EP0859127A1 - Disposition des canaux de réfroidissement dans une une dique du rotor d'une turbine - Google Patents

Disposition des canaux de réfroidissement dans une une dique du rotor d'une turbine Download PDF

Info

Publication number
EP0859127A1
EP0859127A1 EP98101045A EP98101045A EP0859127A1 EP 0859127 A1 EP0859127 A1 EP 0859127A1 EP 98101045 A EP98101045 A EP 98101045A EP 98101045 A EP98101045 A EP 98101045A EP 0859127 A1 EP0859127 A1 EP 0859127A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
disc
disk
duct
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
EP98101045A
Other languages
German (de)
English (en)
Other versions
EP0859127B1 (fr
Inventor
Thomas Schillinger
Neil Milner Evans
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0859127A1 publication Critical patent/EP0859127A1/fr
Application granted granted Critical
Publication of EP0859127B1 publication Critical patent/EP0859127B1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type

Definitions

  • the invention relates to a turbine impeller disk with disk fingers formed disc grooves for receiving turbine blades, as well as with Measures for guiding a cooling air flow from one in front of the pane into a room behind the window.
  • the technical environment becomes In addition to DE 29 47 521 A1, reference is made in particular to DE 34 44 586 A1.
  • a cooling air duct opening into the groove bottom of the disc groove can not arbitrarily with regard to its cross-sectional area be designed large, since the spatial Fields of the individual stress concentrations for the circumferential stresses superimpose and cause locally excessive voltage amplitudes can what is undesirable in terms of fatigue strength is.
  • the object of the present invention is to show remedial measures for these problems.
  • the solution to this problem is characterized in that at least in some of the disk fingers there is a cooling air skimming channel which starts from the front disk front side and which merges into a cooling air blow-out channel which likewise runs essentially in a radial direction in the disk finger and whose mouth opening is on the rear disk front side is closer to the disk axis than the disk ring section which has the disk grooves and is widened in the disk axis direction.
  • Advantageous training and further education are included in the subclaims.
  • At least one separate cooling air blow-out channel is in the
  • the first turbine impeller disk is provided, via which the second, for example, arranged behind the first wheel disc Turbine impeller disk is supplied with cooling air.
  • This cooling air exhaust duct runs in the first turbine impeller disk, for example at least partially in a disc finger of this impeller and is thereby by a cooling air skim, which also is at least partially provided in the corresponding disc finger with Cooling air supplied.
  • This cooling air skimming duct receives the cooling air flow while from the space in front of the front window face, while the cooling air blow-out channel then this cooling air flow in the behind the Promotes disc lying space.
  • this cooling air discharge channel is closer to the disc axis than that the disc grooves and, as usual, in the disc axis direction widened disc ring section is also no mixing of the cooling air flow with the working gas flow passed between the turbine blades to fear.
  • cooling air skim there is usually a single cooling air skim and a single cooling air exhaust duct may not be sufficient, so preferred several such channels are provided, each in one Disc finger.
  • this cooling air channels to promote or guide a cooling air flow from one in front of the turbine impeller disc to one behind the disc lying space in the disc fingers is provided by this Cooling channel system of course no weakening in the bottom of the groove To fear disk grooves. Rather, according to the invention, for example cooling air required for a second turbine impeller disk through the described cooling air ducts, namely the skimming duct and the blow-out channel is guided around the disk grooves.
  • Reference number 1 denotes an impeller disk of a gas turbine, which carries a large number of turbine blades 2 as usual.
  • Figures 2 and 4 one also recognizes a likewise usual closing plate 6, which is a turbine blade 2 secures in the corresponding disk groove 4.
  • the turbine blades 2 are air-cooled, i.e. inside each turbine blade 2, a cooling channel system 7 is provided, which by a Cooling air duct 8, the inside of the impeller 1 from the front Front 1a leads to the groove bottom of the disk groove 4, supplied with cooling air becomes.
  • space 9a the one in front of the disc 1 is significantly closer to the disc axis 3 lies, as the turbine blades 2 is thus - at least opposite the working gas passed between the turbine blades 2 relatively cool air flow.
  • cooling air blow-out channel 10 provided by one with the Room 9a communicating with cooling air skimming duct 11
  • Cooling air flow is supplied, both the cooling air skim 11 and also the cooling air exhaust duct 10 at least partially within one Disc fingers 5 run.
  • These cooling air channels 10 and 11 thus open not in the disc groove 4, but are in the disc fingers 5 on the Disk groove 4 passed. A weakening of the bottom of the groove Disc groove 4 can therefore not occur through these cooling air channels 10 and 11.
  • the cooling air discharge duct 10 in the disc finger 5 is essentially radial Direction, almost goes from the tip area 5 'of the disc finger 5 and lies closer with its mouth opening 10a to space 9b the disc axis 3, as that having the disc grooves 4, in the disc axis direction widened disc ring section 1 '. This ensures that the cooling air flow in space 9b does not coincide with that between mixed the working gas stream passed through the turbine blades 2.
  • the end of the cooling air discharge channel 10 opposite the opening 10a is connected to a so-called channel channel 12, into which the cooling air skimming channel 11 opens.
  • the inlet opening 11a of the cooling air skimming duct 11 on the front pane front side 1a is approximately at the same height as the outlet opening 10a of the blow-out duct 10, that is to say the inlet opening 11a likewise lies in an area in the space 9a in which a relatively cold air flow can be found .
  • the cooling air duct via the duct system described, namely at least via a skimming duct 11 in the radial direction outwards, then via the duct groove 12 and finally via the blow-out duct 10 again essentially in the radial direction inwards is not only with regard to the existing pressure conditions, but also Also particularly advantageous from a manufacturing point of view.
  • the skimming duct 11 open directly into the blow-out duct 10, on the one hand the angle of inclination of these two ducts 10, 11 would be unfavorable and the disk 1 would also be weakened unfavorably by these ducts.
  • This connection of the blow-out channel 10 with the skimming channel 11 via the channel channel 12 is also advantageous in that this channel channel 12 runs in the tip region 5 'of the disc finger 5 and can thus be open in the radial direction to the outside, ie this can actually be an act in the tip area 5 'milled groove running in the direction of the disc axis 3.
  • this side of the channel groove 12, which is open in the radial direction to the outside must be covered in order to achieve the desired cooling air guidance, which is why a so-called cover plate 13 is provided here.
  • This cover plate 13 thus delimits the channel groove 12 in the radial direction to the outside and can thereby be form-fitting be fixed between two turbine blades 2 and by the closing plates 6 also securing these turbine blades 2.
  • the cooling air skimming channel runs 11 in the tip area 5 'of the disc finger 5 substantially parallel to Disc axis 3 and is itself designed as a channel groove 12, the side open again in the radial direction with a cover plate 13 is covered.
  • the design of this channel channel 12 in the embodiment 4 is thus similar to that in the embodiment according to Figure 2.
  • the cooling air to be introduced into space 9b is one has the lowest possible total temperature in the rotating system Room 9a in front of the inlet opening 11a the air through this swirl nozzle 14 so highly swirling or with such a high peripheral speed, that the static pressure ratio between the area in front of this Inlet opening 11a and that passed between the turbine blades 2 Working gas flow just a penetration of the working gases in this Area in front of the entry opening 11a successfully prevented.
  • This ensures that the relative total inlet temperature according to the thermodynamic process control reached a minimum.
  • the guided cooling air experiences a reduction in the peripheral speed according to the change in the orbital radius. Because it it is a largely adiabatic process, the In the case of said overcurrent process, cooling air even works on the turbine impeller disk 1 from.
  • the exemplary embodiment according to FIG. 2 is also analogous to the exemplary embodiment 4, the cover plate 13, inter alia, by the closing plate 6 positively fixed. Furthermore, here the cover plate 13 in its End area facing the inlet opening 11a, a so-called catch apron 13 'on the inlet or inlet cross-section of the skimming channel 11 certainly.
  • the fact that the determining flow cross section for the in the cooling air mass flow entering space 9b from a separate one and replaceable part, namely the cover plate 13 with the defining Apron 13 'is formed, can - at least to a certain extent secondary turbine air system while maintaining the main components, namely in particular the impeller discs 1 quickly and inexpensively be varied and optimized.
  • an impeller disk 1 according to the invention is distinguished inter alia from the fact that a cooling air flow from space 9a in front of front end face 1a in a space 9b behind the rear end face 1b can be performed without thereby the area of the disk grooves 4th and in particular the groove bottom is weakened. Rather, that is shown Channel system with one, several or all disc fingers 5 skimming channel 11 and blow-out channel 10 in view to the tension load on the impeller disk 1 in the area of the disk grooves 4 even more advantageous since the impeller 1 in the area of this Disc grooves 4 through the cooling air in the duct system additionally is cooled. Voltage peaks caused by an uneven Temperature distribution in the disc 1 are thus caused avoided or reduced.
  • Cooling air channels 8, 10 and 11 can be designed as desired, i.e. the respective requirements be correspondingly circular, elliptical or otherwise shaped.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98101045A 1997-02-13 1998-01-22 Disposition des canaux de réfroidissement dans une une dique du rotor d'une turbine Expired - Lifetime EP0859127B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19705441A DE19705441A1 (de) 1997-02-13 1997-02-13 Turbinen-Laufradscheibe
DE19705441 1997-02-13

Publications (2)

Publication Number Publication Date
EP0859127A1 true EP0859127A1 (fr) 1998-08-19
EP0859127B1 EP0859127B1 (fr) 2000-06-14

Family

ID=7820089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98101045A Expired - Lifetime EP0859127B1 (fr) 1997-02-13 1998-01-22 Disposition des canaux de réfroidissement dans une une dique du rotor d'une turbine

Country Status (3)

Country Link
US (1) US5957660A (fr)
EP (1) EP0859127B1 (fr)
DE (2) DE19705441A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1705339A2 (fr) * 2005-03-23 2006-09-27 ALSTOM Technology Ltd Arbre de rotor, particulièrement pour une turbine à gaz
FR2981132A1 (fr) * 2011-10-10 2013-04-12 Snecma Ensemble pour turbomachine a refroidissement de disque

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7238008B2 (en) * 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
GB0513468D0 (en) * 2005-07-01 2005-08-10 Rolls Royce Plc A mounting arrangement for turbine blades
US8128365B2 (en) * 2007-07-09 2012-03-06 Siemens Energy, Inc. Turbine airfoil cooling system with rotor impingement cooling
CH699996A1 (de) * 2008-11-19 2010-05-31 Alstom Technology Ltd Verfahren zum bearbeiten eines gasturbinenläufers.
EP2233692A1 (fr) * 2009-03-27 2010-09-29 Siemens Aktiengesellschaft Rotor de turbomachine axiale doté d'un refroidissement d'aube
DE102009030353B3 (de) 2009-06-22 2010-12-02 Hofsaess, Marcel P. Kappe für einen temperaturabhängigen Schalter sowie Verfahren zur Fertigung eines temperaturabhängigen Schalters
DE102009039948A1 (de) 2009-08-27 2011-03-03 Hofsaess, Marcel P. Temperaturabhängiger Schalter
GB201016597D0 (en) 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement
ES2576736T3 (es) * 2010-11-15 2016-07-11 MTU Aero Engines AG Rotor para una turbomáquina
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
GB201020418D0 (en) * 2010-12-02 2011-01-19 Rolls Royce Plc Fluid impingement arrangement
US8622701B1 (en) * 2011-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade platform with impingement cooling
US9068461B2 (en) * 2011-08-18 2015-06-30 Siemens Aktiengesellschaft Turbine rotor disk inlet orifice for a turbine engine
EP2725191B1 (fr) * 2012-10-23 2016-03-16 Alstom Technology Ltd Turbine à gaz et aube de turbine pour une telle turbine à gaz
WO2015112226A2 (fr) * 2013-12-19 2015-07-30 United Technologies Corporation Élément aube pour support de plaque de protection segmentée
US10107102B2 (en) 2014-09-29 2018-10-23 United Technologies Corporation Rotor disk assembly for a gas turbine engine
US10458242B2 (en) * 2016-10-25 2019-10-29 Pratt & Whitney Canada Corp. Rotor disc with passages
KR102028804B1 (ko) * 2017-10-19 2019-10-04 두산중공업 주식회사 가스 터빈 디스크
FR3085420B1 (fr) * 2018-09-04 2020-11-13 Safran Aircraft Engines Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine
US11674395B2 (en) 2020-09-17 2023-06-13 General Electric Company Turbomachine rotor disk with internal bore cavity

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE573481C (de) * 1930-03-23 1933-04-01 Heinrich Ziegler Gasturbine mit Hohlschaufeln
US2447292A (en) * 1943-10-12 1948-08-17 Joseph E Van Acker Gas-actuated turbine-driven compressor
GB765225A (en) * 1954-02-18 1957-01-09 Parsons & Marine Eng Turbine Improvements in and relating to the cooling of gas turbine blades and rotors
GB801689A (en) * 1954-09-10 1958-09-17 Henschel & Sohn Ges Mit Beschr Improved cooled gas turbine rotor for high gas-temperatures
US2931624A (en) * 1957-05-08 1960-04-05 Orenda Engines Ltd Gas turbine blade
DE2357326A1 (de) * 1973-11-16 1975-05-28 Motoren Turbinen Union Turbine mit innenkuehlung des kranzes und sollbruchstellen
FR2381179A1 (fr) * 1977-02-18 1978-09-15 Rolls Royce Systeme de refroidissement de turbomachines
GB2057573A (en) * 1979-08-30 1981-04-01 Rolls Royce Turbine rotor assembly
DE3444586A1 (de) 1983-12-22 1985-07-04 United Technologies Corp., Hartford, Conn. Laufradanordnung in einer gasturbine
DE2947521A1 (de) 1978-11-27 1986-06-26 Snecma Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids
EP0353447A1 (fr) * 1988-07-29 1990-02-07 Westinghouse Electric Corporation Rainures pour l'insertion axiale des aubes de turbine dans un disque de rotor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE573481C (de) * 1930-03-23 1933-04-01 Heinrich Ziegler Gasturbine mit Hohlschaufeln
US2447292A (en) * 1943-10-12 1948-08-17 Joseph E Van Acker Gas-actuated turbine-driven compressor
GB765225A (en) * 1954-02-18 1957-01-09 Parsons & Marine Eng Turbine Improvements in and relating to the cooling of gas turbine blades and rotors
GB801689A (en) * 1954-09-10 1958-09-17 Henschel & Sohn Ges Mit Beschr Improved cooled gas turbine rotor for high gas-temperatures
US2931624A (en) * 1957-05-08 1960-04-05 Orenda Engines Ltd Gas turbine blade
DE2357326A1 (de) * 1973-11-16 1975-05-28 Motoren Turbinen Union Turbine mit innenkuehlung des kranzes und sollbruchstellen
FR2381179A1 (fr) * 1977-02-18 1978-09-15 Rolls Royce Systeme de refroidissement de turbomachines
DE2947521A1 (de) 1978-11-27 1986-06-26 Snecma Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids
GB2057573A (en) * 1979-08-30 1981-04-01 Rolls Royce Turbine rotor assembly
DE3444586A1 (de) 1983-12-22 1985-07-04 United Technologies Corp., Hartford, Conn. Laufradanordnung in einer gasturbine
EP0353447A1 (fr) * 1988-07-29 1990-02-07 Westinghouse Electric Corporation Rainures pour l'insertion axiale des aubes de turbine dans un disque de rotor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1705339A2 (fr) * 2005-03-23 2006-09-27 ALSTOM Technology Ltd Arbre de rotor, particulièrement pour une turbine à gaz
US7329086B2 (en) 2005-03-23 2008-02-12 Alstom Technology Ltd Rotor shaft, in particular for a gas turbine
EP1705339A3 (fr) * 2005-03-23 2013-11-06 Alstom Technology Ltd Arbre de rotor, particulièrement pour une turbine à gaz
FR2981132A1 (fr) * 2011-10-10 2013-04-12 Snecma Ensemble pour turbomachine a refroidissement de disque
WO2013054043A1 (fr) * 2011-10-10 2013-04-18 Snecma Refroidissement de la queue d ' aronde retenant une aube de turbomachine
US9631495B2 (en) 2011-10-10 2017-04-25 Snecma Cooling for the retaining dovetail of a turbomachine blade

Also Published As

Publication number Publication date
US5957660A (en) 1999-09-28
DE19705441A1 (de) 1998-08-20
DE59800172D1 (de) 2000-07-20
EP0859127B1 (fr) 2000-06-14

Similar Documents

Publication Publication Date Title
EP0859127B1 (fr) Disposition des canaux de réfroidissement dans une une dique du rotor d'une turbine
DE19921644B4 (de) Kühlbare Schaufel für eine Gasturbine
DE3226052C2 (de) Spaltdichtung für axial durchströmte Gasturbinen
EP1318272B1 (fr) Guide anti-tourbillon pour l'air de refroidissement dans le rotor d'une turbine à gaz
EP0621920B1 (fr) Refroidissement de la bande de protection d'une aube de turbine
EP1111189B1 (fr) Chemin d'air de refroidissement pour le rotor d'une turbine à gaz
EP0798448B1 (fr) Système et dispositif pour réfroidir une paroi chauffée d'un côté par un gaz chaud
DE3534905A1 (de) Hohle, durch ein stroemungsmittel gekuehlte turbinenschaufel
DE2221895A1 (de) Gasturbinentriebwerk
EP1503046A2 (fr) Dispositif de séparation de particules étrangères contenues dans des fluides de refroidissement d'aubes mobiles d'une turbine
WO2007110056A1 (fr) Piston de moteur à combustion interne
EP3121372A1 (fr) Roue de turbine refroidie pour un réacteur
DE1955966A1 (de) Gasreinigungsgerät
DE3007763A1 (de) Brenneinrichtung fuer gasturbinentriebwerke
DE3201784A1 (de) Mit lueftungskanaelen ausgestattetes, drehendes organ fuer eine bremse
DE19601818A1 (de) Turbinenschaufel-Anordnung mit einem Deckband
DE2902637A1 (de) Mehrkanaliger schalldaempfer fuer strahltriebwerke
DE102006018249A1 (de) Spindelförmiges Bauteil für eine Luftdüsenspinnvorrichtung mit einem Injektionskanal
DE4332693C2 (de) Innenbelüftete Bremsscheibe
DE602004010557T2 (de) Ringförmige Leitschaufelplattform einer Niederdruckstufe einer Gasturbine
EP1288435B1 (fr) Aube de turbine avec au moins un orifice de refroidissement
DE10331635B4 (de) Gekühlte Schaufel für eine Gasturbine
EP3321589A1 (fr) Buse de carburant d'une turbine à gaz dotée du générateur de tourbillons
DE19601819A1 (de) Turbinenschaufel-Anordnung mit einem gekühlten Deckband
EP3401503A1 (fr) Dispositif rotor d'une turbomachine

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: 19980915

AKX Designation fees paid

Free format text: DE FR GB

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19990520

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Owner name: ROLLS-ROYCE DEUTSCHLAND GMBH

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 59800172

Country of ref document: DE

Date of ref document: 20000720

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

Effective date: 20000808

ET Fr: translation filed
RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

REG Reference to a national code

Ref country code: FR

Ref legal event code: CJ

Ref country code: FR

Ref legal event code: CA

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
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: DE

Payment date: 20090302

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20090129

Year of fee payment: 12

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

Ref country code: FR

Payment date: 20090119

Year of fee payment: 12

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

Effective date: 20100122

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20100930

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: 20100201

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: 20100803

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: 20100122