) analysis and arrangement in sequential cycle during the multistage turbine of each sequential position the exhibition of equal efficient to distribution, as curve 13 corresponding sequential positions among Fig. 4; A sequential cycle is meant that the dimensionless of sequential shown in Fig. 3 position CLK is by 0.0 to 1.0; A sequential cycle comprises a plurality of sequential position;
3) press Fig. 5 example, connect the maximum sequential benefit of each characteristic cross-section point as far as possible to 11 along exhibition;
4), establish target edge line coupling combination (S (r according to maximum sequential benefit point line 15 (see figure 5)s sequential of living in position in the step 3)
Hub), S (r
Mid), S (r
Tip)), to reach optimum efficiency exhibition shown in Figure 4 to distribution curve 14.Wherein, S (r
Hub), S (r
Mid), S (r
Tip) be respectively root, in, the front-seat blade trailing edge 8 of sharp typical section and constitute the circumferential dimensionless distance of the downstream blade leading edge 7 of sequential.Implied in this process each blade primitive when dislocation relatively takes place circumferentially UNSTEADY FLOW the hypothesis of phase change only takes place;
5) consider proximal end wall district (being nearly 1,2 zone) mobile possibility substantial deviation 4) middle hypothesis, so make up (S (r with above-mentioned target edge line coupling
Hub), S (r
Mid), S (r
Tip)) be the center, launch certain SH (root edge line dimensionless circumferential distance, i.e. S (r
Hub)), ST (tip edge line dimensionless circumferential distance, i.e. S (r
Tip)) carry out the combination of edge line coupling in the excursion, shown in curve among Fig. 5 16, each combination means one group of leaf row behind the long-pending again storied one-tenth of blade;
6) each group edge line coupling is combined into line time accurate three-dimensional unsteady flow dynamic simulated;
Equal efficiencies when 7) accurate three-dimensional unsteady flow dynamic simulated is put in order out by the time;
Equal efficiencies is that variable is drawn isopleth with SH, ST when 8) each being organized, all most effective point when wherein selecting;
9) by the long-pending again storied one-tenth blade of all most effective some the respective coordinates SH of institute, the ST of time in the step 8).This is the blade that satisfies three-D sequential benefit maximum substantially;
10) can carry out the check of sequential maximum effect with the blade that time accurate three-dimensional unsteady flow dynamic simulated generates step 9) to guarantee reliable design.
In technique scheme, in the described step 1) multistage turbine is carried out the unsteady flow field time 5 above sequential positions and accurately simulate.
In technique scheme, in the described step 5), the relative character of S (r) (radius r place edge line dimensionless circumferential distance) is when practical application edge line coupling maximization three-D sequential effect, can change front row or long-pending the folding of the back relative static blade of row separately, also can change simultaneously.
In technique scheme, in the step 5) with target (S (r
Hub), S (r
Mid), S (r
Tip)) (SH in the time of ST), is fixed on leaf central part near will save the search optimum the best sequential position amount of calculation for the center changes the combination of edge line coupling;
In technique scheme, get rid of bad above-mentioned steps 5 fast according to the permanent result of calculation of three-dimensional) combination of middle edge line coupling.
Compared with prior art, the invention has the advantages that:
The present invention has overcome conventional three-dimensional sequential benefit not as the big problem of two-dimentional sequential benefit.The present invention adopts " long-pending again folded blade " to open up to section two dimension sequential the best to realize the sequential maximizing the benefits to make each as far as possible.Thereby the conventional method of comparing obtained bigger efficiency earning, and method is simple relatively, engineering is practical.The present invention can improve the multi-stage impeller engine efficiency in the Blade Design process, is applicable to the efficient multistage turbine development in Aeronautics and Astronautics, navigation and industrial energy power field.
Description of drawings
Fig. 1 represents axial-flow blower machine structure meridian view; Wherein turbine is made up of wheel hub 1, casing 2, rotating vane 3, stator blade 4, and commentaries on classics, stator blade have front and rear edge line 7 and 8, and rotating vane 3 is 9 rotations around the shaft;
Fig. 2 represents multistage axial flow turbine blade structural upright view and three-D sequential; Wherein along long-pending superimposing thread 6 long-pending folded forming, blade primitive front and rear amasss and builds up costa 7 and trailing edge line 8 turbine blade by blade primitive 5;
Fig. 3 represents two-dimentional sequential signal, and this two-dimentional sequential forms for the 9 revolution cuttings around the shaft of curve 10 among Fig. 1 and 2, and it is the time that influences performance that static relatively leaf row 3 (or static relatively leaf row 4) circumferential 12 relative displacement takes place.
Fig. 4 represents three-D sequential maximization target figure of the present invention; This figure illustrate maximum three-D sequential efficient be exactly find blade long-pending folded again mode so that the time equal efficient exhibition become curve 14 to the curve 13 that distributes by traditional sequential, curve 14 is maximum value envelopes of curve 13;
Fig. 5 represents three-D sequential maximization approach schematic representation of the present invention, this figure illustrates in the three-D sequential maximization procedure, finding the sequential position exhibition of determining by Fig. 4 target behind distribution curve 15, consider in the long-pending again folded prerequisite hypothesis that can run counter to method of petiolarea blade, and be the center with position bright shown in the curve 15, in curve 16 restricted portions, change blade long-pending folded (being the combination of conversion edge line coupling), seek true maximum three-D sequential.
Fig. 6 represents that 1.5 grades of turbine exhibitions of three-D sequential maximizing the benefits method of the present invention are to cross section two dimension sequential schematic representation;
Fig. 7 represents the 1.5 grades of turbine three-D sequential maximizing efficiency targets and the process schematic representation of three-D sequential maximizing the benefits method of the present invention;
Fig. 8 represents that the SH-ST of 1.5 grades of turbine secondary maximization sequential efficiency improvement of three-D sequential maximizing the benefits method of the present invention makes up the figure that throws the net, and puts target edge line coupling combination (0.0,0.32,0.07) in the 17 corresponding step 3), is the prototype of retrofiting once more;
Fig. 9 represents the SH-ST combined efficiency isoline map of 1.5 grades of turbine secondary maximization sequential efficiency improvement of three-D sequential maximizing the benefits method of the present invention, puts 18 corresponding sequential efficient maximum points, promptly finally improves the result;
Figure 10 represents 1.5 grades of turbines end row's stator blades after the improvement of three-D sequential maximizing the benefits method of the present invention.
Embodiment
Need to prove that the same number designation in the accompanying drawing is used for representing same characteristic, it is the part that the residing position of this numeral of expression will be represented just that the numeral that has has underscore.
Below in conjunction with the drawings and specific embodiments the present invention is described in further detail:
With reference to Fig. 6, certain 1.5 grades (quiet/commentaries on classics/quiet form, totally three row's blades) axial flow turbine blades comprise the steps: in the maximization three-D sequential object procedure realizing long-pending folded again
1) to the multistage turbine of three row's blades combinations in 5 sequential positions 0,0.2,0.4,0.6,0.8 (with pitch nondimensionalization value, Fig. 6 has shown that certain exhibition is to the cross section) carry out the unsteady flow field time and accurately simulate;
2) analyze in the sequential cycle (as sequential dimensionless position CLK among Fig. 3 by 0.0 to 1.0) each exhibition of each sequential position multistage turbine to the time equal efficient of section, by the result put in order out along exhibition to 9%, 25.5%, 50%, 74.5%, 91% 5 typical section at any time the tagmeme efficient of putting variation distribute, as shown in Figure 7, connect the maximum sequential benefit of each characteristic cross-section point along exhibition as far as possible to 11;
3) referring to Fig. 8, according to step 2) in maximum sequential benefit point line 15 sequential of living in positions, establish target edge line coupling combination (S (r
Hub), S (r
Mid), S (r
Tip))=(0.0,0.32,0.07); Those skilled in the art should be noted that this moment, curve 15 did not run through exhibition to all best efficiency points of each cross section, and this is will smooth as far as possible consideration for blade geometry fully; And establish target edge line coupling combination (S (r
Hub), S (r
Mid), S (r
Tip))=(0.0,0.32,0.07) be to consider for verification;
4) with step 3) target edge line coupling combination (S (r
Hub), S (r
Mid), S (r
Tip))=(0.0,0.32,0.07) be the center, launch certain SH, ST ∈ (0.2,0.1) carrying out the combination of edge line coupling in the excursion, every bit means the combination of an edge line coupling, also just means one group of leaf row behind the long-pending again storied one-tenth of blade, singly change last row stator blade, i.e. secondary stator blade in this example; Allow SH and ST to change between [0.2,0.1], as Fig. 8, (this is target combination in the step 3), as the prototype of retrofiting once more for SH, ST)=(0,0) corresponding edge line coupling (0.0,0.32,0.07) in its mid point 17 representatives;
5) according to (SH, ST) the long-pending again storied one-tenth secondary stator blade of every bit coordinate in the domain of variation;
6) the whole three row's blades that comprise step 5) improvement back secondary stator blade are carried out full three-dimensional non-steady Field Flow Numerical Simulation;
Equal efficiencies when 7) accurate three-dimensional unsteady flow dynamic simulated is put in order out by the step 6) time;
Equal efficiencies is that variable is drawn isoline map with SH, ST when 8) each being organized, and as Fig. 9, all most effective point puts 18 as shown in Figure 9 when selecting in view of the above;
9) by the long-pending again storied one-tenth blade of all most effective some the respective coordinates SH of institute, the ST of time in the step 8).As shown in figure 10, be the blade that satisfies three-D sequential benefit maximum substantially.
In above-mentioned example operation process, in the step 1), find maximum traditional sequential efficient 86.58%, minimum efficiency efficient 86.25%, the maximum lift of ordered pair efficient is 0.33% during tradition.Target is improved prototype in the step 3), promptly corresponding (SH, ST)=(0,0), equal efficient is 86.65% when non-permanent calculating, and only slightly promotes compared to traditional sequential peak efficiency, this is the selection problem of Fig. 7 center line 15, also is to depart from the precondition of method because petiolarea flows.For this reason, in further revising, note the mobile influence of petiolarea emphatically, thereby be optimized analysis in the interval at SH, ST ∈ (0.2,0.1), finally find maximum time point, among Fig. 9 18, corresponding Figure 10 middle period sheet, the time, accurate Flow Field Calculation showed, obtained peak efficiency 86.90%, further improve 0.32% than maximum traditional sequential efficient in the step 1), visible validity of the present invention and advantage.
It should be noted last that above embodiment is only unrestricted in order to technological scheme of the present invention to be described.Although the present invention is had been described in detail with reference to embodiment, those of ordinary skill in the art is to be understood that, technological scheme of the present invention is made amendment or is equal to replacement, do not break away from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of the claim scope of the present invention.
Claims (6)
1, a kind of three-D sequential maximizing the benefits method that is used for multistage turbine comprises the steps:
1) multistage turbine being carried out the unsteady flow field time in a plurality of sequential position accurately simulates;
2) in arrangement sequential cycle during the multistage turbine of each sequential position the exhibition of equal efficient to distribution;
3) along opening up to connecting the maximum sequential benefit of each characteristic cross-section point;
4), establish target edge line coupling combination (S (r according to maximum sequential benefit point line sequential of living in position in the step 3)
Hub), S (r
Mid), S (r
Tip)), to reach the optimum efficiency exhibition to distribution curve; Wherein, S (r
Hub), S (r
Mid), S (r
Tip) be respectively root, in, the front-seat blade trailing edge 8 of sharp typical section and constitute the circumferential dimensionless distance of the downstream blade leading edge 7 of sequential;
5) with above-mentioned target edge line coupling combination (S (r
Hub), S (r
Mid), S (r
Tip)) be the center, in certain SH, ST excursion, carry out the combination of edge line coupling; SH is a root edge line dimensionless circumferential distance, and ST is a tip edge line dimensionless circumferential distance;
6) each group edge line coupling is combined into line time accurate three-dimensional unsteady flow dynamic simulated;
Equal efficiencies when 7) accurate three-dimensional unsteady flow dynamic simulated is put in order out by the time;
Equal efficiencies is that variable is drawn isopleth with SH, ST when 8) each being organized, all most effective point when wherein selecting;
9) by the long-pending again storied one-tenth blade of all most effective some the respective coordinates SH of institute, the ST of time in the step 8).
2, according to the described three-D sequential maximizing the benefits method that is used for multistage turbine of claim 1, it is characterized in that, comprise that also the blade that step 10) generates step 9) with time accurate three-dimensional unsteady flow dynamic simulated carries out the check of sequential maximum effect.
3, according to the described three-D sequential maximizing the benefits method that is used for multistage turbine of claim 1, it is characterized in that, in the described step 1) multistage turbine is carried out the unsteady flow field time 5 above sequential positions and accurately simulate.
According to the described three-D sequential maximizing the benefits method that is used for multistage turbine of claim 1, it is characterized in that 4, independent change front row or the back relative static blade of row amass and fold in step 5), or change simultaneously.
5, according to the described three-D sequential maximizing the benefits method that is used for multistage turbine of claim 1, it is characterized in that, in the step 5) with target (S (r
Hub), S (r
Mid), S (r
Tip)) (SH in the time of ST), is fixed on leaf central part near the best sequential position for the center changes the combination of edge line coupling.
6, according to claim 1,2,3, one of the 4 or 5 described three-D sequential maximizing the benefits methods that are used for multistage turbine, it is characterized in that, in step 5), also comprise: get rid of not good match's line coupling combination according to the permanent result of calculation of three-dimensional.
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| CNB2006100584450A CN100376765C (en) | 2005-10-28 | 2006-03-24 | Three-D sequential effect maximization method for multi-stage turbomachine |
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| CN200510116754 | 2005-10-28 | ||
| CN200510116754.4 | 2005-10-28 | ||
| CNB2006100584450A CN100376765C (en) | 2005-10-28 | 2006-03-24 | Three-D sequential effect maximization method for multi-stage turbomachine |
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| CN100376765C CN100376765C (en) | 2008-03-26 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2556824A1 (en) | 2011-08-10 | 2013-02-13 | Les Laboratoires Servier | Solid pharmaceutical composition for buccal administration of agomelatine |
| CN103670526A (en) * | 2012-09-10 | 2014-03-26 | 通用电气公司 | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
| US9435221B2 (en) | 2013-08-09 | 2016-09-06 | General Electric Company | Turbomachine airfoil positioning |
| CN107766598A (en) * | 2016-08-19 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | Turbine optimum timing location determining method and device |
| CN108121838A (en) * | 2016-11-30 | 2018-06-05 | 中国航发商用航空发动机有限责任公司 | Turbine setting out curbs method and device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10053361C1 (en) * | 2000-10-27 | 2002-06-06 | Mtu Aero Engines Gmbh | Blade grid arrangement for turbomachinery |
-
2006
- 2006-03-24 CN CNB2006100584450A patent/CN100376765C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2556824A1 (en) | 2011-08-10 | 2013-02-13 | Les Laboratoires Servier | Solid pharmaceutical composition for buccal administration of agomelatine |
| CN103670526A (en) * | 2012-09-10 | 2014-03-26 | 通用电气公司 | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
| US9435221B2 (en) | 2013-08-09 | 2016-09-06 | General Electric Company | Turbomachine airfoil positioning |
| CN107766598A (en) * | 2016-08-19 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | Turbine optimum timing location determining method and device |
| CN108121838A (en) * | 2016-11-30 | 2018-06-05 | 中国航发商用航空发动机有限责任公司 | Turbine setting out curbs method and device |
| CN108121838B (en) * | 2016-11-30 | 2021-09-21 | 中国航发商用航空发动机有限责任公司 | Impeller edge line matching method and device |
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| CN100376765C (en) | 2008-03-26 |
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Effective date of registration: 20170825 Address after: 100080 No. 15, No. three, Zhongguancun Road, Haidian District, Beijing, No. seventy-fifth, 106 Patentee after: BEIJING ZHONGKE ZHONGNENG TECHNOLOGY Co.,Ltd. Address before: 100080 No. 12, Zhongguancun Road, Beijing, Haidian District Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |
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Effective date of registration: 20171227 Address after: R & D center 9 No. 421000 Hunan province Hengyang City Baishazhou Industrial Park, Yanfeng District Industrial Avenue, room 512 Patentee after: Hengyang Zhongke green nurseries Technology Co.,Ltd. Address before: 100080 No. 15, No. three, Zhongguancun Road, Haidian District, Beijing, No. seventy-fifth, 106 Patentee before: BEIJING ZHONGKE ZHONGNENG TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20190227 Address after: 266500 Binhai Avenue South, Shanchuan West Road, Huangdao District, Qingdao City, Shandong Province Patentee after: Qingdao Zhongke Fanneng Technology Service Co.,Ltd. Address before: Room 512, R&D Center, No. 9 Industrial Avenue, Baishazhou Industrial Park, Yanfeng District, Hengyang City, Hunan Province Patentee before: Hengyang Zhongke green nurseries Technology Co.,Ltd. |
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Effective date of registration: 20190520 Address after: 266500 East Road, University Park, Huangdao District, Qingdao City, Shandong Province Patentee after: Qingdao Zhongke Ark Aviation Technology Co.,Ltd. Address before: 266500 Binhai Avenue South, Shanchuan West Road, Huangdao District, Qingdao City, Shandong Province Patentee before: Qingdao Zhongke Fanneng Technology Service Co.,Ltd. |
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Granted publication date: 20080326 |