WO2005019602A1 - Gasturbine mit einem dichtungselement zwischen leitschaufelkranz und laufschaufelkranz des turbinenteils - Google Patents
Gasturbine mit einem dichtungselement zwischen leitschaufelkranz und laufschaufelkranz des turbinenteils Download PDFInfo
- Publication number
- WO2005019602A1 WO2005019602A1 PCT/EP2004/007333 EP2004007333W WO2005019602A1 WO 2005019602 A1 WO2005019602 A1 WO 2005019602A1 EP 2004007333 W EP2004007333 W EP 2004007333W WO 2005019602 A1 WO2005019602 A1 WO 2005019602A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- sealing element
- turbine
- ring
- gas turbine
- vane
- Prior art date
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
Definitions
- GAS TURBINE WITH A SEALING ELEMENT BETWEEN GUIDANCE RANZ AND RUNNING SHUTTER LIFT OF THE TURBINE PART
- the invention relates to an axial gas turbine, arranged in the hot gas duct axially successive vane rings and blade rings. These blade rings are subjected to cooling air from different pressure levels. For sealing between the individual pressure levels, a sealing element is provided.
- An axial gas turbine comprises a compressor, a combustion chamber and a turbine part.
- combustion air is highly compressed, which is burned in the combustion chamber with fuel.
- the resulting hot gas is passed through a hot gas duct in the turbine part.
- turbine part follow each other alternately
- Vane rings and blade rings In each of these blade rings guide vanes are arranged adjacent in the circumferential direction.
- the temperatures in such a gas turbine can reach values which exceed the melting points of the materials used or intolerably reduce the heat resistance of the materials. For this reason, the components in the hot gas channel are often cooled with a cooling medium. Usually this air is diverted from the compressor as cooling air. The cooling requirement decreases along the flow direction in the hot gas duct. For this reason, a cooling air with a lower pressure level than cooling air for front turbine stages is sufficient for cooling rear turbine stages. In order to keep the cooling air consumption as low as possible, since this reduces the efficiency of the gas turbine, the axially different turbine stages, ie the different blade rings, are acted upon by cooling air from different pressure levels.
- U.S. Patent No. 5,833,244 shows a gas turbine seal assembly.
- the sealing of two adjacent blade rings is achieved here by a labyrinth seal system.
- Individual sealing elements are arranged in grooves of rotor discs. These sealing segments have transversely to the flow direction and in the axial direction one behind the other arranged tooth-like elevations, which are arranged opposite a vane tip. By the juxtaposition in the circumferential direction of such segments is a circumferentially circumferential
- Labyrinthdichtungssystem provided, which is particularly suitable for the seal in large gas turbines.
- the object of the invention is to provide a sealing system for sealing located between two blade rings of a gas turbine pressure levels, which has a particularly good sealing effect and at the same time is easy to install and inexpensive.
- this object is achieved by an axial gas turbine directed along a turbine axis, comprising a compressor, a combustion chamber and a turbine part, in the turbine part axially successive vane rings and rotor blade rings in one
- a hot gas flowing through the hot gas channel and wherein the vane rings and blade rings are cooled with cooling air the pressure level decreases in the flow direction of the hot gas, wherein between at least one blade ring and a directly adjacent vane ring, a sealing element is arranged, which the various Compressive levels against each other and at least a quarter of a perpendicular to the turbine axis as a center extending circle integrally extends.
- the invention pursues the way of extending a sealing element for sealing in the axial direction over a greater circumferential distance.
- the sealing effect is considerably improved because circumferentially extending sealing boundaries are reduced.
- the reduction of components facilitates installation.
- the reduction in components also causes a more cost-effective design.
- the sealing element extends around half of the circle.
- the sealing elements are preferably arranged so that in each case a sealing element extends along one of the two housing halves.
- the sealing element is designed as an annular plate with extending in the radial direction surface having an outer edge and an inner edge. Such an annular metal sheet is particularly easy to manufacture.
- the outer edge is arranged in respectively corresponding platform grooves which are arranged in the side facing away from the hot gas channel from a respective platform of vanes of the vane ring or a guide ring located radially outside the blade ring and the outer edge in a carrier groove extending in a vane carrier.
- Vanes have an airfoil that is bordered by a platform. This platform serves to shield the hot gas from the vane carrier. Attached to the platform is a fixture that secures the vane to the vane support. In the axial direction adjacent to a vane ring, a blade ring, the rotor side also leads through platforms on the blades, the hot gas.
- the surface of the hot gas passage adjacent the vane support is shielded from the hot gas by guide rings facing the rotating blade tips of the blades.
- the outer edge of the annular sealing plate can be performed.
- the outer edge is guided in a carrier groove extending in the guide vane carrier.
- the sealing element with a pressing on its surface screw, the sealing element against the opposite comparativelynuten sidewall and Victoriaernuten sidewall presses, tense.
- a secure, independent of the operating condition sealing is achieved.
- Vanes typically have an entanglement with which they are hooked into the vane carrier. Such a hooking then defines an axial fixed point by an axial contact surface between hooking and Leitschaufelani.
- the sealing element is arranged in the region of the axial fixed points. This position of the sealing element is particularly advantageous in the above-described active approach of the sealing element, since thermal displacements in the region of the axial fixed point are small.
- the sealing element is preferably arranged away from the region of the axial fixed points. Due to the large temperature differences at standstill and operating state, considerable thermally induced shifts of the blade platforms or guide rings relative to the guide blade carrier result here. By loosely inserting the sealing element in the platform or Leitschaufelaninuten a passive approach is achieved here just by these thermal shifts. The sealing element is pressed during thermal displacement against the groove walls so that no secure seal is achieved. Further preferably, in addition to the groove walls in the guide blade carrier, a further projection extending in the circumferential direction is arranged as an axial contact surface for the sealing element. In the above-described active approach for the sealing element, it is preferable to first complete the vane ring during installation by installing the guide vanes, and then then to install the adjacent guide rings.
- FIG. 1 shows a gas turbine
- FIG. 2 shows a cross section through the turbine part of a gas turbine
- Figure 4 is an enlarged view with a sealing element of Figure 3
- Figure 5 shows a further detail of a longitudinal section through a gas turbine
- Figure 6 is an enlargement with a sealing element
- FIG. 5 is a diagrammatic representation of FIG. 5.
- FIG. 1 shows a gas turbine 1.
- the gas turbine 1 has a compressor 3, a combustion chamber 5 and a turbine part 7 directed in succession along a turbine axis 10.
- the compressor 3 and the turbine part 7 are arranged on a common shaft 9 extending along the turbine axis 10.
- In the turbine part 7 extends a conically expanding hot gas channel 12.
- In this hot gas duct 12 protrude guide vanes 11 and blades 13 into it.
- a plurality of vanes 11 are disposed adjacent to each other in a vane ring 14 in the circumferential direction.
- a plurality of blades 13 are arranged in a blade ring 16 circumferentially adjacent to each other. Leitschaufelkränze 14 and blade rings 16 alternate in the hot gas duct 12 alternately.
- Compressor air 15 is supplied to the combustion chamber 5 and is burnt there by adding fuel to a hot gas 17.
- the hot gas 17 flows through the hot gas channel 12 and thus past the guide vanes 11 and the rotor blades 13.
- the shaft 9 is set in rotation, since the blades 13 absorb kinetic energy from the hot gas 17 and transmitted to the shaft 9, with which they are firmly connected.
- the energy thus obtained from the hot gas 17 may, for. B. are transmitted to a generator for power generation.
- Figure 2 shows a cross section through the hot gas channel 12.
- a portion of the blade ring 16 and a portion of the vane ring 14 are shown.
- a formed as an annular plate seal member 35 extends between the vane ring 14 and the blade ring 16 in the circumferential direction over half of a circle 41 which is perpendicular to the turbine axis 10.
- a similar sealing element 35 runs along the second half of the circle 41, so that both sealing elements 35 form a closed circle.
- the parting line 42 corresponds to a joint not shown in detail for the half-way division of the hot gas duct 12 enclosing the gas turbine housing.
- the sealing element 35 is flat, with a plan view of the surface F is shown.
- the surface F is bounded by an outer edge 37 and an inner edge 39 of the sealing element 35.
- FIG. 3 shows a detail of a longitudinal section through the hot gas channel 12.
- a guide blade 11 is shown, which is enclosed in the axial direction on both sides by a respective guide ring 51.
- a sealing element 35 is formed according to Figure 2. The exact arrangement will be described with reference to FIG.
- the vane 11 is supplied to cooling air 53 from a first pressure level.
- the guide ring 51 is supplied with cooling air 55 from a second pressure level.
- the pressure level of the cooling air 53 is higher than that of the cooling air 55, since there is a higher cooling requirement for the guide vane 11 located further forward in the direction of flow of the hot gas 17 than for the guide ring 51 located farther downstream.
- Figure 4 shows an enlarged section of Figure 3 with the sealing element 35.
- a platform 87 of the guide vane 11 is on the side facing away from the hot gas a circumferentially extending groove 85 is introduced.
- the guide blade 11 on the side facing away from the hot gas channel 12 is opposite a guide vane carrier 79.
- In Leitschaufelani 79 is in the radial direction of the platform groove 85 opposite a Leitschaufelaninut 83 also extending in the circumferential direction.
- the sealing element 35 is a correspondingly formed in FIG 2 annular metal strip whose inner edge 37 engages in the platform groove 85.
- the outer edge 39 of the sealing member 35 is located in the Leitschaufelitatinut 83.
- the axial position of the sealing element 35 is selected in the region of an entanglement 71 of the guide blade 11.
- Verhakung 71 serves to assemble the vane 11. Furthermore, with this entanglement 71 by an axial contact surface, an axial fixed point 73 defined as well as a radial fixed point 75 by means of a radial approach surface. In the region of the axial fixed point 73, thermal expansions of the platform 87 of the guide blade 11 relative to the guide blade carrier 79 are relatively small, so that a good sealing effect is achieved by the active attachment of the sealing element 35, independently of the operating state of the gas turbine.
- the guide ring 51 is also arranged by a hooking 77 in the guide vane carrier 79. In prior art configurations, i. without the sealing member 35, an axial seal by means of entanglements 71 and 77 has often been attempted to be achieved.
- FIG. 5 shows a further detail of a longitudinal section through the hot gas channel 12. Again, a guide blade 11 is shown, which is enclosed on both sides by guide rings 51 in the axial direction. Here, however, the sealing element 35 is far away from the axial fixed point 73 arranged. In addition, no device for pressing the sealing element 35 is provided on the groove walls. This will be described in more detail with reference to FIG.
- FIG. 6 shows a cutout with the sealing element 35 from FIG. 5.
- the sealing element 35 is again arranged with its inner edge 39 in a platform groove 85 and with its outer edge 37 in a Leitschaufelaninut 83.
- an additional shoulder 91 is formed as an axial contact surface so that it lies approximately in the region of the radial center of the sealing element 35.
- the platform groove 85 is arranged in the guide ring 51 in the example shown here.
- the guide ring 51 is movable relative to the vane support 79 to avoid thermal stresses. In operation, temperature differences result in a displacement of the guide ring 51 relative to the guide blade carrier 79. In this way, the sealing element 35 is bent and pressed against the projection 91 in the guide blade carrier 79.
- This form of passive approach of the sealing element 35 leads to a good sealing effect, at the same time a very low expenditure on equipment is required.
- the sealing element 35 When mounting the gas turbine 1 or even during a service operation, the sealing element 35 is simply inserted into the Leitschaufelitatinut 83 and the guide vanes 11 or the guide rings 51 mounted, depending on which ' the components has the corresponding platform groove 85. Subsequently, either the guide vanes 11 or the guide rings 51 are then mounted in each case, which adjoin the previously installed components.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/567,667 US7303371B2 (en) | 2003-08-11 | 2004-07-05 | Gas turbine having a sealing element between the vane ring and a vane carrier of the turbine |
DE502004008830T DE502004008830D1 (de) | 2003-08-11 | 2004-07-05 | Gasturbine mit einem dichtungselement im bereich ds des turbinenteils |
EP04740664A EP1654440B1 (de) | 2003-08-11 | 2004-07-05 | Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils |
PL04740664T PL1654440T3 (pl) | 2003-08-11 | 2004-07-05 | Turbina gazowa z elementem uszczelniającym w obszarze wieńca łopatek kierowniczych lub wieńca łopatek wirujących części turbinowej |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03018240 | 2003-08-11 | ||
EP03018240.6 | 2003-08-11 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005019602A1 true WO2005019602A1 (de) | 2005-03-03 |
Family
ID=34203213
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2004/007333 WO2005019602A1 (de) | 2003-08-11 | 2004-07-05 | Gasturbine mit einem dichtungselement zwischen leitschaufelkranz und laufschaufelkranz des turbinenteils |
Country Status (7)
Country | Link |
---|---|
US (1) | US7303371B2 (de) |
EP (1) | EP1654440B1 (de) |
CN (1) | CN100395431C (de) |
DE (1) | DE502004008830D1 (de) |
ES (1) | ES2316994T3 (de) |
PL (1) | PL1654440T3 (de) |
WO (1) | WO2005019602A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2971590A4 (de) * | 2013-03-14 | 2016-01-20 | United Technologies Corp | Anordnung zur abdichtung eines spaltes zwischen komponenten eines turbinenmotors |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2923525B1 (fr) * | 2007-11-13 | 2009-12-18 | Snecma | Etancheite d'un anneau de rotor dans un etage de turbine |
US8821114B2 (en) | 2010-06-04 | 2014-09-02 | Siemens Energy, Inc. | Gas turbine engine sealing structure |
US9080457B2 (en) | 2013-02-23 | 2015-07-14 | Rolls-Royce Corporation | Edge seal for gas turbine engine ceramic matrix composite component |
US9963989B2 (en) * | 2013-06-12 | 2018-05-08 | United Technologies Corporation | Gas turbine engine vane-to-transition duct seal |
US10240473B2 (en) * | 2013-08-30 | 2019-03-26 | United Technologies Corporation | Bifurcated sliding seal |
EP3039316B1 (de) * | 2013-08-30 | 2020-10-21 | United Technologies Corporation | Gleitdichtung |
EP2960439A1 (de) * | 2014-06-26 | 2015-12-30 | Siemens Aktiengesellschaft | Turbomaschine mit äußerer Dichtung und Verwendung dieser Turbomaschine |
US10161257B2 (en) * | 2015-10-20 | 2018-12-25 | General Electric Company | Turbine slotted arcuate leaf seal |
US12012858B1 (en) | 2023-04-28 | 2024-06-18 | Rtx Corporation | Failsafe blade outer airseal retention |
CN117345433B (zh) * | 2023-12-06 | 2024-02-06 | 成都中科翼能科技有限公司 | 一种燃气轮机排气机匣的封严装配组件 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4379560A (en) * | 1981-08-13 | 1983-04-12 | Fern Engineering | Turbine seal |
US4425078A (en) * | 1980-07-18 | 1984-01-10 | United Technologies Corporation | Axial flexible radially stiff retaining ring for sealing in a gas turbine engine |
US5609469A (en) * | 1995-11-22 | 1997-03-11 | United Technologies Corporation | Rotor assembly shroud |
US5833244A (en) * | 1995-11-14 | 1998-11-10 | Rolls-Royce P L C | Gas turbine engine sealing arrangement |
US6164656A (en) * | 1999-01-29 | 2000-12-26 | General Electric Company | Turbine nozzle interface seal and methods |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1605310A (en) * | 1975-05-30 | 1989-02-01 | Rolls Royce | Nozzle guide vane structure |
US5785499A (en) * | 1996-12-24 | 1998-07-28 | United Technologies Corporation | Turbine blade damper and seal |
US6273683B1 (en) * | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6702549B2 (en) * | 2000-03-02 | 2004-03-09 | Siemens Aktiengesellschaft | Turbine installation |
GB0108398D0 (en) * | 2001-04-04 | 2001-05-23 | Siemens Ag | Seal element for sealing a gap and combustion turbine having a seal element |
US7094025B2 (en) * | 2003-11-20 | 2006-08-22 | General Electric Company | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction |
US7040857B2 (en) * | 2004-04-14 | 2006-05-09 | General Electric Company | Flexible seal assembly between gas turbine components and methods of installation |
-
2004
- 2004-07-05 PL PL04740664T patent/PL1654440T3/pl unknown
- 2004-07-05 WO PCT/EP2004/007333 patent/WO2005019602A1/de active Application Filing
- 2004-07-05 EP EP04740664A patent/EP1654440B1/de not_active Not-in-force
- 2004-07-05 US US10/567,667 patent/US7303371B2/en active Active
- 2004-07-05 CN CNB2004800228347A patent/CN100395431C/zh not_active Expired - Fee Related
- 2004-07-05 DE DE502004008830T patent/DE502004008830D1/de active Active
- 2004-07-05 ES ES04740664T patent/ES2316994T3/es active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4425078A (en) * | 1980-07-18 | 1984-01-10 | United Technologies Corporation | Axial flexible radially stiff retaining ring for sealing in a gas turbine engine |
US4379560A (en) * | 1981-08-13 | 1983-04-12 | Fern Engineering | Turbine seal |
US5833244A (en) * | 1995-11-14 | 1998-11-10 | Rolls-Royce P L C | Gas turbine engine sealing arrangement |
US5609469A (en) * | 1995-11-22 | 1997-03-11 | United Technologies Corporation | Rotor assembly shroud |
US6164656A (en) * | 1999-01-29 | 2000-12-26 | General Electric Company | Turbine nozzle interface seal and methods |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2971590A4 (de) * | 2013-03-14 | 2016-01-20 | United Technologies Corp | Anordnung zur abdichtung eines spaltes zwischen komponenten eines turbinenmotors |
Also Published As
Publication number | Publication date |
---|---|
US20060245915A1 (en) | 2006-11-02 |
US7303371B2 (en) | 2007-12-04 |
DE502004008830D1 (de) | 2009-02-26 |
CN100395431C (zh) | 2008-06-18 |
PL1654440T3 (pl) | 2009-06-30 |
EP1654440A1 (de) | 2006-05-10 |
CN1833094A (zh) | 2006-09-13 |
EP1654440B1 (de) | 2009-01-07 |
ES2316994T3 (es) | 2009-04-16 |
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