EP1907671A1 - Gasturbinenschaufel und plattformelement für einen gasturbinenschaufelkranz, tragstruktur zu deren befestigung, gasturbinenschaufelkranz und seine verwendung - Google Patents
Gasturbinenschaufel und plattformelement für einen gasturbinenschaufelkranz, tragstruktur zu deren befestigung, gasturbinenschaufelkranz und seine verwendungInfo
- Publication number
- EP1907671A1 EP1907671A1 EP06764202A EP06764202A EP1907671A1 EP 1907671 A1 EP1907671 A1 EP 1907671A1 EP 06764202 A EP06764202 A EP 06764202A EP 06764202 A EP06764202 A EP 06764202A EP 1907671 A1 EP1907671 A1 EP 1907671A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- gas turbine
- blade
- turbine blade
- longitudinal direction
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
-
- 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
- F05D2250/711—Shape curved convex
-
- 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
- F05D2250/712—Shape curved concave
Definitions
- the invention relates to a gas turbine blade having a profiled in cross-section blade root, followed successively by a platform and thereon a longitudinally curved blade profile, wherein the blade root 5 extends in the longitudinal direction of the blade profile and the platform has two longitudinal curved curved platform longitudinal edges.
- the invention relates to a gas turbine blade ring gear deck member, comprising a profiled platform leg and a platform plate having two curved longitudinal edges and wherein the platform plate and the platform base extend in a longitudinal direction.
- the invention relates to a support structure for attachment of arranged in a ring gas turbine blades, in which 5 Schaufelhaltenuten are provided, in each of the
- the invention relates to a gas turbine blade ring for a gas turbine having a support structure and gas turbine blades and the use of such a gas turbine blade ring.
- Gas turbine blades with purely straight blade roots and platforms as well as curved blade profiles are known from the prior art.
- the pressure-side and the suction-side platforms run with greatly varying platform overhangs.
- the pressure side in the middle region between leading edge and trailing edge, such gas turbine blades have large Overhangs, which are steadily smaller towards the trailing edge and the leading edge. These large overhangs are poorly coolable and reduce the fatigue life of the gas turbine blade.
- WO 2001/059263 A2 discloses a turbine blade arrangement for a gas turbine.
- the gas turbine blade having a rectilinear blade root is positively inserted in a retaining groove, which on the outer circumference of a
- Turbine disc is provided.
- the gas turbine blades only have platform stubs whose longitudinal edges are curved in the axial direction of the turbine. Between two adjacent gas turbine blades, a separate platform is connected to the turbine disk by means of an additional support. Due to the comparatively lightweight, because platformless gas turbine blade radial extension of the blade profiles is possible.
- each platform element must be secured by means of a separate holding element or a separate holder on the turbine disk.
- the object of the invention is to specify a simplified system for fastening gas turbine blades on a
- Support structure for forming a gas turbine blade ring for a gas turbine Another object of the invention is the use of a gas turbine blade ring according to the invention.
- the object directed to the system is achieved by providing a gas turbine blade ring with the features of claim 13.
- the simplified system is composed at least of a support structure according to any one of claims 10 to 12, are attached to the gas turbine blades according to one of claims 1 to 6. Accordingly, a support structure is also required for the solution in which the gas turbine blade forms a corresponding shape relative to the blade root Blade retaining grooves are provided.
- the invention is based on the recognition that the platform and the blade root of the gas turbine blade and the retaining grooves of the support structure must be similarly shaped in the longitudinal direction or axial direction in order to achieve a particularly simple, even individual assembly of the gas turbine blades.
- the platform longitudinal edges are curved in the axial direction
- the blade root extends in a straight line in the axial direction. Since the known gas turbine blade is inserted in a purely translational movement due to the rectilinear blade root, and the platform longitudinal edges are curved, the intermediate platform elements must be radially introduced into their operating position, then attached to the rotor disc with an additional, mounted in a rectilinear direction of movement bracket to become.
- the invention proposes that the blade root is shaped such that the respective blade end surface facing the suction side and pressure side profile wall runs convexly or concavely curved in accordance with the platform longitudinal edges. All geometric surfaces influencing the assembly are then curved in the same direction, so that all components forming the gas turbine blade ring can be individually assembled in a direction of movement corresponding to their curvature.
- the design is subject to the condition that the gas turbine blades and, if necessary, the platform elements, in the support structure, based on their mounting position in the
- Gas turbine blade ring more gas turbine blades than previously provided in a wreath.
- Advantageous embodiments are specified in the subclaims.
- the gas turbine blade according to the invention has a blade root surface on which all curvature lines extending in the longitudinal direction extend parallel to the curved platform longitudinal edges on a circular arc.
- the suction-side and the pressure-side blade root surfaces could also be curved in such a way that the blade root becomes sharpened from an oncoming-edged end face to a downstream-edged end face, i. wedge-shaped shrinking its cross section in the longitudinal direction, tapers. in the
- a suction-side or pressure-side platform protrusion projects from the suction-side profile wall to the suction-side platform longitudinal edge and / or from the pressure-side profile wall to the pressure-side platform longitudinal edge, whose platform width is approximately constant over 30% of its longitudinal length. Due to the almost constant platform width, the transition of platform and blade profile during operation is exposed to more uniform thermal and mechanical stresses. Such a designed platform is particularly good and uniformly cool and avoids non-uniform, because substantially different width wide platform projections along the blade profile. In addition, due to the now uniformized stresses, an increase in the fatigue life can be achieved.
- a particularly small platform can be achieved if the suction-side and / or pressure-side platform overhang Platform stub is formed with a comparatively short platform width.
- the gas turbine blade is almost platformless, which significantly simplifies their structural design.
- the simplification leads to a cost reduction in the design of the gas turbine blade and in their manufacture.
- the occurring in the transition region between the blade profile and platform and responsible for the early fatigue material stresses are eliminated.
- the gas turbine blade is designed as a gas turbine blade, the blade root is formed in cross-section dovetailed, hammer-shaped or fir-tree-like.
- the preferably cast gas turbine blade is coolable.
- the generic platform element must have a platform foot which is shaped so that each lateral platform root surface corresponding to the respective longitudinal edge is convex or concavely curved.
- the platform foot is shaped in the longitudinal direction in such a way that all the longitudinally extending curvature lines of the platform foot surface extend parallel to the longitudinal edges on a circular arc.
- the platform foot is so in the same degree as the blade foot of the
- Both feet thus have identical circular arcs or radii, so that each element can be mounted individually in the support structure.
- this consists at least partially of ceramic.
- the platform cooling can be reduced by what happens efficiency-increasing effect on a gas turbine equipped therewith.
- the gas turbine blades are mounted in a support structure to a gas turbine blade ring, in the
- Blade holding grooves are provided, in which the blade roots of the gas turbine blade can be inserted, wherein the blade retaining grooves correspond to the blade roots of the gas turbine blades, d. H. each blade retaining groove is identical to the blade root in FIG.
- the support structure is designed as a rotor disk, in which the blade retaining grooves are provided in the axial direction of the rotor disk extending in its outer periphery.
- platform elements according to the invention in one of their curvature corresponding
- the upstream and / or pressure-side platform or their overhangs Due to the approximately constant width of the upstream and / or pressure-side platform or their overhangs, they can be cooled easier and more efficiently.
- the use of Cooling air can be reduced.
- the saved cooling air can be supplied in the stationary gas turbine to increase the efficiency of the combustion.
- the platform element is provided as a ceramic or with a ceramic thermal barrier coating, it may even be possible to dispense with the platform cooling, which has an efficiency-increasing effect on a gas turbine equipped therewith.
- FIG. 2 shows a gas turbine blade according to the invention with a curved blade root and a curved
- FIG. 3 shows an inventive platform element with a curved platform foot
- FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 follow one another an intake housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
- the annular combustion chamber 6 forms a combustion chamber 17 which is provided with an annular hot gas channel 18th communicated.
- four turbine stages 10 connected in series form the turbine unit 8. Each turbine stage 10 is composed of two
- FIG. 2 shows a gas turbine blade 50 according to the invention designed as a gas turbine blade with a blade root 52, on which a platform 54 and a successive one follow
- Blade profile 56 is provided.
- the blade profile 56 is longitudinally L, i. curved in the installed position in a gas turbine 1 in the axial direction A.
- the blade profile 56 is not shown in its full height, but it ends comparatively close to the platform 54th
- the blade profile 56 has a pressure-side profile wall 62 and a suction-side profile wall 64, which extend from a front edge 66 of the blade profile 56 to a trailing edge 68.
- the hot gas 11 flows around the gas turbine blade 50. It flows along the profile walls 62, 64, from the front edge 66 in the direction of the trailing edge 68.
- the platform 54 is curved along the longitudinal direction L, the longitudinal edges 55 of the platform 54 do not run in a straight line but on an arc.
- the suction side platform longitudinal edge 55a is convex and the pressure side platform longitudinal edge 55b is concavely curved.
- the platform 54 has, in each case in the region of the front edge 66 and in the region of the rear edge 68, a cross-platform transverse edge 53 running transversely on the front side.
- the blade root 52 is curved in the same manner as the longitudinal edges 55 of the platform 54.
- the suction-side blade root surface 72b is longitudinal curved convexly and the pressure-side blade root surface 72a in the longitudinal direction concave.
- the blade root 52 is also shaped in the embodiment shown in such a way that all extending in the longitudinal direction L lines of curvature 70 of Schaufelfußober Design 72 extend parallel to the platform longitudinal edge 55 on a circular arc.
- the curvature lines 70 of the platform longitudinal edges 55 and of the blade root 52 can run on a circular arc, so that they can be pushed into a supporting structure 80 (FIG. 4) in blade receiving grooves 82 in a particularly simple manner.
- thermomechanical stresses can be reduced particularly well
- platform overhangs 75 which extend along the longitudinal axis L at least over 30% of the length of the platform 54 (in the longitudinal direction) approximately constant, both the suction side and the pressure side.
- An inventive platform element 74 is shown in a perspective view in FIG. The
- Platform element 74 has a platform plate 76 and a platform foot 78, both of which extend in the longitudinal direction L. Analogous to the platform 54 of the gas turbine blade
- the platform plate 76 of the platform element 74 has a platform longitudinal edge 79a that is convexly curved in the longitudinal direction L, and a concavely curved platform longitudinal edge 79b.
- the platform foot 78 is curved to the platform longitudinal edges 79 in the longitudinal direction L correspondingly.
- Like all longitudinally L extending curvature lines 70 of the Schaufelfußober Structure 72 of the gas turbine blade 50 according to the invention all extend in the longitudinal direction L. extending curvature lines 77 of the platform foot surface 81 to the longitudinal edges 79 of the platform plate 76 in parallel on a circular arc.
- FIG. 4 shows a perspective view of a detail of a gas turbine blade ring 90 according to the invention for a gas turbine 1.
- the gas turbine blade ring 90 is held by a support structure 80, in particular a rotor disk 19.
- a support structure 80 in particular a rotor disk 19.
- the retaining grooves serve to receive and secure gas turbine blades 50 and platform elements 74 according to the invention.
- the retaining grooves provided for securing gas turbine blades 50 are the blade retaining grooves 92 in FIG.
- Profile profiled fir-tree-shaped whereas the platform holding grooves 93 provided for holding and securing platform elements 74 are dovetail-shaped in cross-section or may have other foot shapes.
- Each blade root 52 is seated in the blade retaining groove 92 in a positive fit, as well as each platform root 78 in the platform retaining groove 93.
- Both the blade retaining grooves 92 and the platform retaining grooves 93 are curved in the axial direction A such that their axial direction A extending curvature lines of the groove surface parallel to a
- Run circular arc and thereby correspond to the curvature of the blade root 52 and the platform foot 78.
- all longitudinal edges curved in the axial direction A or in the longitudinal direction L can lie parallel on a circular arc, so that each component, both the gas turbine blade 50 and the platform element 74, is fully populated Gas turbine blade ring 90 guided out of this slidable.
- Blade profile i. on the suction side and on the pressure side.
- the pressure-side as well as the suction-side platform overhangs can thus be approximately the same size and thus comparatively symmetrical, which avoids one-sided platform overhangs and correspondingly locally varying mass accumulations. Varying mass accumulations have a negative effect on the voltage distributions and thus on the service life of the gas turbine blade.
- the unilaterally occurring in sections platform overhangs are difficult to cool, which also has a negative impact on the life of the gas turbine blade. Fatigue symptoms appear delayed. Due to the design with curved blade root and curved
- Platform longitudinal edges can be a structural simplification of the gas turbine blade and thus a more efficient cooling brought about, which advantageously also allows the introduction of provided between the gas turbine blades platform elements or intermediate platforms.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Low-Molecular Organic Synthesis Reactions Using Catalysts (AREA)
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL06764202T PL1907671T3 (pl) | 2005-07-25 | 2006-07-19 | Wieniec łopatkowy turbiny gazowej |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US70235805P | 2005-07-25 | 2005-07-25 | |
US11/214,303 US7300253B2 (en) | 2005-07-25 | 2005-08-29 | Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring |
PCT/EP2006/064400 WO2007012587A1 (de) | 2005-07-25 | 2006-07-19 | Gasturbinenschaufel und plattformelement für einen gasturbinenschaufelkranz, tragstruktur zu deren befestigung, gasturbinenschaufelkranz und seine verwendung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1907671A1 true EP1907671A1 (de) | 2008-04-09 |
EP1907671B1 EP1907671B1 (de) | 2008-12-31 |
Family
ID=37054737
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06764202A Not-in-force EP1907671B1 (de) | 2005-07-25 | 2006-07-19 | Gasturbinenschaufelkranz |
Country Status (9)
Country | Link |
---|---|
US (1) | US7300253B2 (de) |
EP (1) | EP1907671B1 (de) |
JP (1) | JP2009503330A (de) |
CN (1) | CN101233299B (de) |
AT (1) | ATE419451T1 (de) |
DE (1) | DE502006002518D1 (de) |
ES (1) | ES2317560T3 (de) |
PL (1) | PL1907671T3 (de) |
WO (1) | WO2007012587A1 (de) |
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US8277190B2 (en) * | 2009-03-27 | 2012-10-02 | General Electric Company | Turbomachine rotor assembly and method |
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US8322977B2 (en) * | 2009-07-22 | 2012-12-04 | Siemens Energy, Inc. | Seal structure for preventing leakage of gases across a gap between two components in a turbine engine |
US8292583B2 (en) * | 2009-08-13 | 2012-10-23 | Siemens Energy, Inc. | Turbine blade having a constant thickness airfoil skin |
DE102010004854A1 (de) | 2010-01-16 | 2011-07-21 | MTU Aero Engines GmbH, 80995 | Laufschaufel für eine Strömungsmaschine und Strömungsmaschine |
US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
US8657579B2 (en) | 2010-08-27 | 2014-02-25 | General Electric Company | Blade for use with a rotary machine and method of assembling same rotary machine |
US8599082B2 (en) | 2011-02-01 | 2013-12-03 | Siemens Energy, Inc. | Bracket assembly for a wireless telemetry component |
US8527241B2 (en) | 2011-02-01 | 2013-09-03 | Siemens Energy, Inc. | Wireless telemetry system for a turbine engine |
CH704825A1 (de) | 2011-03-31 | 2012-10-15 | Alstom Technology Ltd | Turbomaschinenrotor. |
US8827643B2 (en) * | 2011-10-26 | 2014-09-09 | General Electric Company | Turbine bucket platform leading edge scalloping for performance and secondary flow and related method |
US8967973B2 (en) * | 2011-10-26 | 2015-03-03 | General Electric Company | Turbine bucket platform shaping for gas temperature control and related method |
US9303531B2 (en) | 2011-12-09 | 2016-04-05 | General Electric Company | Quick engine change assembly for outlet guide vanes |
US9303520B2 (en) | 2011-12-09 | 2016-04-05 | General Electric Company | Double fan outlet guide vane with structural platforms |
US20130149127A1 (en) * | 2011-12-09 | 2013-06-13 | General Electric Company | Structural Platforms for Fan Double Outlet Guide Vane |
US9033669B2 (en) | 2012-06-15 | 2015-05-19 | General Electric Company | Rotating airfoil component with platform having a recessed surface region therein |
FR2994211B1 (fr) * | 2012-08-03 | 2018-03-30 | Safran Aircraft Engines | Aube mobile de turbine |
US9739158B2 (en) | 2013-03-10 | 2017-08-22 | Rolls-Royce Corporation | Attachment feature of a gas turbine engine blade having a curved profile |
EP2971736B1 (de) | 2013-03-13 | 2019-07-10 | Rolls-Royce Corporation | Zwischenschaufelmetallplattform für keramikmatrix- verbundturbinenschaufeln |
WO2014204542A2 (en) * | 2013-04-01 | 2014-12-24 | United Technologies Corporation | Lightweight blade for gas turbine engine |
US9670781B2 (en) * | 2013-09-17 | 2017-06-06 | Honeywell International Inc. | Gas turbine engines with turbine rotor blades having improved platform edges |
US9896946B2 (en) * | 2013-10-31 | 2018-02-20 | General Electric Company | Gas turbine engine rotor assembly and method of assembling the same |
FR3014942B1 (fr) * | 2013-12-18 | 2016-01-08 | Snecma | Aube, roue a aubes et turbomachine ; procede de fabrication de l'aube |
FR3018849B1 (fr) | 2014-03-24 | 2018-03-16 | Safran Aircraft Engines | Piece de revolution pour un rotor de turbomachine |
US10830065B2 (en) * | 2015-06-02 | 2020-11-10 | Siemens Aktiengesellschaft | Attachment system for a turbine airfoil usable in a gas turbine engine |
FR3048719B1 (fr) * | 2016-03-14 | 2018-03-02 | Safran Aircraft Engines | Redresseur de flux pour turbomachine avec plateformes integrees et rapportees |
US10428661B2 (en) | 2016-10-26 | 2019-10-01 | Roll-Royce North American Technologies Inc. | Turbine wheel assembly with ceramic matrix composite components |
US10358922B2 (en) * | 2016-11-10 | 2019-07-23 | Rolls-Royce Corporation | Turbine wheel with circumferentially-installed inter-blade heat shields |
US10557350B2 (en) * | 2017-03-30 | 2020-02-11 | General Electric Company | I beam blade platform |
FR3066531B1 (fr) * | 2017-05-19 | 2019-05-03 | Safran Aircraft Engines | Aube en materiau composite et a plateforme integree pour une turbomachine d'aeronef |
US10724390B2 (en) | 2018-03-16 | 2020-07-28 | General Electric Company | Collar support assembly for airfoils |
US10767498B2 (en) | 2018-04-03 | 2020-09-08 | Rolls-Royce High Temperature Composites Inc. | Turbine disk with pinned platforms |
US10577961B2 (en) | 2018-04-23 | 2020-03-03 | Rolls-Royce High Temperature Composites Inc. | Turbine disk with blade supported platforms |
US10890081B2 (en) | 2018-04-23 | 2021-01-12 | Rolls-Royce Corporation | Turbine disk with platforms coupled to disk |
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FR3140649A1 (fr) * | 2022-10-07 | 2024-04-12 | Safran Aircraft Engines | Disque pour une turbine de turbomachine d’aeronef |
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2005
- 2005-08-29 US US11/214,303 patent/US7300253B2/en not_active Expired - Fee Related
-
2006
- 2006-07-19 AT AT06764202T patent/ATE419451T1/de not_active IP Right Cessation
- 2006-07-19 PL PL06764202T patent/PL1907671T3/pl unknown
- 2006-07-19 EP EP06764202A patent/EP1907671B1/de not_active Not-in-force
- 2006-07-19 JP JP2008523322A patent/JP2009503330A/ja active Pending
- 2006-07-19 CN CN2006800273303A patent/CN101233299B/zh not_active Expired - Fee Related
- 2006-07-19 WO PCT/EP2006/064400 patent/WO2007012587A1/de not_active Application Discontinuation
- 2006-07-19 DE DE502006002518T patent/DE502006002518D1/de active Active
- 2006-07-19 ES ES06764202T patent/ES2317560T3/es active Active
Non-Patent Citations (1)
Title |
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See references of WO2007012587A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE502006002518D1 (de) | 2009-02-12 |
ATE419451T1 (de) | 2009-01-15 |
WO2007012587A1 (de) | 2007-02-01 |
PL1907671T3 (pl) | 2009-06-30 |
CN101233299B (zh) | 2011-06-15 |
JP2009503330A (ja) | 2009-01-29 |
ES2317560T3 (es) | 2009-04-16 |
US7300253B2 (en) | 2007-11-27 |
CN101233299A (zh) | 2008-07-30 |
US20070020102A1 (en) | 2007-01-25 |
EP1907671B1 (de) | 2008-12-31 |
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