EP2459934B1 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz Download PDF

Info

Publication number
EP2459934B1
EP2459934B1 EP10747801.8A EP10747801A EP2459934B1 EP 2459934 B1 EP2459934 B1 EP 2459934B1 EP 10747801 A EP10747801 A EP 10747801A EP 2459934 B1 EP2459934 B1 EP 2459934B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
housing
combustion chamber
perforated plate
turbine combustion
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.)
Active
Application number
EP10747801.8A
Other languages
German (de)
English (en)
Other versions
EP2459934A2 (fr
Inventor
Jaman El Masalme
Emil Aschenbruck
Reiner Brinkmann
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.)
Everllence SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2459934A2 publication Critical patent/EP2459934A2/fr
Application granted granted Critical
Publication of EP2459934B1 publication Critical patent/EP2459934B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a gas turbine combustion chamber having a housing, a flame tube accommodated therein and a perforated plate surrounding this, which is fastened to the housing at a front end, and a gas turbine, in particular a stationary gas turbine, with such a gas turbine combustor.
  • combustion air a fluid, usually called air and therefore generalized hereinafter as combustion air, first compressed to a higher pressure level and burned as a combustion air-fuel mixture in a combustion chamber before in a turbine enthalpy of the exhaust gas is converted into mechanical energy and as useful power is available.
  • the combustion chamber experiences both high pressure and temperature loads due to the pressure level and the combustion. Therefore, it has hitherto been customary in the prior art to reinforce the housing of the combustion chamber by inner and / or outer stiffening ribs, to use highly heat-resistant materials and to provide a so-called flame tube in the housing, which limits the combustion zone and thus at least partially shields the housing against the combustion heat ,
  • an impingement cooling of the flame tube known.
  • a perforated plate surrounding the flame tube is provided. Compressed combustion air hits through holes in the perforated plate from the outside to the flame tube and cools this before it is fed by a radial swirl generator the Flammrohrinnen- or combustion chamber and burned there.
  • the US 6,134,877 shows a gas turbine combustor having a housing, a flame tube accommodated therein and a conical cylinder surrounding it, having in a downstream region openings for impingement cooling a region of decreasing diameter of the flame tube and at one front end attached to the housing.
  • a folded region By a folded region, an axial compliance of the cylinder is introduced to allow thermal expansion.
  • the cylinder opens with its other front end in the turbine outlet.
  • the US 5,784,876 shows a generic gas turbine combustor. From the JP 58 210413 A and the DE 197 51 299 A1 In each case, combustors for gas turbine burners with various wall / housing structures are disclosed.
  • the object of the present invention is therefore to improve a gas turbine or its combustion chamber.
  • a gas turbine combustion chamber according to the preamble of claim 1 is further developed by its characterizing features.
  • Claim 9 provides a gas turbine with at least one gas turbine combustor according to the invention under protection, the dependent claims relate to advantageous developments.
  • the present invention is based on the idea to reduce or replace previously required stiffening ribs of the housing by integrating or integrating the perforated plate as a support structure on both sides into the housing structure and thus increasing the structural rigidity and / or strength of the housing.
  • a gas turbine combustor for this purpose, comprises a housing with a flame tube received therein and a perforated plate surrounding it at least partially, which is fastened to the housing at an end face, wherein the perforated plate is likewise fastened to the housing at its other front end, wherein the housing is an outer casing of the combustion chamber and forms an annular chamber which is formed from a plurality of parts welded together sheets, wherein the gas turbine combustor at a End face has an annular plate of a swirl generator and at the other end a flange for attachment to a turbine housing and the perforated plate is integrally formed and is secured via welds on the one hand at both ends with an annular plate or the flange and on the other hand attached to the annular chamber, so that its two end-side end portions form integral parts of the outer housing and loads of the housing are received and transmitted by the perforated plate.
  • the perforated plate in addition to the flow guide and cooling according to the invention also used for transmitting loads of the housing and this is connected on both sides of the housing, the strength and / or rigidity of the housing can be increased without increasing its weight by excessive inner or outer ribs.
  • the perforated plate at least in a primary combustion region of the flame tube, has cooling openings, in particular bores and / or slot openings, for impingement cooling of the flame tube.
  • the cooling holes for example, an angular offset of axially adjacent cooling holes, so that the perforated plate has network structure, or axially aligned cooling holes, so that the perforated plate axially continuous webs, by slits in the axial and / or circumferential direction of the perforated plate and / or a limitation of the number and / or diameter of the cooling openings can be adjusted, in particular axial, rigidity and strength of the perforated plate.
  • the annular chamber urges the perforated plate with combustion air, so as to preferably cool this thermally highly stressed axial portion of the flame tube.
  • the annular chamber is preferably designed such that the entire supplied combustion air is supplied to the flame tube through cooling openings of the perforated plate and, for this purpose, may preferably extend substantially in the primary combustion region in the axial direction.
  • the perforated plate can define or define the annular chamber radially from the inside and extend axially on one or both sides beyond the annular chamber adjoining it from outside.
  • the annular chamber can put on the outside of the perforated plate, which is thus structurally integrated as part of the outer housing in this.
  • the perforated plate is permanently attached to both sides of welds on welds on the housing.
  • structural loads can be transferred particularly favorably between housing and perforated plate.
  • the perforated plate can have one or more sections which delimit a combustion air feed to the outside environment.
  • Such sections may be formed with a section having cooling openings in one or more parts, in particular ur- or reshaped with each other.
  • the housing at least in the region of the perforated plate, be formed largely free of ribs.
  • the swirl generator is a radial swirl generator.
  • the housing can be advantageously formed thinner walls.
  • one or more corresponding areas of the housing and the perforated plate have substantially the same wall thickness.
  • regions at the same axial height of the combustion chamber are referred to as corresponding regions.
  • the flame tube is axially fixed at its upstream front end to the housing. Due to the connection on both sides of the perforated plate, the larger clearance or the larger thermal expansions can occur in an upstream head region of the combustion chamber occur, so that it may be advantageous to now provide the fixed storage of a fixed-mounted flame tube there.
  • Fig. 1 is, as stated in the introduction, shown a gas turbine according to the prior art with two external combustion chambers, the housing 100 are reinforced with stiffening ribs 110 and thus complicate the handling by their higher weight and burden the underlying turbine housing to which they are attached.
  • Fig. 2 shows a gas turbine combustor according to an embodiment of the present invention in axial or longitudinal section to replace the in Fig. 1 shown combustion chambers.
  • a flame tube 2 In its interior, a flame tube 2 defines a combustion chamber. This is supplied by a radial swirl generator 5, a combustion air-fuel mixture B, burned substantially in a cylindrical primary combustion zone of the combustion or flame tube interior and the exhaust gas A from there to a turbine (not shown) supplied.
  • the outer housing 1 of the combustion chamber forms an annular chamber 1 which is formed in several parts from sheet-metal parts welded together.
  • the one-piece perforated plate 3 is on welds 8 on the one hand at both ends with an annular plate 6 of the swirl generator 5 and a flange for attachment of the outer combustion chamber to a turbine housing (not shown) and on the other hand attached to the annular chamber 1, so that its two end-side end portions 3.1, 3.2 form integral parts of the outer housing.
  • the perforated plate is formed axially in several parts with a central part having the cooling holes 4 and the front side in each case to the annular chamber 1 or edge strips 3.1, 3.2 of the perforated plate is welded.
  • the plate 6 of the swirl generator 5 and the flange, to which the perforated plate 3 forming part of the outer housing is welded, are connected via screw connections 7.1, 7.2 to a cover or turbine housing (not shown).
  • the perforated plate 3 for transmitting loads of the housing 1 and for this purpose at its front ends 3.1, 3.2 attached to the housing, it can in addition to its function, combustion air V to be directed to the flame tube 2 and to the swirl generator lead to reinforce the housing. This can therefore, at least in the reinforced by the tethered perforated plate area, largely free of ribs and thus easier to be formed.
  • the perforated plate can also be advantageous, especially in low-load areas 3.1, 3.2, directly form the outer housing, which makes the construction of the combustion chamber advantageously more compact and manufacturing technology cheaper. Since the perforated plate defines the annular chamber radially from the inside and subsequently defines the combustion air supply to the swirl generator in the regions 3.1, 3.2 as the outer housing, the entire combustion air serves to cool the flame tube in a structurally advantageous manner. At the same time by placing the annular chamber 1 outside of the axially projecting beyond the perforated plate. 3 this perforated plate, the front-side edge portions 3.1, 3.2 act as part of the outer housing, integrated in a structurally advantageous manner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Claims (10)

  1. Chambre de combustion de turbine à gaz comportant un carter (1), un tube foyer (2) renfermé à l'intérieur de celle-ci et une tôle perforée (3) entourant celui-ci au moins partiellement, qui est fixée à une extrémité frontale (3.1) sur le carter (1), dans laquelle la tôle perforée (3) est fixée sur son autre extrémité frontale (3.2) également sur le carter (1), dans laquelle le carter (1) est un carter extérieur (1) de la chambre de combustion et forme une chambre annulaire (1), qui est formée en plusieurs parties par des tôles soudées les unes aux autres, dans laquelle la chambre de combustion de turbine à gaz présente sur un côté frontal (3.2) une bride pour la fixation à un carter de turbine, caractérisée en ce que la chambre de combustion de turbine à gaz présente sur l'autre côté frontal (3.1) une plaque annulaire (6) d'un générateur de tourbillon (5) et la tôle perforée (3) est configurée en un seul tenant et est fixée par l'intermédiaire de joints de soudure (8) d'un côté sur les deux côtés frontaux (3.1,3.2) avec la plaque annulaire (6), respectivement est fixée sur la bride et d'un autre côté est fixée sur la chambre annulaire (1), de sorte que ses deux zones d'extrémité frontales (3.1,3.2)forment des parties intégrales du carter extérieur et les charges du carter (1) soient absorbées et transmises par la tôle perforée.
  2. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que la tôle perforée présente au moins dans une zone de combustion primaire du tube foyer des ouvertures de refroidissement (4) pour le refroidissement par impact du tube foyer (2).
  3. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que le carter est configuré sans nervures au moins au niveau de la tôle perforée.
  4. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que le générateur de tourbillon (5) est un générateur de tourbillon radial.
  5. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que au moins une zone correspondante du carter et de la tôle perforée présente essentiellement la même épaisseur de paroi.
  6. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que le tube foyer (2) est immobilisé axialement sur le carter à son extrémité frontale du côté en amont.
  7. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que la tôle perforée (3) est de forme essentiellement cylindrique.
  8. Chambre de combustion de turbine à gaz selon une des revendications précédentes, caractérisée en ce que la chambre annulaire (1) sollicite la tôle perforée avec de l'air de combustion (L).
  9. Turbine à gaz, notamment turbine à gaz stationnaire, comportant au moins une chambre de combustion de turbine à gaz selon une des revendications précédentes.
  10. Turbine à gaz selon la revendication 9, caractérisée en ce que la chambre de combustion de turbine à gaz située à l'extérieur est reliée par l'intermédiaire de liaisons de vissage (7.1,7.2) avec un couvercle et/ou un carter de base.
EP10747801.8A 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz Active EP2459934B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009035550A DE102009035550A1 (de) 2009-07-31 2009-07-31 Gasturbinenbrennkammer
PCT/DE2010/050048 WO2011012126A2 (fr) 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2459934A2 EP2459934A2 (fr) 2012-06-06
EP2459934B1 true EP2459934B1 (fr) 2018-07-18

Family

ID=43087426

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10747801.8A Active EP2459934B1 (fr) 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz

Country Status (6)

Country Link
US (1) US9377197B2 (fr)
EP (1) EP2459934B1 (fr)
JP (1) JP5443604B2 (fr)
CA (1) CA2769233C (fr)
DE (1) DE102009035550A1 (fr)
WO (1) WO2011012126A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2405200A1 (fr) * 2010-07-05 2012-01-11 Siemens Aktiengesellschaft Appareil de combustion et moteur de turbine à gaz
US9625153B2 (en) * 2010-11-09 2017-04-18 Opra Technologies B.V. Low calorific fuel combustor for gas turbine
DE102011007562A1 (de) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Brennkammergehäuse und damit ausgerüstete Gasturbine
US9341374B2 (en) * 2014-06-03 2016-05-17 Siemens Energy, Inc. Fuel nozzle assembly with removable components

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3777484A (en) * 1971-12-08 1973-12-11 Gen Electric Shrouded combustion liner
JPS57154857U (fr) * 1981-03-19 1982-09-29
JPS57154857A (en) 1981-03-20 1982-09-24 Hitachi Ltd Semiconductor integrated circuit device
JPS58210413A (ja) * 1982-06-02 1983-12-07 Hitachi Ltd ガスタ−ビン燃焼器
US4567730A (en) * 1983-10-03 1986-02-04 General Electric Company Shielded combustor
JPH0752014B2 (ja) * 1986-03-20 1995-06-05 株式会社日立製作所 ガスタ−ビン燃焼器
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US5457954A (en) * 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
GB9505067D0 (en) 1995-03-14 1995-05-03 Europ Gas Turbines Ltd Combustor and operating method for gas or liquid-fuelled turbine
GB2328011A (en) 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
DE19751299C2 (de) * 1997-11-19 1999-09-09 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer
JP2002162036A (ja) 2000-11-22 2002-06-07 Mitsubishi Heavy Ind Ltd 燃焼器
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
EP1312865A1 (fr) 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Chambre de combustion annulaire de turbine à gaz
JP2003176728A (ja) 2001-12-10 2003-06-27 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器のバイバス空気取入装置
US6826913B2 (en) * 2002-10-31 2004-12-07 Honeywell International Inc. Airflow modulation technique for low emissions combustors
US7036316B2 (en) * 2003-10-17 2006-05-02 General Electric Company Methods and apparatus for cooling turbine engine combustor exit temperatures
US7334960B2 (en) * 2005-06-23 2008-02-26 Siemens Power Generation, Inc. Attachment device for removable components in hot gas paths in a turbine engine
DE102006042124B4 (de) 2006-09-07 2010-04-22 Man Turbo Ag Gasturbinenbrennkammer
US20100225902A1 (en) * 2006-09-14 2010-09-09 General Electric Company Methods and apparatus for robotically inspecting gas turbine combustion components
US7617684B2 (en) * 2007-11-13 2009-11-17 Opra Technologies B.V. Impingement cooled can combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2459934A2 (fr) 2012-06-06
JP2013501203A (ja) 2013-01-10
US9377197B2 (en) 2016-06-28
DE102009035550A1 (de) 2011-02-03
WO2011012126A3 (fr) 2011-04-14
US20120144834A1 (en) 2012-06-14
CA2769233A1 (fr) 2011-02-03
JP5443604B2 (ja) 2014-03-19
WO2011012126A2 (fr) 2011-02-03
CA2769233C (fr) 2014-04-08

Similar Documents

Publication Publication Date Title
EP2154431B1 (fr) Machine thermique
EP0244693B1 (fr) Dispositif protecteur contre le surchauffage à gaz chaud pour les propulseurs à turbine à gaz
DE69312362T2 (de) Brennkammer mit Verdünnungsleitschaufeln
DE102005025823B4 (de) Verfahren und Vorrichtung zum Kühlen einer Brennkammerauskleidung und eines Übergangsteils einer Gasturbine
EP2340397B1 (fr) Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP2808611B1 (fr) Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
DE19538746B4 (de) Segmentierter Mittelkörper für eine Doppelring-Brennkammer
DE102012100520A1 (de) Halterung zwischen dem Übergangsstück und der Prallhülse in einer Brennkammer
EP2242916B1 (fr) Turbine à gaz
DE102006026969A1 (de) Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer
CH707762A2 (de) System mit einer Vielrohr-Brennstoffdüse.
DE102008022669A1 (de) Brennstoffdüse und Verfahren für deren Herstellung
EP2307806B1 (fr) Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
EP2459934B1 (fr) Chambre de combustion de turbine à gaz
EP2812636B1 (fr) Dérivation de chambre de combustion annulaire
DE69306290T2 (de) Geteilter Mittelkörper für eine Ringbrennkammer
EP2184445A1 (fr) Support d'aubes statorique axialement segmenté d'une turbine à gaz
WO2012016748A2 (fr) Chambre de combustion de turbine à gaz
DE60225411T2 (de) Flammrohr oder Bekleidung für die Brennkammer einer Gasturbine mit niedriger Schadstoffemission
EP3143335B1 (fr) Brûleur pour un moteur à combustion et moteur à combustion
EP2409086B1 (fr) Arrangement de brûleur pour une turbine à gaz
EP3004741B1 (fr) Chambre de combustion tubulaire dotée d'une zone d'extrémité et turbine à gaz
EP1422479B1 (fr) Chambre pour la combustion d' un mélange combustible fluide
EP3926238B1 (fr) Module d'une turbine à gaz pourvu de dérivation d'air de la chambre de combustion
WO2006053825A1 (fr) Dispositif de turbine a gaz, et chambre de combustion correspondante

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: 20120109

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20160122

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20180227

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): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1019774

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010015174

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: E. BLUM AND CO. AG PATENT- UND MARKENANWAELTE , CH

Ref country code: CH

Ref legal event code: PFA

Owner name: MAN ENERGY SOLUTIONS SE, DE

Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180718

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: MAN ENERGY SOLUTIONS SE

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

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181118

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181019

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181018

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181018

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502010015174

Country of ref document: DE

Owner name: MAN ENERGY SOLUTIONS SE, DE

Free format text: FORMER OWNER: MAN DIESEL & TURBO SE, 86153 AUGSBURG, DE

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

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: LU

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

Effective date: 20180720

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180731

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010015174

Country of ref document: DE

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

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: IE

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

Effective date: 20180720

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

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

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

Ref country code: BE

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

Effective date: 20180731

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

26N No opposition filed

Effective date: 20190423

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

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1019774

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180720

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

Ref country code: AT

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

Effective date: 20180720

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

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20100720

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: MK

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

Effective date: 20180718

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180718

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

Ref country code: DE

Payment date: 20240719

Year of fee payment: 15

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

Ref country code: GB

Payment date: 20240723

Year of fee payment: 15

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

Ref country code: FR

Payment date: 20240730

Year of fee payment: 15

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

Ref country code: CH

Payment date: 20240801

Year of fee payment: 15

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

Ref country code: SE

Payment date: 20240719

Year of fee payment: 15

Ref country code: IT

Payment date: 20240725

Year of fee payment: 15

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502010015174

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: H13

Free format text: ST27 STATUS EVENT CODE: U-0-0-H10-H13 (AS PROVIDED BY THE NATIONAL OFFICE)

Effective date: 20260224

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

Effective date: 20250720

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: 20250720

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: 20260203

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: 20250731

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

Ref country code: CH

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

Effective date: 20250731