EP2245275A1 - Guide vane for a variable turbine geometry - Google Patents
Guide vane for a variable turbine geometryInfo
- Publication number
- EP2245275A1 EP2245275A1 EP08869779A EP08869779A EP2245275A1 EP 2245275 A1 EP2245275 A1 EP 2245275A1 EP 08869779 A EP08869779 A EP 08869779A EP 08869779 A EP08869779 A EP 08869779A EP 2245275 A1 EP2245275 A1 EP 2245275A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sections
- guide vane
- section
- curvature
- region
- 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.)
- Granted
Links
- 238000010586 diagram Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 230000007704 transition Effects 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
Definitions
- the invention relates to a guide vane for a variable turbine geometry of a turbocharger.
- a turbocharger generally consists of an exhaust gas turbine in the exhaust stream, which is connected via a shaft with a compressor in An ⁇ aug Th.
- the turbine is set in rotation by the exhaust gas flow of the engine and thus drives the compressor.
- the pressure in the intake tract of the engine is increased via the compressor, so that a larger amount of air enters the cylinder during the intake stroke than in a naturally aspirated engine. In this way, more oxygen is available for burning a correspondingly larger amount of fuel.
- bypass or wastegate the hot exhaust gas is partly passed by the turbine and thus the performance of the turbine is reduced.
- the turbine is designed so large that it works well well below the rated operating point of the engine.
- turbochargers are known from the prior art, which are provided with a variable turbine geometry VTG, in order to better adapt the power output and the response to different operating conditions, such as load changes.
- VTG variable turbine geometry
- high peripheral components of the flow velocity and a high enthalpy gradient lead to a high turbine output and thus to a high boost pressure.
- full open position of the vanes in turn, the maximum throughput of the turbine opens up high centripetal fraction of the velocity vector of the flow.
- the advantage of this power control over a bypass control is that always the full exhaust gas mass flow is routed through the turbine and used for power conversion.
- the shape of the blade profile is the main influencing factor for the thermodynamic efficiency, the control characteristics and the required radial space.
- the profile of the adjusting blade there are a variety of shapes for the profile of the adjusting blade. In general, it is important to combine the optimum of efficiency, control characteristics and the smallest possible pitch circle (installation space).
- the shape is described by the line of curvature that extends between the center of the head radius and the center of the end radius of the pitch blade. This curvature line is created by assuming tangential circles within the profile to the top and bottom. The connecting line of the circle centers here describes the curvature line.
- curvature lines have a continuous course, i.
- the individual curve pieces merge tangentially.
- the curvature line has no kink.
- a guide vane is provided, in particular for a turbocharger, wherein the manifold ment line of the guide vane has at least one or more areas with a discontinuous course.
- the guide vane is particularly advantageous in the design of a flow profile.
- the efficiency can be improved with unchanged control behavior and space requirements.
- the line of curvature has at least one region with two sections which are connected to one another, the two sections discontinuously or not tangentially merging at their connection point.
- the sections form a kink at their junction.
- the line of curvature of the guide vane has, in addition to at least one region with a bend or with a non-tangential transition between two sections, at least one region whose two sections merge continuously or tangentially into one another at their junction.
- the line of curvature of a guide vane can be varied as desired with continuously and discontinuously extending regions, depending on which flow profile is to be achieved.
- At least one, several or all portions of the line of curvature are identical or different, for example with respect to their shape, position and / or dimension.
- the guide vane for example consists of four sections, wherein the first and second section form a first region, with a continuous course.
- a second region is formed by the second portion and a third portion, wherein the second and third portions at their junction discontinuously into each other or form a kink.
- Such a vane is an example in which the curvature line has a kink.
- the sections of the first or third area may in this case be curved, for example, both or at least one of them upwards or downwards.
- the portions of which the curvature line is composed for example, arcuate or straight.
- the sections can be curved upwards or downwards or, if the sections are straight, for example horizontally, vertically, or obliquely upwards or obliquely downwards.
- the sections can be combined as desired with each other, wherein at least one area which is formed by the sections has a discontinuous course. In this way, a variety of flow profiles, depending on the desired function or desired application can be realized.
- FIG. 2 shows a second embodiment of a guide vane according to the prior art
- FIG. 3 shows a third embodiment of a guide vane according to the prior art
- FIG. 4 shows a first embodiment of a guide vane according to the invention.
- Fig. 5 shows a second embodiment of a vane according to the invention.
- FIG. 1 a first embodiment of a guide vane 10 according to the prior art is shown.
- the vane 10 is shown in a diagram, wherein the diagram has an X-axis and a Y-axis. This illustration applies to all guide vanes 10 as shown in FIGS. 1 to 5.
- the shape of a vane 10 is normally described by the line of curvature 12 that extends between the midpoint 14 of the head radius and the midpoint 16 of the end radius of the vane 10.
- This curvature line 12 is formed by 20 tangential circles are assumed within the profile of the guide vane 10 to the top and bottom 18 ,.
- the connecting line of the circular center points describes the curvature line 12.
- the curvature line 12 is wavy.
- the curvature line 12 consists of four sections al to a4 together.
- the first and second sections a1, a2, which form a first area b1 are in each case arched upwards in a curved shape, wherein the two sections a1, a2 of the curve 12 merge tangentially into one another at their connection point 22.
- the area bl forms a continuous course without a kink.
- the third portion a3 is also arcuate, being curved downward, in contrast to the first and second portions al, a2.
- the second and third sections a2, a3 also merge tangentially into one another at their connection point 22, so that the second region b2, which is formed from the second and third sections a2, a3, has a continuous profile.
- the two sections a3, a4 of the curvature line 12 merge tangentially into one another, ie the region b3 has a continuous course, without a kink being formed at the transition 22 between the two sections a3, a4.
- All three areas bl to b3 extend above the X axis in the diagram in FIG. 1, furthermore, the first area bl is significantly longer and more curved than the third area b3.
- the line of curvature 12 is also composed of four sections al to a4.
- the curvature line 12 in this case runs above the X axis and in this case initially rises in an arc upwards, before it slowly drops towards the other end.
- the first section al of the line of curvature 12 is arched downward in a downward arc and the adjoining section a2 is curved upward.
- the two sections al and a2 tangentially merge into each other, so that the first area bl, by the first and second portion al, a2 has a continuous course.
- the third section a3 is also curved arcuately upwards, wherein he and the second section a2 at their junction 22 tangentially merge into each other, without causing a kink arises.
- the third region b3 of the curvature line 12 is formed from the third section a3 and a fourth section a4.
- the fourth section a4 is arched downward in an arc shape, with the third and fourth sections a3, a4 merging tangentially into one another at their connection point 22.
- Fig. 3 Further shown in Fig. 3 is a third embodiment of a prior art vane form.
- the guide vane 10 consists, as in the first and second embodiment of four sections al to a4.
- the curvature line 12 runs in a waveform initially in an arc above the X axis and then in an arc below the X axis.
- the first and second sections al, a2 of the curvature line 12 is arcuate and extends upwardly curved. At their connection point 22, the two first and second sections al, a2 merge tangentially into one another.
- the second region b2 of the curvature line 12 is formed by the second section a2 and a third section a3.
- the third section a3 is also arcuate and curved downwards.
- the two sections a2 and a3 pass tangentially into one another at their connection point 22, so that no sharp kink occurs in this area.
- the fourth region b4 is formed by the third section a3 and a fourth section a4.
- the fourth section a4 is likewise arched in an arcuate manner.
- the guide vane 10 here consists for example of four sections al to a4.
- a first region, consisting of the first and second sections al, a2, has a continuous course.
- the first and second sections al, a2 is here arc-shaped and curved upwards.
- the first section al passes tangentially into the second section a2, so that a continuous course is created without a kink.
- a second region b2 is formed by the second portion a2 and a third portion a3, wherein the second and third portions a2, a3 are each arcuate and are curved upward.
- the sections a2 and a3 do not tangentially merge into one another at their connection point 22 but form a kink 24.
- the second area b2 does not form a continuous course as in the prior art but has a discontinuous course or has a sharp kink 24 at the Junction 22 of the two sections a2, a3.
- the third area b3 consists of the third section a3 and a fourth section a4 and forms a continuous course.
- the fourth section a4 is arc-shaped and arched upwards. At their connection point 22, the third and fourth sections a3, a4 merge tangentially into one another.
- the guide vane 10 has a region b2 with a discontinuous course of the curvature line 12, in which the second and third sections a2, a3 at their junction 22 form a kind of kink 24 or not tangentially into each other.
- the other areas b1 and b3 have a continuous course of the curvature line 12, without one of the areas forming a bend.
- the curvature line 12 in the present case forms two arcs, once an upwardly arched arc of the sections al and a2 and another compared to a very much shallow arched arc consisting of the sections a3 and a4. Both bends form at their junction 22 the kink 24th
- FIG. 5 a second embodiment of a guide blade 10 according to the invention is shown in FIG. 5.
- the curvature line 12 of the guide vane 10 consists of four sections al to a4.
- the first and second sections al, a2 is arc-shaped and arched upwards.
- the first and second sections al, a2 merge tangentially into one another, so that the area b1, which is formed from the two sections al, a2, has a continuous course.
- the second region b2 is formed from the second portion a2 and a third portion a3, wherein the third portion a3 is also curved upwards.
- the two sections a2, a3 do not merge tangentially into one another at their connection point 22, but form a kind of kink 24, as shown in FIG.
- the second area b2 has a discontinuous course.
- the two third and fourth sections a3, a4 are here arc-shaped and curved upwards. At their junction 22 they go tangentially into each other.
- the curvature line 12 of the guide vane 10 according to the invention has a discontinuous course at least in the region b2, while the two other regions b1 and b3 have a continuous course without buckling.
- the first area bl is formed longer, or the stretched from the sections al and a2 arch.
- the third area b3, or the arc stretched from the sections a3 and a4 is shorter in the second embodiment than in the first embodiment.
- a guide vane may comprise at least one region consisting of two sections or a plurality of sections, for example two, three, four, five, six and more sections.
- sections having an arbitrary shape, arrangement and / or dimensioning can be combined with one another.
- the areas that are formed from the sections are formed from the sections.
- the areas b 1 to b 3 are each arranged substantially above the x-axis in the diagrams.
- the regions or sections of the curvature line 12 can run as desired, for example at least partially below the X axis, as is illustrated, for example, in FIG. 3 with reference to the prior art.
- the portions of the line of curvature 12 may also extend entirely below or partially along the X-axis.
- straight and arcuate portions at the curve line 12 of a vane 10 can be varied as desired.
- the guide blade 10 can have at least one kink 24 or a plurality of kinks 24 or points at which the individual curve pieces of the curve line 12 do not merge tangentially into one another.
- the curvature line 12 can have one, two, three, four or more of these so-called kinks 24 or non-tangential transitions, wherein the kinks 24 can be provided at arbitrary positions of the curvature line 12, depending on the function or intended use.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008004014A DE102008004014A1 (en) | 2008-01-11 | 2008-01-11 | Guide vane for a variable turbine geometry |
PCT/EP2008/064594 WO2009086959A1 (en) | 2008-01-11 | 2008-10-28 | Guide vane for a variable turbine geometry |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2245275A1 true EP2245275A1 (en) | 2010-11-03 |
EP2245275B1 EP2245275B1 (en) | 2015-04-08 |
Family
ID=40193669
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08869779.2A Active EP2245275B1 (en) | 2008-01-11 | 2008-10-28 | Adjustable guide vane of a turbine of a turbocharger |
Country Status (7)
Country | Link |
---|---|
US (1) | US20100296924A1 (en) |
EP (1) | EP2245275B1 (en) |
JP (2) | JP2011509371A (en) |
KR (1) | KR20100110867A (en) |
CN (1) | CN101910565B (en) |
DE (1) | DE102008004014A1 (en) |
WO (1) | WO2009086959A1 (en) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009057987B4 (en) | 2009-12-11 | 2020-08-20 | BMTS Technology GmbH & Co. KG | Loading device and guide vane for such a loading device |
US8834104B2 (en) * | 2010-06-25 | 2014-09-16 | Honeywell International Inc. | Vanes for directing exhaust to a turbine wheel |
CN103946487B (en) | 2011-11-30 | 2016-01-20 | 三菱重工业株式会社 | Radial-flow turbine |
JP5964081B2 (en) | 2012-02-29 | 2016-08-03 | 三菱重工業株式会社 | Variable capacity turbocharger |
FR2991373B1 (en) * | 2012-05-31 | 2014-06-20 | Snecma | BLOWER DAWN FOR AIRBORNE AIRCRAFT WITH CAMBRE PROFILE IN FOOT SECTIONS |
US9790796B2 (en) * | 2013-09-19 | 2017-10-17 | General Electric Company | Systems and methods for modifying a pressure side on an airfoil about a trailing edge |
DE102013224572A1 (en) * | 2013-11-29 | 2015-06-03 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Exhaust gas turbocharger, in particular for a motor vehicle |
DE102013225642B4 (en) * | 2013-12-11 | 2020-09-17 | Vitesco Technologies GmbH | Exhaust gas turbocharger with an adjustable guide grille |
US10240469B2 (en) * | 2014-03-04 | 2019-03-26 | Borgwarner Inc. | Cast turbocharger turbine housing having guide vanes |
DE102014221362A1 (en) * | 2014-10-21 | 2016-04-21 | Siemens Aktiengesellschaft | Profiling of vanes of nozzles in turbomachinery, in particular compressors |
DE102015205208A1 (en) | 2015-03-23 | 2016-09-29 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device with variable turbine geometry |
US11041505B2 (en) | 2016-03-31 | 2021-06-22 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotary machine blade, supercharger, and method for forming flow field of same |
US10935041B2 (en) | 2016-06-29 | 2021-03-02 | Rolls-Royce Corporation | Pressure recovery axial-compressor blading |
US10774650B2 (en) * | 2017-10-12 | 2020-09-15 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
WO2020129192A1 (en) * | 2018-12-19 | 2020-06-25 | 三菱重工エンジン&ターボチャージャ株式会社 | Nozzle vane |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE522531C (en) * | 1929-01-12 | 1931-04-10 | Bbc Brown Boveri & Cie | Method for adapting the free passage cross-section of adjustably inserted guide vanes of turbines, in particular exhaust gas turbines |
DE1096536B (en) * | 1953-08-17 | 1961-01-05 | Rheinische Maschinen Und App G | Centrifugal compressor, from the impeller of which the conveying medium enters a guide device concentrically surrounding the impeller at supersonic speed |
CH351065A (en) * | 1957-02-21 | 1960-12-31 | Ingenieurbureau W Hausammann & | Impeller for turbo machines, especially axial compressors |
EP0056569A1 (en) * | 1981-01-21 | 1982-07-28 | ATELIERS DE CONSTRUCTIONS ELECTRIQUES DE CHARLEROI (ACEC) Société Anonyme | Turbine with variable inlet section |
JPH01227823A (en) * | 1988-03-08 | 1989-09-12 | Honda Motor Co Ltd | Variable nozzle structure of turbine |
DE4220960A1 (en) * | 1992-06-25 | 1994-01-05 | Turbowerke Meisen Ventilatoren | Blades for axial and radial flow machines - use series of segments and connecting elements to create variable flow contour |
DE4238550A1 (en) * | 1992-11-14 | 1994-05-19 | Daimler Benz Ag | Exhaust gas turbocharger for an internal combustion engine |
FR2714109B1 (en) * | 1993-12-22 | 1996-01-19 | Snecma | Variable camber turbomachine blade. |
DE59709447D1 (en) * | 1997-11-17 | 2003-04-10 | Alstom Switzerland Ltd | Power stage for turbine with axial flow |
JP2000087899A (en) * | 1998-09-14 | 2000-03-28 | Ishikawajima Harima Heavy Ind Co Ltd | Noise reducing device for inlet guide vane device |
JP3605398B2 (en) * | 2002-02-26 | 2004-12-22 | 三菱重工業株式会社 | Variable capacity turbocharger |
US6709232B1 (en) * | 2002-09-05 | 2004-03-23 | Honeywell International Inc. | Cambered vane for use in turbochargers |
DE10255389A1 (en) * | 2002-11-28 | 2004-06-09 | Alstom Technology Ltd | Low pressure steam turbine has multi-channel diffuser with inner and outer diffuser rings to take blade outflow out of it |
EP1714008B1 (en) * | 2003-12-31 | 2009-02-25 | Honeywell International | Turbocharger assembly |
JP2008520881A (en) * | 2004-11-16 | 2008-06-19 | ハネウェル・インターナショナル・インコーポレーテッド | Variable nozzle turbocharger |
US7510371B2 (en) * | 2005-06-06 | 2009-03-31 | General Electric Company | Forward tilted turbine nozzle |
US20090104023A1 (en) * | 2005-07-19 | 2009-04-23 | Frederic Favray | Variable Nozzle Turbocharger |
EP3150805B1 (en) * | 2005-11-25 | 2020-09-23 | BorgWarner, Inc. | Variable geometry turbocharger guide vane and turbocharger |
DE102008020673B4 (en) * | 2007-05-09 | 2018-10-31 | Schaeffler Technologies AG & Co. KG | Graded stator blade |
-
2008
- 2008-01-11 DE DE102008004014A patent/DE102008004014A1/en not_active Withdrawn
- 2008-10-28 EP EP08869779.2A patent/EP2245275B1/en active Active
- 2008-10-28 US US12/812,499 patent/US20100296924A1/en not_active Abandoned
- 2008-10-28 KR KR1020107017638A patent/KR20100110867A/en not_active Application Discontinuation
- 2008-10-28 CN CN200880124892.9A patent/CN101910565B/en active Active
- 2008-10-28 WO PCT/EP2008/064594 patent/WO2009086959A1/en active Application Filing
- 2008-10-28 JP JP2010541722A patent/JP2011509371A/en active Pending
-
2013
- 2013-09-05 JP JP2013184103A patent/JP5701352B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009086959A1 * |
Also Published As
Publication number | Publication date |
---|---|
JP2011509371A (en) | 2011-03-24 |
CN101910565B (en) | 2014-06-11 |
KR20100110867A (en) | 2010-10-13 |
EP2245275B1 (en) | 2015-04-08 |
JP5701352B2 (en) | 2015-04-15 |
US20100296924A1 (en) | 2010-11-25 |
WO2009086959A1 (en) | 2009-07-16 |
DE102008004014A1 (en) | 2009-07-23 |
JP2013238249A (en) | 2013-11-28 |
CN101910565A (en) | 2010-12-08 |
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