EP1787009A1 - Schaufel mit deckband - Google Patents
Schaufel mit deckbandInfo
- Publication number
- EP1787009A1 EP1787009A1 EP05856216A EP05856216A EP1787009A1 EP 1787009 A1 EP1787009 A1 EP 1787009A1 EP 05856216 A EP05856216 A EP 05856216A EP 05856216 A EP05856216 A EP 05856216A EP 1787009 A1 EP1787009 A1 EP 1787009A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- platform
- shroud
- platform portion
- inclination angle
- 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
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- the invention relates to a shroud equipped with a shroud according to the preamble of claim 1 and to a shovel arrangement according to the preamble of the independent main claim.
- the shrouds can be formed, for example, as outer shrouds on the outer circumference of a blade row. Also, the shrouds are usually designed as a split shrouds, wherein the shroud in question on the circumference of a row of blades in one of the number of blades of the blade row corresponding plurality of
- Shroud elements is divided. Each blade is then associated with a shroud element, wherein the blade and shroud element are usually made in one piece.
- the shroud elements are usually designed like a platform and extend substantially perpendicular to the blade longitudinal direction. Are the blades in a known manner on
- the shroud elements of the blades adjoin one another and thus form a circumferentially closed shroud.
- the respective shroud element is at the blade tip, i. at the free end of the blade of the blade.
- An arrangement of a shroud on a blade row can be done for various purposes. On the one hand can be improved by the arrangement of a shroud, the vibration behavior of a blade. Neighboring vanes are separated by the divided shroud elements
- Vibration behavior is fundamentally improved.
- the damping can be increased by means of a shroud, as it is in vibrational excitation of the blade to a Relatiwerschiebungen the 2/22 B04 / 057-0
- the outer shroud elements of an outer shroud of a rotor are usually arranged on the blade tip such that the center of gravity of the outer shroud is balanced in relation to the respective blade root.
- this means that the shroud elements are not symmetrically balanced. That the one deck portion of the shroud member extending on one side of the airfoil (eg, the pressure side) is unlike the other deck portion of the shroud member located on the other side of the airfoil
- the suction side extends.
- the platform sections often have unequal length Kragin. This non-uniformity of the platform sections results in the use of the blade in a rotor due to the force acting on the platform sections centrifugal forces to different high bending moments on the pressure side and the suction side platform section. As a result of the different levels of bending moments, in turn, different degrees of elastic deformation of the pressure-side and suction-side platform sections occur. This situation is shown in Figure 2c.
- the pressure-side platform section has a larger cantilever length in FIG.
- the escape of the fluid through the resulting gap is here further increased by the fact that the fluid is scooped or pressed into the gap as a result of the direction of rotation in the direction of the pressure side as a blade effect.
- the invention seeks to remedy this situation.
- the invention is therefore an object of the invention to provide a blade and a blade assembly of the type mentioned, with which the disadvantages of the prior
- the invention helps to increase the service life of blades equipped with shrouds. 4/22 B04 / 057-0
- the blade according to the invention comprises an airfoil and a shroud in the airfoil longitudinal direction final shroud element.
- the airfoil in turn comprises a suction side and a pressure side.
- the platform-shaped shroud element extends substantially perpendicular to the blade leaf longitudinal direction and comprises a first platform section projecting over the blade leaf and a second platform section projecting over the blade leaf.
- the first platform section is designed as a pressure-side platform section and the second platform section is designed as a suction-side platform section.
- the platform sections are asymmetrical to each other. As a result of the asymmetry of the platform sections, a larger bending moment acts on the first platform section during operation of the bucket than on the second platform section.
- Such an asymmetry may be caused, for example, by the fact that the platform sections have different cantilever-relevant cantilever lengths. In the case of a blade rotating during operation, the asymmetry may also be due to different material thicknesses of the platform sections.
- the bending-moment-relevant cantilever length of the pressure-side platform section is greater than the bending-moment-relevant cantilever length of the suction-side platform section, whereby a ratio of the bending-moment-relevant cantilever length of the pressure-side platform section to the bending-moment-relevant cantilevered-side cantilever-side platform section is usually greater than 1.15.
- the first one is 5/22 B04 / 057-0
- Platform portion of the shroud element according to the invention with respect to a normal orientation of the first platform portion arranged at an additional inclination angle.
- the additional angle of inclination is in this case in the opposite direction to the effective direction of the bending moment, which acts in operation on the first platform section, and thus also applied to the deflection of the first platform section.
- the platform section is in this case aligned so that when Aneinaderreihung the shroud elements results in a circumferentially closed circular shroud.
- the alignment according to the invention of at least one platform section of a shroud element at an additional angle of inclination ultimately means that the platform sections of the shroud element run differently inclined to the perpendicular to the blade airfoil longitudinal direction.
- the shroud element thus has in the region of the airfoil quasi a kink, this kink is preferably rounded.
- At least one platform portion of the shroud element of the inventively constructed blade is arranged with respect to a normal orientation at an additional angle of inclination, in an arrangement of the blade in series with another blade, for example in a rotor, in the transition region between the Shroud element of the inventively designed blade to the shroud element of the adjacent blade in
- Hibernation formed a step.
- the platform portion arranged at an additional inclination angle protrudes more into the flow channel than the platform portion of the adjacent blade due to the inclination angle. Only in the operation of the rotor occur due to the rapid rotation of the rotor centrifugal forces on the
- the inventively designed blade is particularly suitable for use as a rotor blade in a turbine of a turbomachine or turbo group. Especially in the rotors of a turbine occur both high centrifugal forces and at the same time high temperatures, which lead here to combined loads on the blades. Thus, the invention can contribute here to a significant increase in the life of the blades of the rotors.
- Shroud element is formed. Particularly in the case of a rotor blade designed with an outer shroud element, the centrifugal forces acting on the rotor blade during operation cause a bending of the platform section of the shroud element. But the shroud element can also be designed as inner cover tape element. In a blade formed with an outer shroud element and an inner shroud element, the invention can also be applied to both shroud elements.
- Platform portion and the suction-side platform portion in operation an effective angle of inclination of more than 0 ° obtained so that forms a step in the transition of the pressure-side platform portion to the suction-side platform section, this stage acts on the flow similar to a ski jump.
- the flow overflows the stage without being dammed up.
- the additional inclination angle should be suitably chosen so that adjusts an effective additional inclination angle of at least 0 ° during operation of the blade.
- An inclination angle of 0 ° means that the platform section arranged at an inclination angle adjoins the platform section of the adjacent blade without forming a step.
- Inclination angle is when the arranged under an angle angle platform portion connects to form a step to the platform portion of the adjacent blade and the angle of inclination is plotted in the opposite direction to a bending moment occurring in operation on the platform section.
- the additional inclination angle is selected so that adjusts an effective additional inclination angle of more than 0 ° during operation of the blade. That as long as the bucket is relatively new, the bucket is in operation between the bucket
- Shroud element of the considered blade and the shroud element of the adjacent blade formed a step. After some operating time of the blade, however, due to thermally induced creep and the resulting plastic deformation of the shroud element to a reduction of the stage and finally to a complete
- the additional inclination angle is selected so that adjusts an effective additional inclination angle during operation of the blade, which is approximately equal to the additional inclination angle at which adjusts an additional effective inclination angle of 0 °. This can be achieved on the one hand a much longer life of the blade. On the other hand, the main flow experiences only a small disturbance, so that no appreciable increase in the flow losses of the main flow is caused thereby.
- the blade is produced together with shroud element as a casting. If the arrangement according to the invention of the platform section is already taken into account in the casting process at an additional angle of inclination, then for the production of the blade formed according to the invention in FIG.
- a blade arrangement comprising a plurality of blades arranged in series on the circumference of a turbomachine, at least one of the blades is formed in the manner according to the invention.
- the blade arrangement according to the invention is advantageously further developed as a rotor of a turbine.
- the blade arrangement can also be developed as a stator.
- all blades of such a blade arrangement are formed in the manner according to the invention.
- the platform portions of the shroud elements of the blades of the blade assembly are formed at their free ends in each case substantially rectangular with a flow-facing edge and a flow-facing edge.
- the additional inclination angle is then appropriate to choose so that the outflow edge of the arranged at an additional inclination angle platform section comes to rest during operation of the blade assembly between the flow-facing edge and the outflow edge of the adjacent platform portion of the adjacent blade.
- the additional inclination angle is to be selected so that the outflow edge of the arranged at an additional inclination angle platform section during operation of the blade assembly between the flow-facing edge and a median plane between the flow-facing edge and the downstream edge of the adjacent platform portion of the adjacent blade to lie comes.
- the additional angle of inclination is expediently selected so that the outwardly facing edge of the respective platform section, which is arranged at an additional angle of inclination, projects further into the area of the flow when the blade arrangement is not in operation than the edge of the adjacent platform section adjacent to the flow Shovel.
- Figure 1 shows a detail of a known from the prior art, running with outer shroud rotor
- Figure 2a is a known from the prior art, with
- Outer shroud element executed rotor blade in a detailed view
- FIG. 2b shows the rotor blade of FIG. 2a designed with outer cover tape element in a plan view
- FIG. 2c shows an illustration of the forces and flow conditions acting on the shroud elements during operation of the rotor blade of FIG. 2a;
- Figure 2d shows a schematic representation of a known from the prior art arrangement of platform sections adjacent
- FIG. 2e shows the arrangement from FIG. 2d in the operating state
- 3a shows a schematic illustration of an arrangement according to the invention of platform sections of adjacent blades in the idle state
- FIG. 3b shows the arrangement from FIG. 3a in the operating state.
- FIG. 1 is a schematic representation of a detail of a part of FIG.
- Prior art known rotor 1 which is carried out in a conventional manner with an inner shroud 6 and with an outer shroud 7.
- the rotor 1 shown in Figure 1 is designed here as a rotor of a turbine.
- the rotor 1 shown in Figure 1 comprises a centrally disposed rotor shaft 2 and a plurality of circumferentially of the rotor shaft 2 juxtaposed blades 3-a, 3-b and 3-c.
- the blades 3-a, 3-b, 3-c each comprise an airfoil 4-a, 4-b and 4-c and are over 11/22 B04 / 057-0
- Tannenbaumfpune 5-a, 5-b and 5-c anchored in the rotor shaft 2.
- the inner shroud elements 6i-a, 6i-b and 6i-c are each designed in a platform-like manner and extend essentially perpendicular to the respective blade longitudinal direction L4-a, L4-b or L4-c.
- an outer shroud element 7a-a, 7a-b, 7a-c is located at the blade tip of each shovel 3a, 3b, 3c.
- the outer shroud elements 7a-a, 7a-b, 7a-c are formed like a platform and also extend substantially perpendicular to the respective
- Turbine is the very hot air coming from the combustion chamber, which forms the main flow of the turbine.
- shroud elements 6i-a, 6i-b, 6i-c and 7a-a, 7a-b, 7a-c also serve to the vibration behavior of the blades 3-a, 3-b, 3-c in a desired manner change.
- Shroud elements 6i-a, 6i-b, 6i-c and 7a-a, 7a-b, 7a-c changes the natural frequency of the blades 3-a, 3-b, 3-c to lower frequencies.
- the outer shroud elements 7a-a, 7a-b, 7a-c but also the clamping of the airfoil is changed so that in each case a bilateral
- Outer shroud 7 and the housing remain a small gap to allow such a relative movement.
- the housing is often additionally provided with an abrasive on the side facing the outer shroud
- FIG. 2a shows in a detailed view of a known from the prior art, with outer shroud element 7a running rotor blade 3.
- FIG. 2b the rotor blade 3 of Figure 2a is shown in a plan view.
- the section shown in Figure 2a is an upper portion of the
- the airfoil 4 has a pressure side I and a suction side II. At the upper end of the airfoil 4 closes the
- Outer shroud element 7a the blade 4 from.
- the outer shroud element 7a extends approximately perpendicular to the blade airfoil longitudinal direction L4 and has a substantially platform-like design.
- At the front and at the back of the shroud element 7a is here in each case additionally a sealing lip 7a-D1 and
- Base platform 7a-B, front and rear sealing lips 7a-D1 and 7a-D2 and adjacent housing form a small flow channel, which extends at the periphery of the rotor and through the in
- the cooling fluid is supplied for this purpose, for example, in a known manner by the blade 4.
- the outer shroud element 7a and the blade 4 are, as shown in Figure 2a, usually designed in one piece.
- the outer shroud elements 7a are typically positioned on the airfoil tip such that the center of gravity is balanced in relation to the respective blade root. This ensures that the centrifugal forces caused by the rotation are introduced in a straight line over the blade root into the rotor shaft, without lateral forces being induced to any appreciable extent. Since modern blades but nowadays mostly wound and sometimes also bent, this means that the 13/22 B04 / 057-0
- Shroud elements are not balanced symmetrically to the respective airfoil.
- the one deck section 7a-1 of the shroud element extending on one side of the airfoil 4 (here the pressure side) is unlike the other platform section 7a-2 extending on the other side of the airfoil 4 (here the suction side) ,
- Nonuniformity of the platform sections 7a-1 and 7a-2 is shown in FIG. 2a by the different canting lengths KL1 of the pressure-side platform section 7a-1 and KL2 of the suction-side platform section 7a-2 of the shroud element 7a.
- different cantilever lengths KL1 and KL2 different bending moments act on the pressure-side and suction-side platform sections 7a-1 and 7a-2 when the rotor is rotating.
- This situation is illustrated in FIG. 2a by the virtual center of gravity M1 of the pressure-side platform section 7a-1 with the associated lever arm Y-M 1 and the virtual center of mass M2 of the suction-side platform section 7a-2 with the associated lever arm Z-M2.
- bending moment arrows 10-a and 10-b are plotted indicating the direction of the deflection.
- the pressure-side platform sections 7a-1a and 7a-1-b bend more than the suction-side platform sections 7a-2-a and 7a-2-b of the respective adjacent shroud elements due to the higher bending moment loads.
- a considerably enlarged gap 11 is formed in each case between the pressure-side platform section and the suction-side platform section. Due to the enlarged gap 11, the fluid of the main flow can escape into the cooling channel according to the flow arrow 12 shown in FIG. 2c.
- Inflowing of fluid of the main flow into the enlarged gap 11 is hereby reinforced by the fact that the fluid is additionally pressed into the gap as a result of the rotation in the direction of rotation 13.
- FIGS. 2d and 2e the alignment of adjoining platform sections 7a-2-a and 7a-1-b of two shroud elements of adjacent blades corresponding to FIGS. 2a to 2c is shown again in a schematic representation in each case.
- the left platform section 7a-2-a in FIGS. 2d and 2e is the suction-side platform section of the shroud element of a first blade
- the right-hand platform section 7a-1b in FIGS. 2d and 2e is the pressure-side platform section of the shroud element of a second one the first bucket adjacent bucket.
- Arrow 15 indicates the direction of rotation of the blades, arrow 14 the relative flow direction of the main flow.
- FIG. 3a and 3b is a schematic representation of a section of a blade arrangement according to the invention is shown.
- the representation corresponds to the representation of Figures 2d and 2e.
- FIG. 3a a stationary state and in FIG. 3b a state during operation of the blade arrangement are shown.
- the blade assembly shown in Figures 3a and 3b comes from a rotor of a turbine.
- the respective left platform section in FIGS. 3a and 3b is a suction-side platform section 7a-2-a of a shroud element of a first blade
- the respective right platform section is a pressure-side platform section 7a-1-b of a shroud element second, adjacent to the first blade blade is.
- Arrow 15 indicates the direction of rotation of the blades, arrow 14 the relative flow direction of the main flow.
- the blades are made in one piece with the shroud elements as a casting.
- the pressure-side platform section 7a-1-b has a greater cantilever length than the suction side
- Platform portion 7a-2-a wherein the ratio of Kragin the pressure-side platform portion 7a-1-b to Kragin the suction-side platform portion 7a-2-a here is about 1, 2.
- the platform sections are substantially rectangular in shape with the edge A facing away from the flow and the edge B of the suction side facing the flow
- Platform portion and the flow-facing edge C and the flow-facing edge D of the pressure-side platform portion In the dormant and cold state, which is shown in Figure 3a, is the 16/22 B04 / 057-0
- suction side platform portion 7a-2-a formed in a conventional manner, while the pressure-side platform portion 7a-1-b is aligned from the normal orientation of the platform portion shown in Figure 2d at an additional inclination angle ⁇ .
- the additional inclination angle ⁇ is in the opposite direction to that in the
- the platform section of the second blade projects further into the region of the main flow 14 than the flow-facing edge B of the suction-side platform section of the first blade.
- the platform sections 7a-2-a and 7a-1-b are thus offset relative to one another and aligned with each other.
- This can, as shown in Figure 3a, also mean that the gap 11 between the platform sections in the stationary and cold state is effectively greater than in an aligned arrangement of the platform sections, as shown in Figure 2d.
- the centrifugal forces acting on the platform sections 7a-2-a and 7a-1-b cause the pressure-side platform section 7a-1-b to be bent outwards.
- the gap between the platform sections, as shown in Figure 3 b closed.
- the additional inclination angle ⁇ is selected so that during operation of the blade an effective additional inclination angle ⁇ -eff of slightly more than
- the additional inclination angle ⁇ has been chosen such that an effective additional inclination angle ⁇ -eff, which is approximately equal to the additional inclination angle ⁇ at which an additional effective inclination angle ⁇ -eff of 0 ° occurs, is established during operation of the blade , This means here that the outflow facing
- the pressure-side platform section 7a-1-b is aligned with an offset ⁇ opposite the centrifugal force deflection.
- the force acting on the pressure-side platform section centrifugal deflection of the offset ⁇ is indeed reduced to an effective offset ⁇ -eff, but initially it does not go back to zero. Only through the creeping creeping over time
- the main flow 14 would impinge on the end face of the platform section 7a-2-a and would thereby be directed even more into the gap 11 and the cavity located behind the shroud.
- FIGS. 3a and 3b represent only one exemplary embodiment of the invention, which can be readily modified by a person skilled in the art in many different ways, without thereby abandoning the inventive idea.
- Shroud element be aligned at an additional inclination angle with respect to the normal orientation.
- the invention can also be applied to an inner cover tape element instead of an outer cover tape element.
- the blade can also be developed as a stator blade.
- KL1 KL2 cantilever lengths
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Food-Manufacturing Devices (AREA)
- Toys (AREA)
- Table Devices Or Equipment (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH01483/04A CH698087B1 (de) | 2004-09-08 | 2004-09-08 | Schaufel mit Deckbandelement. |
| PCT/EP2005/054327 WO2006079423A1 (de) | 2004-09-08 | 2005-09-02 | Schaufel mit deckband |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1787009A1 true EP1787009A1 (de) | 2007-05-23 |
| EP1787009B1 EP1787009B1 (de) | 2008-11-19 |
Family
ID=34973823
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP05856216A Expired - Lifetime EP1787009B1 (de) | 2004-09-08 | 2005-09-02 | Schaufel mit deckband |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US7654797B2 (de) |
| EP (1) | EP1787009B1 (de) |
| AT (1) | ATE414842T1 (de) |
| AU (1) | AU2005325824B8 (de) |
| CH (1) | CH698087B1 (de) |
| DE (1) | DE502005006015D1 (de) |
| WO (1) | WO2006079423A1 (de) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8221057B2 (en) * | 2008-06-25 | 2012-07-17 | General Electric Company | Method, system and controller for establishing a wheel space temperature alarm in a turbomachine |
| CH699984A1 (de) * | 2008-11-27 | 2010-05-31 | Alstom Technology Ltd | Verfahren zur Optimierung der Kontaktflächen von aneinander anstossenden Deckbandsegmenten benachbarter Schaufeln einer Gasturbine. |
| US9156086B2 (en) * | 2010-06-07 | 2015-10-13 | Siemens Energy, Inc. | Multi-component assembly casting |
| US9279335B2 (en) | 2011-08-03 | 2016-03-08 | United Technologies Corporation | Vane assembly for a gas turbine engine |
| US10138736B2 (en) | 2012-01-20 | 2018-11-27 | General Electric Company | Turbomachine blade tip shroud |
| US9109455B2 (en) * | 2012-01-20 | 2015-08-18 | General Electric Company | Turbomachine blade tip shroud |
| US20130209258A1 (en) * | 2012-02-15 | 2013-08-15 | General Electric Company | Tip shrouded blade |
| US9273565B2 (en) | 2012-02-22 | 2016-03-01 | United Technologies Corporation | Vane assembly for a gas turbine engine |
| US11608747B2 (en) | 2021-01-07 | 2023-03-21 | General Electric Company | Split shroud for vibration reduction |
| US11572794B2 (en) | 2021-01-07 | 2023-02-07 | General Electric Company | Inner shroud damper for vibration reduction |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1033197A (fr) * | 1951-02-27 | 1953-07-08 | Rateau Soc | Amortisseurs de vibrations pour aubages mobiles de turbo-machines |
| FR1252763A (fr) * | 1959-12-15 | 1961-05-10 | Alsthom Cgee | Entretoise pour aubes de turbines |
| US3165441A (en) * | 1961-03-01 | 1965-01-12 | Monsanto Co | Methylphosphonothioate insecticide |
| DE1159965B (de) * | 1961-08-10 | 1963-12-27 | Bbc Brown Boveri & Cie | Einrichtung zur Schwingungsdaempfung an einem Turbinen- oder Verdichter-Schaufelkranz |
| CH418360A (de) * | 1962-11-21 | 1966-08-15 | Ass Elect Ind | Turbomaschine |
| GB1194061A (en) * | 1968-01-17 | 1970-06-10 | Rolls Royce | Improvements relating to Pressure Exchanger Rotors |
| US3771922A (en) * | 1972-10-30 | 1973-11-13 | Mc Donnell Douglas Corp | Stabilized rotary blades |
| GB2032535A (en) * | 1978-07-25 | 1980-05-08 | Rolls Royce | Overlapping cantilevers |
| SU1087675A1 (ru) * | 1982-01-29 | 1984-04-23 | Брянский Ордена "Знак Почета" Институт Транспортного Машиностроения | Осева турбомашина |
| JPS58162702A (ja) * | 1982-03-23 | 1983-09-27 | Mitsubishi Heavy Ind Ltd | 軸流タ−ボ機械 |
| SU1059222A1 (ru) * | 1982-09-01 | 1983-12-07 | Предприятие П/Я В-2285 | Бандаж рабочего колеса осевой турбомашины |
| US5238366A (en) * | 1992-07-06 | 1993-08-24 | Westinghouse Electric Corp. | Method and apparatus for determining turbine blade deformation |
| JPH10339105A (ja) * | 1997-06-11 | 1998-12-22 | Mitsubishi Heavy Ind Ltd | インテグラルシュラウド翼 |
| WO2003104616A1 (ja) * | 2002-06-07 | 2003-12-18 | 三菱重工業株式会社 | タービン動翼組立体及びその組立方法 |
| US7128522B2 (en) * | 2003-10-28 | 2006-10-31 | Pratt & Whitney Canada Corp. | Leakage control in a gas turbine engine |
-
2004
- 2004-09-08 CH CH01483/04A patent/CH698087B1/de not_active IP Right Cessation
-
2005
- 2005-09-02 AT AT05856216T patent/ATE414842T1/de not_active IP Right Cessation
- 2005-09-02 DE DE502005006015T patent/DE502005006015D1/de not_active Expired - Lifetime
- 2005-09-02 AU AU2005325824A patent/AU2005325824B8/en not_active Ceased
- 2005-09-02 WO PCT/EP2005/054327 patent/WO2006079423A1/de not_active Ceased
- 2005-09-02 EP EP05856216A patent/EP1787009B1/de not_active Expired - Lifetime
-
2007
- 2007-03-06 US US11/682,624 patent/US7654797B2/en not_active Expired - Lifetime
Non-Patent Citations (1)
| Title |
|---|
| See references of WO2006079423A1 * |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1787009B1 (de) | 2008-11-19 |
| US20070231143A1 (en) | 2007-10-04 |
| AU2005325824A1 (en) | 2006-08-03 |
| ATE414842T1 (de) | 2008-12-15 |
| AU2005325824B8 (en) | 2008-07-24 |
| CH698087B1 (de) | 2009-05-15 |
| US7654797B2 (en) | 2010-02-02 |
| AU2005325824B2 (en) | 2008-07-03 |
| DE502005006015D1 (de) | 2009-01-02 |
| WO2006079423A1 (de) | 2006-08-03 |
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