EP1006263A1 - Refroidissement d'aube - Google Patents

Refroidissement d'aube Download PDF

Info

Publication number
EP1006263A1
EP1006263A1 EP98811184A EP98811184A EP1006263A1 EP 1006263 A1 EP1006263 A1 EP 1006263A1 EP 98811184 A EP98811184 A EP 98811184A EP 98811184 A EP98811184 A EP 98811184A EP 1006263 A1 EP1006263 A1 EP 1006263A1
Authority
EP
European Patent Office
Prior art keywords
blade
recess
cooling
insert element
channel
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
Application number
EP98811184A
Other languages
German (de)
English (en)
Other versions
EP1006263B1 (fr
Inventor
Hartmut Hähnle
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Switzerland GmbH
Original Assignee
ABB Schweiz AG
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ABB Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz AG
Priority to DE59810560T priority Critical patent/DE59810560D1/de
Priority to EP98811184A priority patent/EP1006263B1/fr
Priority to US09/450,729 priority patent/US6328532B1/en
Priority to CN99125857.6A priority patent/CN1261673C/zh
Publication of EP1006263A1 publication Critical patent/EP1006263A1/fr
Application granted granted Critical
Publication of EP1006263B1 publication Critical patent/EP1006263B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Definitions

  • the invention relates to devices for guiding the flow of a cooling fluid in one Cooling channel of an internally cooled blade of a turbomachine, in particular one Gas turbine.
  • turbomachines in particular gas turbines
  • the efficiency of turbomachines can be improved by increasing the pressure and the temperature of the fluid as parameters determining the cycle.
  • the fluid temperatures that are common today in the operation of turbomachinery, especially in the turbine inlet area, are already well above the permissible material temperatures of the components. Above all, the blading of the turbine is directly exposed to the hot fluid flow. The heat dissipation of the turbine blades caused by the heat conduction of the material is generally not sufficient to prevent the blades from overheating. Too high material temperatures initially lead to a decrease in the strength values of the material. This often leads to cracking in components. If the melting temperature of the material is exceeded, the component is locally or completely destroyed.
  • convection cooling is predominantly used as a cooling method for cooling blades by means of a cooling fluid, mostly cooling air, which is common today.
  • the cooling fluid is passed through the blades, which are each hollow or provided with cooling channels.
  • the material temperature that is set is therefore below the maximum permissible temperature of the blade material.
  • the cooling fluid usually flows out into the main flow via one or more openings in the blade wall. Often, however, the cooling fluid is also conducted into another internal chamber at the end of the cooling channel and from there into another cooling channel or also into the main flow.
  • Another method for cooling blades is the so-called film cooling.
  • a cooling fluid usually also cooling air, which is supplied in cooling channels, is blown out onto the blade surface through openings in the blade.
  • the cooling fluid forms a separating layer, similar to a fluid film, between the blade wall and the hot flow fluid. Thus there is no direct heat transfer between the hot fluid of the main flow and the blade.
  • the invention has for its object the flow of a cooling fluid of a cooled Guide blade of a turbomachine.
  • At least one insertion element is arranged in at least one recess in the blade for guiding the cooling fluid.
  • the blade has at least one supply opening for supplying cooling fluid into the cooling channel and moreover at least one further opening.
  • the cutout and the insertion element extend in the longitudinal direction of the blade only over a partial area of the blade.
  • the insert element projects at least partially into at least one cooling channel of the blade.
  • the recess and the insertion element are preferably designed with a rectangular or slot-shaped cross section.
  • the cross section to be considered here is the cross section perpendicular to the insertion direction of the insertion element. It is particularly expedient to carry out the dimensions of the cutout and of the insertion element in the form of an interference fit.
  • the insert element can be inserted into the recess by means of a positive connection.
  • the insertion element is often also soldered appropriately.
  • the recess can be manufactured and processed in a simple manner in terms of production technology.
  • the outer contour of the insert element is advantageously adapted to the contour of the blade profile at the point of the recess. In this way, tripping point-like transitions in the course of the wall contour of the blade are avoided. Such tripping point-like transitions would lead to higher flow losses in the main flow of the turbomachine.
  • at least the insert element has a shoulder or a continuously reducing cross-section.
  • the cross section of the insert element is advantageously reduced in the insertion direction of the insert element into the recess.
  • the recess is expediently designed in the same way so that the insert element can be inserted into the recess by means of a positive connection.
  • the insert element arranged in this way also advantageously has at least one flow channel arranged in the insert element.
  • a groove is preferably arranged in the insertion element such that this groove forms the flow channel together with the adjacent top wall and / or an adjacent side wall of the blade.
  • the flow channel is connected to the cooling channel via at least one opening and moreover preferably has at least one outlet opening.
  • the flow channel is usually designed with a smaller flow cross section than the cooling channel.
  • the outlet opening of the flow channel is particularly expedient to design the outlet opening of the flow channel as a through opening in the adjacent top wall and / or an adjacent side wall. If the cooling channel has no further outlet openings, the entire cooling fluid supplied to the cooling channel flows through the flow channel. If there are further outlet openings of the cooling channel, the cooling fluid mass flow is divided accordingly. If several cooling channels are arranged in the blade or the cooling channel is subdivided into partial channels, the outlet opening of the flow channel can also expediently open into a further cooling channel or a further partial channel of the cooling channel. It was found that by means of such a flow channel, the cooling fluid can be guided in a targeted manner along the adjacent top wall and / or the adjacent side wall. This enables targeted cooling of wall areas that were previously poorly or not at all cooled.
  • the recess and the insertion element are also advantageous to arrange the recess and the insertion element so that the in the recess arranged insert element directly to the top wall and / or at least one side wall is adjacent or at least partially in the top wall and / or Sidewall is integrated and at least one opening of the cooling channel at least partially closed.
  • the cooling channel is additional to the inlet opening and the outlet openings further or too large openings through which the cooling fluid would escape too quickly. Such openings can occur, for example, as a result of casting core mounts due to casting technology.
  • FIG. 1 shows an internally cooled blade 110 of a turbomachine with a recess 121 according to the invention and one according to the invention in the recess arranged insertion element 120.
  • the blade 110 shown is in the region of the Insert element 120 executed without a cover tape.
  • the one running in the blade 110 Cooling channel is not shown in Figure 1.
  • the recess 121 and the insertion element 120 are here approximately vertical in the area of the blade tip in an advantageous embodiment arranged to the blade height direction 118.
  • the Recess 121 and the insert element 120 in the area of maximum blade thickness in the Blade arranged and extend in the longitudinal direction of the blade only over a portion the shovel.
  • the recess 121 and the insert element 120 have a rectangular shape Cross section on.
  • the cross section considered here is the cross section perpendicular to Direction of insertion of the insertion element.
  • the dimensions of the recess 121 and the Insert elements 120 are expediently realized with one another as a press fit.
  • the insert element is fixed in the recess by means of soldering. This makes it in one simple and inexpensive way possible to insert the insert element in the recess fasten.
  • the outer contour of the insert element 120 is the blade profile contour adjusted at the location of the recess. As a result, trip hazards become Transitions in the contour of the blade avoided.
  • FIG. 2 the arrangement according to the invention of the insertion element 220 in the cutout 221 of the blade 210 is shown in perspective in a section through the blade 210.
  • the blade 210 which is hollow on the inside, has, in addition to a pressure-side and a suction-side wall 211, a top wall 212 which closes off the cavity inside the blade.
  • the cavity inside the blade serves here as a one-piece cooling channel 213 of the blade 210.
  • the cooling fluid 230 is fed to the blade through a feed opening in the blade root, not shown in the figure.
  • the insertion element 220 shown in FIG. 2 is arranged in the blade tip region approximately perpendicular to the blade height direction in the recess 221.
  • the recess 221 and the insert element 220 only extend over a partial area of the blade 210, whereas both the recess 221 and the insert element 220 extend continuously in the blade thickness direction from the pressure side to the suction side of the blade.
  • the outer contours of the insert element 220 are expediently adapted to the outer profile contours of the blade 210, and thus the pressure-side and suction-side blade profile contours.
  • the recess 221 and the insertion element 220 are each designed with a cross-section that is matched to one another and are joined together by means of an interference fit.
  • the flat top of the insert element 220 directly adjoins the inside of the blade of the top wall 212.
  • the insert element 220 in the illustrated embodiment of the invention has a plurality of grooves such that two grooves arranged separately from one another on the upper side of the insert element 220 form two flow channels 222 together with the top wall 212. These flow channels 222 thus run parallel to the top wall 212 along this.
  • the flow channels 212 are connected to the cooling channel 213 of the blade 210 via further openings 223 arranged in the front end face of the insertion element 220. Cooling fluid 230 can thus flow from the cooling channel 213 into the flow channels 222.
  • the illustrated flow channels 222 and the openings 223 are designed as rectangular grooves; the designs of the grooves are, however, basically freely selectable.
  • an outlet opening 224 realized as a through opening is arranged in the top wall 212 or in the side wall 211 for each flow duct 222.
  • FIG. 3 shows the arrangement of the passage opening 224 in the side wall 211 of the blade in FIG an enlargement.
  • the passage opening 224 is designed here as a bore and runs placed obliquely to the surface of the side wall 211.
  • the passage opening opens here at the closed end of the flow channel 222 in this.
  • the angle of attack of the Passage openings 224 were advantageously chosen here so that emerging fluid unites has as small a misalignment as possible to the main flow flowing around the blade. If the cooling fluid 230 in the blade 210 has a higher resting pressure than that Fluid flowing around the blade of the main flow, then flows out of the cooling channel 213 Flow channel 222 supplied cooling fluid through the passage openings 224 in the Main flow.
  • a continuous cooling fluid flow is thus formed through the Flow channels and the passage openings.
  • FIG. 4 shows a side view of a section through an internally cooled blade with a further embodiment of the insert element 320 arranged according to the invention in the recess 321.
  • the section runs in the center of the blade and shows, in addition to the cut top wall 312 of the blade, a section of the cooling channel 313 running in the blade.
  • the arrangement of the recess 321 was chosen here so that part of the recess 321 extends into the top wall 312.
  • the insertion element 320 inserted into the recess 321 is also partially fitted into the top wall 312 here.
  • the insert element 320 expediently has a rectangular cross section. The insert element is thus positioned in the recess by means of a positive connection.
  • the insert element and the cutout can also be designed with other cross sections, for example with oval, trapezoidal, rhomboidal or polygonal cross sections, which, however, are then in turn to be coordinated with one another.
  • the insert element 320 in the embodiment shown has two grooves, which are shown in the center in FIG. 4. The groove arranged on the upper side of the insert element, together with the adjacent top wall 312, forms a flow channel 322 running parallel to the top wall on the underside of the top wall. This flow channel 322 is via the opening 323 through the second one, which is arranged on the end face of the insert element 320 Groove is formed, connected to the cooling channel 313.
  • the opening 323 could also be designed as a bore provided in the insertion element.
  • a passage opening 324 is made in the top wall 312 by means of an obliquely positioned bore. This passage opening 324 opens into the end of the flow channel 322, which is closed toward the cooling channel. Cooling fluid 330 flows from the cooling channel 313 via the flow channel 322 arranged in the insertion element 320 into the passage opening 324 and from there onto the top of the top wall 312 and thus into the main flow flowing around the blade. By means of the cooling fluid 330 guided in the flow channel 322, a targeted cooling of the wall adjoining the flow channel 322 is established. Furthermore, the passage opening 324 can be designed with a larger cross section due to the upstream arrangement of the flow channel 322 and the pressure loss occurring in the flow channel 322 compared to an arrangement without an upstream flow channel. This leads to a lower risk of clogging the passage openings during the operation of a turbomachine due to foreign particles.
  • FIG. 5 Another embodiment of the invention is shown in Figure 5 in a section through a internally cooled shovel shown.
  • the cooling channel shown here is by a Partition 417 divided into two sub-channels 415, 416.
  • the arrangement according to the invention of the insert element 420 in the recess 421 of the blade in the one shown here Implementation of the invention corresponds to the arrangement according to Figure 4. This correspondence limits the freely and independently selectable configurations of the Invention in Figures 4 and 5 is not a.
  • this flows out Cooling fluid 430 does not enter the main flow, but is introduced by means of the insertion element 420 diverted from the first sub-channel 415 of the cooling channel into the second sub-channel 416.
  • the flow channel 422 arranged in the insertion element 420 is in each case by means of a Opening 423 connected to the respective sub-channels 415, 416. That in that Flow channel 422 along the top wall 412 from the first sub-channel 415 into the second Sub-channel 416 flowing cooling fluid 430 leads to a targeted cooling of the Cover wall 412.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98811184A 1998-11-30 1998-11-30 Refroidissement d'aube Expired - Lifetime EP1006263B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59810560T DE59810560D1 (de) 1998-11-30 1998-11-30 Schaufelkühlung
EP98811184A EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube
US09/450,729 US6328532B1 (en) 1998-11-30 1999-11-30 Blade cooling
CN99125857.6A CN1261673C (zh) 1998-11-30 1999-11-30 叶片冷却

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811184A EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube

Publications (2)

Publication Number Publication Date
EP1006263A1 true EP1006263A1 (fr) 2000-06-07
EP1006263B1 EP1006263B1 (fr) 2004-01-07

Family

ID=8236462

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811184A Expired - Lifetime EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube

Country Status (4)

Country Link
US (1) US6328532B1 (fr)
EP (1) EP1006263B1 (fr)
CN (1) CN1261673C (fr)
DE (1) DE59810560D1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005013464B3 (de) * 2005-03-21 2006-08-24 Voith Turbo Gmbh & Co. Kg Verfahren zur Herstellung eines Schaufelrades mit in einzelnen Schaufeln integrierten Öffnungen, insbesondere Auslassöffnungen
EP3101230B1 (fr) * 2015-05-29 2019-12-25 General Electric Company Composant de turbine à canaux de refroidissement de surface et son procédé de fabrication
EP3597859A1 (fr) * 2018-07-13 2020-01-22 Honeywell International Inc. Aube de turbine avec système de refroidissement tolérant à la poussière

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001049975A1 (fr) * 2000-01-06 2001-07-12 Damping Technologies, Inc. Amortisseur pour moteur a turbine
DE10064265A1 (de) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel
US6749400B2 (en) * 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
US6976826B2 (en) * 2003-05-29 2005-12-20 Pratt & Whitney Canada Corp. Turbine blade dimple
EP1847696A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Composant pour un système de post-combustion dans une turbine à gaz et turbine à gaz associée.
US7721844B1 (en) 2006-10-13 2010-05-25 Damping Technologies, Inc. Vibration damping apparatus for windows using viscoelastic damping materials
US8082707B1 (en) 2006-10-13 2011-12-27 Damping Technologies, Inc. Air-film vibration damping apparatus for windows
US8167572B2 (en) * 2008-07-14 2012-05-01 Pratt & Whitney Canada Corp. Dynamically tuned turbine blade growth pocket
US20130051976A1 (en) * 2011-08-29 2013-02-28 General Electric Company Flow control module for a turbomachine
US10914320B2 (en) * 2014-01-24 2021-02-09 Raytheon Technologies Corporation Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
US9645120B2 (en) 2014-09-04 2017-05-09 Grant Nash Method and apparatus for reducing noise transmission through a window
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine
CN110142426B (zh) * 2019-06-12 2023-12-08 温岭市文昌数控机床设备有限公司 一种数控刀塔冷却结构
US12215597B1 (en) * 2024-01-26 2025-02-04 Pratt & Whitney Canada Corp. Gas turbine engine rotor blade geometry and method for selecting same

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2176315A5 (en) * 1972-03-15 1973-10-26 Neu Ets Turbine blades - of metal deposited on a lightweight (polyamide) or fusible core
US3825984A (en) * 1972-03-02 1974-07-30 Gen Electric Method for fabricating a hollow blade
US3867068A (en) * 1973-03-30 1975-02-18 Gen Electric Turbomachinery blade cooling insert retainers
US4177010A (en) * 1977-01-04 1979-12-04 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5390509A (en) * 1977-01-20 1978-08-09 Koukuu Uchiyuu Gijiyutsu Kenki Structure of air cooled turbine blade
US5405242A (en) * 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5259730A (en) * 1991-11-04 1993-11-09 General Electric Company Impingement cooled airfoil with bonding foil insert
DE19709607A1 (de) * 1997-03-08 1998-09-10 Abb Research Ltd Leitschaufel für Dampfturbinen

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3825984A (en) * 1972-03-02 1974-07-30 Gen Electric Method for fabricating a hollow blade
FR2176315A5 (en) * 1972-03-15 1973-10-26 Neu Ets Turbine blades - of metal deposited on a lightweight (polyamide) or fusible core
US3867068A (en) * 1973-03-30 1975-02-18 Gen Electric Turbomachinery blade cooling insert retainers
US4177010A (en) * 1977-01-04 1979-12-04 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005013464B3 (de) * 2005-03-21 2006-08-24 Voith Turbo Gmbh & Co. Kg Verfahren zur Herstellung eines Schaufelrades mit in einzelnen Schaufeln integrierten Öffnungen, insbesondere Auslassöffnungen
EP3101230B1 (fr) * 2015-05-29 2019-12-25 General Electric Company Composant de turbine à canaux de refroidissement de surface et son procédé de fabrication
EP3597859A1 (fr) * 2018-07-13 2020-01-22 Honeywell International Inc. Aube de turbine avec système de refroidissement tolérant à la poussière
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
US11333042B2 (en) 2018-07-13 2022-05-17 Honeywell International Inc. Turbine blade with dust tolerant cooling system

Also Published As

Publication number Publication date
CN1255581A (zh) 2000-06-07
EP1006263B1 (fr) 2004-01-07
CN1261673C (zh) 2006-06-28
DE59810560D1 (de) 2004-02-12
US6328532B1 (en) 2001-12-11

Similar Documents

Publication Publication Date Title
EP1006263B1 (fr) Refroidissement d'aube
DE60018817T2 (de) Gekühlte Gasturbinenschaufel
DE3211139C1 (de) Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
DE69324506T2 (de) Gekühlte turbinenschaufel
EP1267039B1 (fr) Configuration de refroidissement du bord de fuite d'une aube
EP1113145B1 (fr) Aube pour turbine a gaz avec section de mesure sur le bord de fuite
DE602004003331T2 (de) Kühlluftauslass-Schlitze von Turbinenschaufeln
DE3534905C2 (de) Gekühlte hohle Turbinenschaufel
DE69302614T2 (de) Gekühlte Schaufel für eine Turbomaschine
DE60015233T2 (de) Turbinenschaufel mit interner Kühlung
DE69808056T2 (de) Verfahren zur herstellung innerer hohlräume in gegenständen und dadurch geformte gegenstände
DE60024517T2 (de) Turbinenwand mit Rillen an der Innenseite
DE102009003327B4 (de) Turbinenlaufschaufel-Spitzendeckband
DE3789514T2 (de) Gekühlte Gasturbinenschaufel.
EP1789654B1 (fr) Pale de turbomachine a couronne a refroidissement fluidique
EP1013884A2 (fr) Aube de turbine avec plateforme refroidie
DE60021650T2 (de) Kühlkanäle mit Tublenzerzeugern für die Austrittskanten von Gasturbinenleitschaufeln
EP1008723B1 (fr) Refroidissement de plateformes de turbomachines
EP1191189A1 (fr) Aube de turbine à gaz
DE102011055375A1 (de) Turbomaschinenleitschaufel und Verfahren zur Kühlung einer Turbomaschinenleitschaufel
CH698339A2 (de) Turbinenschaufel mit einem gekühlten Deckband.
EP1126136B1 (fr) Aube de turbine avec carenage d'extremité refroidie
EP1219780B1 (fr) Dispositif et procédé de refroidissement d'un élément d'une turbomachine par jet
EP0973998B1 (fr) Procede pour refroidir une aube de turbine
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale

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

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20001027

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ABB (SCHWEIZ) AG

AKX Designation fees paid

Free format text: DE FR GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

17Q First examination report despatched

Effective date: 20020702

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM (SWITZERLAND) LTD

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 FR 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: 59810560

Country of ref document: DE

Date of ref document: 20040212

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
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: 20041008

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810560

Country of ref document: DE

Representative=s name: UWE ROESLER, DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120802 AND 20120808

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810560

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810560

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810560

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810560

Country of ref document: DE

Owner name: ALSTOM TECHNOLOGY LTD., CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ALSTOM TECHNOLOGY LTD., CH

Effective date: 20120918

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810560

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: 59810560

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810560

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: ALSTOM TECHNOLOGY LTD, CH

Effective date: 20161110

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20161121

Year of fee payment: 19

Ref country code: FR

Payment date: 20161118

Year of fee payment: 19

Ref country code: GB

Payment date: 20161122

Year of fee payment: 19

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810560

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: 59810560

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170824 AND 20170830

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Effective date: 20171221

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59810560

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20171130

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180602

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130