EP1488077A1 - Gekühlte turbinenschaufel - Google Patents
Gekühlte turbinenschaufelInfo
- Publication number
- EP1488077A1 EP1488077A1 EP03702263A EP03702263A EP1488077A1 EP 1488077 A1 EP1488077 A1 EP 1488077A1 EP 03702263 A EP03702263 A EP 03702263A EP 03702263 A EP03702263 A EP 03702263A EP 1488077 A1 EP1488077 A1 EP 1488077A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- blade according
- bypass
- rib
- cooling gas
- 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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Definitions
- the invention relates to a turbine blade with the features of the preamble of claim 1.
- Such a turbine blade is known from DE 198 59 787 A1, which has a flow-around and aerodynamically shaped jacket.
- This jacket has a first side wall and a second side wall which are connected to one another on an upstream front edge and on a downstream side edge, which extend longitudinally from a blade root to a blade tip and which are connected to one another between the front edge and the rear edge by a plurality of inner ribs ,
- These ribs form two cooling gas paths in the interior of the turbine blade or in the interior of the jacket, each of which leads a cooling gas flow from the foot to the tip of the turbine blade and thereby deflect the cooling gas flow several times from outside to inside and from inside to outside in a serpentine shape.
- Such a serpentine cooling gas path thus consists of a series of 180 ° reversing arches.
- the ribs are arranged in such a way that in one cooling gas path in the area of the front edge and in the other cooling gas path in the area of the rear edge they protrude inwards from the jacket and at an angle of approximately 45 ° to the blade root. This results in an intensive braking of the cooling gas flow, which improves the cooling effect.
- Each cooling gas path begins in the blade root and ends at the tip of the blade, where the cooling gas can exit through a cover plate arranged at the tip approximately centrally in a hot gas path surrounding the turbine blade.
- the invention seeks to remedy this.
- the invention as characterized in the claims, deals with the problem of specifying an improved embodiment for a turbine blade of the type mentioned in the introduction, in which in particular the required cooling capacity can be guaranteed for a longer time and / or in which the risk of deposits in the cooling gas path is reduced.
- the invention is based on the general idea of using bypass openings and / or outlet openings in areas of extreme cooling gas deflection for the particles carried in the cooling gas flow. to provide an alternative flow path that the particles can follow more easily than the cooling gas path due to the acting inertial forces.
- the bypass openings and / or outlet openings enable the particles to be removed from these areas and thus prevent their accumulation in these deflection areas. Since the invention thus prevents or at least inhibits the formation of a deposit layer, the cooling effect of the cooling gas flow can be ensured for considerably longer, which increases the service life of the turbine blade.
- the proposed bypass openings on the jacket penetrate one of the ribs, so that the bypass flow thus created remains in the cooling gas path.
- the bypass opening on the jacket can penetrate a cover plate arranged at the tip, the bypass flow then escaping into the hot gas path.
- the Outlet openings proposed according to the invention penetrate the jacket in the region of a rib, so that the cooling gas exits through these outlet openings into the hot gas path. With a corresponding dimensioning of the outlet openings, a cooling gas film which lies against the outside of the jacket can be formed at the same time, so that the outlet openings can also work as film cooling openings.
- bypass openings penetrate the respective rib or the cover plate parallel to the jacket and in particular along the inside of the jacket.
- outlet openings if they penetrate the jacket in the region of the respective rib parallel to this rib and in particular are essentially aligned with an upstream side of the respective rib.
- At least one of the outlet openings can have a chamfered or rounded edge at its entrance, at least on the side closer to the blade tip.
- at least one of the outlet openings at its entrance on the side closer to the blade root can have a nose projecting inwards from the jacket.
- FIG. 2 is an enlarged view of a detail II from FIG. 1.
- a turbine blade 1 which can be designed as a moving blade or as a guide blade, has a casing 2 which is aerodynamically shaped on its outside 3.
- the turbine blade 1 extends into a hot gas path 4 of a turbine, which is otherwise not shown.
- the hot gas flow in the hot gas path 4 is symbolically represented by an arrow 5.
- the jacket 2 extends longitudinally from a blade tip 6, that is to say in its longitudinal direction, to a blade root 7, with which the blade 1 is anchored in a rotor (rotor blade) or in a housing (guide blade) in the usual way.
- the jacket 2 consists of two side walls 8 and 9, the first side wall 8 being arranged on the side of the blade 1 facing away from the viewer, so that only the inside thereof can be seen, and the second side wall 9 facing the viewer, but through the selected section is not recognizable.
- the two side walls 8, 9 are connected to one another on an upstream front edge 10 of the blade 1 and on an outflow side rear edge 11 of the blade 1 and thereby envelop an interior 12 of the turbine blade 1.
- the side walls 8, 9 are connected to one another in the interior 12 by internal or internal ribs 13.
- approximately half of the ribs 13 originate from the front edge 10 or from the rear edge 11, while the other half of the ribs 13 (inner rib 13) originate from a central web 14 which extends here extends over the entire length of the blade 1.
- the ribs 13 form two parallel cooling gas paths 15 in the interior 12 of the blade 1, which cooling paths 15 are identified in FIG. 1 by flow arrows.
- Each of these cooling gas paths 15 leads a cooling gas flow from the foot 7 to the tip 6 and thereby repeatedly causes a serpentine deflection directed from outside to inside and subsequently from inside to outside.
- the ribs 13 beginning at the front edge 10 and at the rear edge 11 extend from the jacket 2 on the one hand inwards and on the other hand to the foot 7, these ribs 13 enclosing an acute angle ⁇ with the jacket 2 on the side facing the foot 7 , which in the present case is approximately 45 °.
- This orientation of the outer ribs 13 results in a very strong deflection in the area of the acute angle ⁇ degasströmu ⁇ g, whereby an intensive heat transfer between jacket 2 and cooling gas can be achieved.
- the turbine blade 1 In the area of its tip 6, the turbine blade 1 has a cover plate 16 which contains at least one outlet opening 17 for each cooling gas path 15, through which the cooling gas exits into the hot gas path 4.
- the turbine blade 1 has bypass openings 18 and outlet openings 19 in the region of its ribs 13 that deflect the cooling gas flow from the outside inwards, that is to say in the region of its outer ribs 13 that begin at the front edge 10 or at the rear edge 11.
- the bypass openings 18 are arranged in this way that they penetrate the respective rib 13 on the jacket 2.
- the outlet openings 19 are arranged in the region of the respective rib 13 in such a way that they penetrate the jacket 2 at this rib 13.
- each cooling gas path 15 there is at least one bypass opening 20 in the cover plate 16, which penetrates the cover plate 16 on the jacket 2.
- these bypass openings 18, 20 and the outlet openings 19 are each formed in the region of the front edge 10 or in the region of the rear edge 11 in the ribs 13 or in the cover plate 16 or in the jacket 2.
- bypass openings 18 and 20 are expediently arranged such that, as in FIG. 2, they penetrate the respective rib 13 or the cover plate 16 parallel to the jacket and in particular along an inner side 30 of the jacket 2.
- successive outer ribs 13 are each equipped with such a bypass opening 18, so that several, in particular all, bypass openings 18 and 19 are arranged in alignment with one another in this special embodiment.
- bypass openings 18 and outlet openings 19 are alternately arranged in the outer ribs 13 following one another along the wall 2.
- the outlet openings 19 penetrate the jacket 2 expediently parallel to the respective outer rib 13.
- the outlet openings 19 are positioned such that they are essentially aligned with an inflow side 21 of the respective rib 13.
- a side 22 of the outlet opening 19 arranged closer to the tip 6 is aligned with this inflow side 21.
- This relationship is shown in more detail in FIG.
- This lower outer rib 13 also shows a special embodiment for the outlet opening 19, which has a cross section which widens from the inside to the outside.
- the throttle resistance of the outlet opening 19 can be configured in a suitable manner by the cross-sectional geometry.
- At least one of the outlet openings 19 can be designed at its entrance 23 by special measures such that larger particles 24, which are carried along by the cooling gas flow, are prevented from entering the outlet opening 19. In this way, clogging of the outlet opening 19 by particles 24 that are too large can be avoided.
- the inlet 23 can have a beveled or rounded edge 25, at least on the side 22 arranged closer to the tip 6, which makes it difficult for larger particles 24 to enter the outlet opening 19.
- a nose 27 can be formed at the entrance 23 on a side 26 of the outlet opening 19 arranged closer to the foot 7, which protrudes inwards from the jacket 2 and thus causes the particles 24 to be aerodynamically repelled. This measure also prevents larger particles 24 from being able to enter the outlet opening 19.
- the bypass openings 18 expediently have a larger cross section than the outlet openings 19.
- bypass openings 18 on the one hand and the outlet openings 19 on the other hand are dimensioned such that a sufficiently large cooling gas flow through the cooling gas path or paths 15 can still be ensured.
- the turbine blade 1 functions as follows:
- the cooling gas flow comes from the blade root 7 and for the most part follows the cooling gas path 15 along the flow-guiding ribs 13.
- the cooling gas flow carries small particles, for example with a diameter of less than 0.5 mm, and larger particles, for example with a diameter of about 0, 5 mm to about 3 mm, with itself.
- the particles 24 carried along in the flow cannot readily follow this strong deflection, since they basically follow a straight path due to the inertial forces. This finding is used by the invention, in which the bypass openings 18, 20 and the outlet openings 19 are arranged precisely there.
- heavier coarser particles 24 in particular can flow through the respective rib 13 through the bypass opening 18 in accordance with an arrow 28 shown with a broken line.
- Small particles 24 can also flow through the bypass opening 18.
- smaller particles 24 can also flow through the outlet opening 19 in accordance with an arrow 29 drawn with a dotted line and enter the hot gas path 4 through the jacket 2.
- the Pressure drop at the outlet opening 19 favors the entry of lighter particles 24 into the outlet opening 19, while heavier particles 24 tend to flow through the bypass opening 18.
- the particles 24 likewise reach the hot gas path 4 through the bypass opening 20.
- bypass openings 18, 20 and the outlet openings 19 effectively prevent deposits in the deflection area between the rib 13 and the jacket 2 and between the cover plate 16 and jacket 2. Since material deposits within the cooling gas paths 15 are thus avoided or inhibited in the turbine blade 1 according to the invention, the required cooling effect can be ensured for a long time, which is associated with an increased service life for the turbine blade 1.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH507022002 | 2002-03-25 | ||
CH5072002 | 2002-03-25 | ||
PCT/CH2003/000134 WO2003080998A1 (de) | 2002-03-25 | 2003-02-21 | Gekühlte turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1488077A1 true EP1488077A1 (de) | 2004-12-22 |
EP1488077B1 EP1488077B1 (de) | 2006-07-12 |
Family
ID=28048290
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03702263A Expired - Lifetime EP1488077B1 (de) | 2002-03-25 | 2003-02-21 | Gekühlte turbinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US7293962B2 (de) |
EP (1) | EP1488077B1 (de) |
AU (1) | AU2003205491A1 (de) |
DE (1) | DE50304226D1 (de) |
WO (1) | WO2003080998A1 (de) |
Families Citing this family (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1488077B1 (de) | 2002-03-25 | 2006-07-12 | ALSTOM Technology Ltd | Gekühlte turbinenschaufel |
GB0524735D0 (en) | 2005-12-03 | 2006-01-11 | Rolls Royce Plc | Turbine blade |
US7549843B2 (en) * | 2006-08-24 | 2009-06-23 | Siemens Energy, Inc. | Turbine airfoil cooling system with axial flowing serpentine cooling chambers |
US20090003987A1 (en) * | 2006-12-21 | 2009-01-01 | Jack Raul Zausner | Airfoil with improved cooling slot arrangement |
US7967567B2 (en) * | 2007-03-27 | 2011-06-28 | Siemens Energy, Inc. | Multi-pass cooling for turbine airfoils |
US7785070B2 (en) * | 2007-03-27 | 2010-08-31 | Siemens Energy, Inc. | Wavy flow cooling concept for turbine airfoils |
US8047788B1 (en) * | 2007-10-19 | 2011-11-01 | Florida Turbine Technologies, Inc. | Turbine airfoil with near-wall serpentine cooling |
US10286407B2 (en) | 2007-11-29 | 2019-05-14 | General Electric Company | Inertial separator |
US8105033B2 (en) * | 2008-06-05 | 2012-01-31 | United Technologies Corporation | Particle resistant in-wall cooling passage inlet |
US8167558B2 (en) * | 2009-01-19 | 2012-05-01 | Siemens Energy, Inc. | Modular serpentine cooling systems for turbine engine components |
US8096772B2 (en) * | 2009-03-20 | 2012-01-17 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall |
JP2011085084A (ja) * | 2009-10-16 | 2011-04-28 | Ihi Corp | タービン翼 |
US8616834B2 (en) * | 2010-04-30 | 2013-12-31 | General Electric Company | Gas turbine engine airfoil integrated heat exchanger |
US9074482B2 (en) | 2012-04-24 | 2015-07-07 | United Technologies Corporation | Airfoil support method and apparatus |
US11033845B2 (en) | 2014-05-29 | 2021-06-15 | General Electric Company | Turbine engine and particle separators therefore |
WO2016032585A2 (en) | 2014-05-29 | 2016-03-03 | General Electric Company | Turbine engine, components, and methods of cooling same |
US9915176B2 (en) | 2014-05-29 | 2018-03-13 | General Electric Company | Shroud assembly for turbine engine |
EP3149311A2 (de) | 2014-05-29 | 2017-04-05 | General Electric Company | Turbinenmotor und partikeltrenner dafür |
US10167725B2 (en) | 2014-10-31 | 2019-01-01 | General Electric Company | Engine component for a turbine engine |
US10036319B2 (en) | 2014-10-31 | 2018-07-31 | General Electric Company | Separator assembly for a gas turbine engine |
US10156157B2 (en) * | 2015-02-13 | 2018-12-18 | United Technologies Corporation | S-shaped trip strips in internally cooled components |
CN107429569B (zh) | 2015-04-03 | 2019-09-24 | 西门子公司 | 具有低流动框架式通道的涡轮动叶后缘 |
US10174620B2 (en) | 2015-10-15 | 2019-01-08 | General Electric Company | Turbine blade |
US9988936B2 (en) | 2015-10-15 | 2018-06-05 | General Electric Company | Shroud assembly for a gas turbine engine |
US10428664B2 (en) | 2015-10-15 | 2019-10-01 | General Electric Company | Nozzle for a gas turbine engine |
US10704425B2 (en) | 2016-07-14 | 2020-07-07 | General Electric Company | Assembly for a gas turbine engine |
EP3473808B1 (de) * | 2017-10-19 | 2020-06-17 | Siemens Aktiengesellschaft | Schaufelblatt für eine innengekühlte turbinenlaufschaufel sowie verfahren zur herstellung einer solchen |
US10669896B2 (en) * | 2018-01-17 | 2020-06-02 | Raytheon Technologies Corporation | Dirt separator for internally cooled components |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3527543A (en) * | 1965-08-26 | 1970-09-08 | Gen Electric | Cooling of structural members particularly for gas turbine engines |
US3533712A (en) * | 1966-02-26 | 1970-10-13 | Gen Electric | Cooled vane structure for high temperature turbines |
US3533711A (en) * | 1966-02-26 | 1970-10-13 | Gen Electric | Cooled vane structure for high temperature turbines |
GB2165315B (en) | 1984-10-04 | 1987-12-31 | Rolls Royce | Improvements in or relating to hollow fluid cooled turbine blades |
US4753575A (en) * | 1987-08-06 | 1988-06-28 | United Technologies Corporation | Airfoil with nested cooling channels |
US4820123A (en) * | 1988-04-25 | 1989-04-11 | United Technologies Corporation | Dirt removal means for air cooled blades |
EP0340149B1 (de) | 1988-04-25 | 1993-05-19 | United Technologies Corporation | Staubabscheider für eine luftgekühlte Schaufel |
US5700131A (en) | 1988-08-24 | 1997-12-23 | United Technologies Corporation | Cooled blades for a gas turbine engine |
GB2262314A (en) * | 1991-12-10 | 1993-06-16 | Rolls Royce Plc | Air cooled gas turbine engine aerofoil. |
US5368441A (en) * | 1992-11-24 | 1994-11-29 | United Technologies Corporation | Turbine airfoil including diffusing trailing edge pedestals |
US5611662A (en) * | 1995-08-01 | 1997-03-18 | General Electric Co. | Impingement cooling for turbine stator vane trailing edge |
US5842829A (en) * | 1996-09-26 | 1998-12-01 | General Electric Co. | Cooling circuits for trailing edge cavities in airfoils |
US6220817B1 (en) | 1997-11-17 | 2001-04-24 | General Electric Company | AFT flowing multi-tier airfoil cooling circuit |
US5997251A (en) * | 1997-11-17 | 1999-12-07 | General Electric Company | Ribbed turbine blade tip |
US5971708A (en) * | 1997-12-31 | 1999-10-26 | General Electric Company | Branch cooled turbine airfoil |
US5967752A (en) * | 1997-12-31 | 1999-10-19 | General Electric Company | Slant-tier turbine airfoil |
DE19921644B4 (de) | 1999-05-10 | 2012-01-05 | Alstom | Kühlbare Schaufel für eine Gasturbine |
GB2350867B (en) * | 1999-06-09 | 2003-03-19 | Rolls Royce Plc | Gas turbine airfoil internal air system |
US6186741B1 (en) * | 1999-07-22 | 2001-02-13 | General Electric Company | Airfoil component having internal cooling and method of cooling |
DE10064269A1 (de) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Komponente einer Strömungsmaschine mit Inspektionsöffnung |
EP1488077B1 (de) | 2002-03-25 | 2006-07-12 | ALSTOM Technology Ltd | Gekühlte turbinenschaufel |
-
2003
- 2003-02-21 EP EP03702263A patent/EP1488077B1/de not_active Expired - Lifetime
- 2003-02-21 DE DE50304226T patent/DE50304226D1/de not_active Expired - Lifetime
- 2003-02-21 WO PCT/CH2003/000134 patent/WO2003080998A1/de active IP Right Grant
- 2003-02-21 AU AU2003205491A patent/AU2003205491A1/en not_active Abandoned
-
2004
- 2004-09-27 US US10/949,521 patent/US7293962B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO03080998A1 * |
Also Published As
Publication number | Publication date |
---|---|
AU2003205491A1 (en) | 2003-10-08 |
EP1488077B1 (de) | 2006-07-12 |
US7293962B2 (en) | 2007-11-13 |
WO2003080998A1 (de) | 2003-10-02 |
DE50304226D1 (de) | 2006-08-24 |
US20050129508A1 (en) | 2005-06-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1488077B1 (de) | Gekühlte turbinenschaufel | |
EP0902167B1 (de) | Kühlvorrichtung für Gasturbinenkomponenten | |
DE60020007T2 (de) | Internes Luftkühlungssystem für Turbinenschaufeln | |
DE69916368T2 (de) | Partikelfalle im Kühlsystem von Gasturbinen | |
DE4119216C2 (de) | Tropfenabscheider | |
DE4126907C2 (de) | ||
DE4000248C2 (de) | ||
DE10330471A1 (de) | Vorrichtung zum Abscheiden von Fremdpartikeln aus der den Laufschaufeln einer Turbine zuführbaren Kühlluft | |
DE10248410A1 (de) | Vorrichtung zur Ausfilterung von Partikeln aus einer Strömung | |
DE2847814A1 (de) | Gasturbine | |
DE2202858B1 (de) | Gekuehlte leitschaufel fuer gasturbinen | |
DE102010051638A1 (de) | Gasturbinenbrennkammer mit einer Kühlluftzuführvorrichtung | |
WO2009109462A1 (de) | Schaufel für eine gasturbine | |
DE3322578C2 (de) | Sortiervorrichtung | |
DE112015001576T5 (de) | Flüssigkeitsabscheidevorrichtung | |
EP1292760B1 (de) | Konfiguration einer kühlbaren turbinenschaufel | |
DE2543878A1 (de) | Luftfuehrender kanal | |
EP2643595A1 (de) | Selbstreinigende schraubenzentrifugalradpumpe mit rezirkulation hinter dem schaufelrad | |
DE3333261C2 (de) | Vorrichtung zum pneumatischen oder hydraulischen Fördern von Schüttgut | |
EP3473808A1 (de) | Schaufelblatt für eine innengekühlte turbinenlaufschaufel sowie verfahren zur herstellung einer solchen | |
DE102017118583B4 (de) | Anordnung von Stützstreben in einem abstromseitigen Ringraum einer Gasturbine | |
EP1219779B1 (de) | Komponente einer Strömungsmaschine mit Inspektionsöffnung, und Verfahren zur Inspection und Reinigung einer solchen Komponente | |
EP2963243B1 (de) | Strömungsmaschine mit laufschaufeln mit in richtung der hinterkante abgesenkter schaufelspitze | |
EP2225467B1 (de) | Drallerzeugungsapparat und turbolader mit einem solchen drallerzeugungsapparat | |
DE4014574A1 (de) | Abgasduesengelenk |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20040914 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE GB |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REF | Corresponds to: |
Ref document number: 50304226 Country of ref document: DE Date of ref document: 20060824 Kind code of ref document: P |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20060923 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20070413 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 50304226 Country of ref document: DE Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE Ref country code: DE Ref legal event code: R081 Ref document number: 50304226 Country of ref document: DE Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH Ref country code: DE Ref legal event code: R081 Ref document number: 50304226 Country of ref document: DE Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20170727 AND 20170802 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 50304226 Country of ref document: DE Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE Ref country code: DE Ref legal event code: R081 Ref document number: 50304226 Country of ref document: DE Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20180219 Year of fee payment: 16 Ref country code: GB Payment date: 20180216 Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 50304226 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190221 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190903 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190221 |