EP2511613A2 - Chambre de combustion de turbine à gaz dotée d'un joint pour un élément de montage - Google Patents

Chambre de combustion de turbine à gaz dotée d'un joint pour un élément de montage Download PDF

Info

Publication number
EP2511613A2
EP2511613A2 EP12002558A EP12002558A EP2511613A2 EP 2511613 A2 EP2511613 A2 EP 2511613A2 EP 12002558 A EP12002558 A EP 12002558A EP 12002558 A EP12002558 A EP 12002558A EP 2511613 A2 EP2511613 A2 EP 2511613A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
holder
seal
turbine combustor
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.)
Withdrawn
Application number
EP12002558A
Other languages
German (de)
English (en)
Other versions
EP2511613A3 (fr
Inventor
Miklós Dr.-Ing. Gerendás
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
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2511613A2 publication Critical patent/EP2511613A2/fr
Publication of EP2511613A3 publication Critical patent/EP2511613A3/fr
Withdrawn legal-status Critical Current

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
    • F23R3/42—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
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2900/00—Special features of, or arrangements for controlling combustion
    • F23N2900/05005—Mounting arrangements for sensing, detecting or measuring devices
    • 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
    • F23R2900/00012—Details of sealing devices
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a gas turbine combustion chamber with a combustion chamber head made of a metallic material, which supports a burner, and with a combustion chamber, which is made of a ceramic material, in particular a ceramic matrix reinforced with ceramic fibers (CMC).
  • a combustion chamber head made of a metallic material, which supports a burner
  • a combustion chamber which is made of a ceramic material, in particular a ceramic matrix reinforced with ceramic fibers (CMC).
  • CMC ceramic matrix reinforced with ceramic fibers
  • the invention relates to a mounting of a seal on a CMC combustion chamber, for example for a spark plug or an attachment.
  • the US 6,397,603 A represents a combustion chamber, wherein a single-walled combustion chamber wall consists of a ceramic fiber reinforced ceramic matrix (CMC) and this CMC combustion chamber wall is flexibly connected to a metallic combustion chamber head to compensate for the different thermal strains.
  • CMC ceramic fiber reinforced ceramic matrix
  • the CMC material of a combustion chamber is still very intrusion-tolerant even with drastically improved properties compared to monolithic ceramics.
  • the impact of a bird, other debris or a fragment of a compressor component on the CMC must therefore be prevented.
  • This task is assigned to the metallic combustion chamber head.
  • the necessary metallic combustion chamber head can also serve to support the combustion chamber in the engine, as in the US 6,397,603 A executed, or this task is taken over by brackets at the other end of the combustion chamber at the transition towards turbines. Regardless of the CMC combustion chamber walls are connected by correspondingly flexible solutions with the metallic head.
  • WO 2010/077764 A and EP 1962018 A1 are sealed connections of acoustic dampers of different modes of action to a metallic combustion chamber shown.
  • the CMC wall material can also be used in the temperature range above 1200 ° C, which would not be possible for metallic materials. Due to the high working temperature of the CMC combustion chamber wall, cooling air can be drastically saved, which can be used either to reduce the exhaust emissions or to cool other components. This cooling air saving comes off only when all leakage points of the combustion chamber are sealed. This also includes access holes for spark plugs, pressure sensors or other attachments or installations. In the following, for simplicity, only the spark plug is mentioned, since it is the most common application without neglecting the other applications. In metallic combustion chambers, the holders for the spark plug seals are usually welded to the combustion chamber wall, which also provides the flat sealing or sliding surface.
  • the resulting by the different thermal expansions of the two components relative movements between the combustion chamber wall and housing, in which the spark plug is fixed, can be divided into a radial and an axial movement relative to the engine axis.
  • the radial relative movement is made possible by the sliding of the spark plug in the spark plug seal and the relative axial movement by sliding the spark plug seal on the combustion chamber wall, wherein the opening in the combustion chamber wall according to the relative movement must be made larger.
  • the known seal also has the shape known from metallic combustion chambers with an L- or V-shaped cross-section.
  • the bore through the seal accommodates the spark plug and permits radial relative movement between the combustion chamber and the spark plug.
  • the spark plug is passed through a funnel with a second, slightly smaller outer diameter to the bore without the risk of damaging the spark plug or seal. After inserting the spark plug, the seal can only slide along the axis of the spark plug and in operation, the feed funnel has no function.
  • the invention has for its object to provide a gas turbine combustor of the type mentioned, which is provided with a simple and inexpensive to produce support structure for the spark plug seal and avoids the known from the prior art disadvantages.
  • the invention thus provides a gas turbine combustion chamber with a combustion chamber head made of a metallic material, which supports a burner, and with a combustion chamber, which is made of a ceramic material, wherein at least one spark plug is arranged in a recess of the combustion chamber, wherein in the region of the recess a seal is arranged, which is held by means of a metallic holder radially outside the spark plug.
  • the holder is web-shaped and has a recess for receiving the seal.
  • the seal is preferably provided with a supply funnel for mounting the spark plug.
  • the recess of the holder is dimensioned so that the feed hopper is feasible through this recess of the holder.
  • the holder is according to the invention preferably attached to a metallic component, for example, on the combustion chamber head or a component which supports the combustion chamber.
  • the holder can be formed in one piece with the metallic component which supports it or can be joined thereto or be connected to the component by means of a fastening element (screw or the like).
  • This proximate component may be the metallic combustion chamber head or a metallic component which serves to mount the CMC combustion chamber in the metallic housings of the engine.
  • the web-shaped metallic support may be integral with the other metallic component, that is, for example, the combustion chamber head, or be joined, for example, by soldering, or be attached to the other component with at least one fastener such as a screw or a rivet.
  • the web-shaped holder can also be attached to the outer combustion chamber housing or to the spark plug adapter, which is mounted in the outer combustion chamber housing.
  • the web-shaped support is not designed purely radial.
  • it is designed for the connection to the spark plug adapter in the form of a spiral or a wave or trapezoidal carrier.
  • the bore in the web-shaped metallic support is large enough to pass the (slightly smaller in diameter) feed hopper of the seal, but not the (slightly larger in diameter) standing perpendicular to the bore axis sealing collar.
  • the web-shaped metallic holder is located at a distance from the combustion chamber wall. It may have a simple rectangular cross-section, in particular advantageous for a connection to the spark plug adapter, or to increase the rigidity against vibrations, a cross-section with a higher moment of inertia, for example a V-shaped cross section, in particular advantageous in a connection to the combustion chamber head.
  • the flat surface necessary as a sealing surface is provided by a local thickening of the CMC combustion chamber wall, which is created during the production of the combustion chamber wall of the same material as the combustion chamber itself, the additional CMC material on the combustion chamber inside while maintaining a circular inner contour of the combustion chamber , is added within the combustion comb wall by one or more inserts or on the outside of the combustion chamber through an attachment of CMC material.
  • the web-shaped metallic support serves to position the seal during assembly.
  • the seal In operation, the seal is pressed by the prevailing pressure difference between the combustion chamber outside and inside the sealing surface, so a pressing mechanism as a spring in operation is not necessary.
  • the seal In order to develop this sealing effect when starting the engine, the seal must be at least in the vicinity of the opening in the combustion chamber wall. Therefore, it is sufficient if the web-shaped metallic holder for the spark plug seal, the seal with a few millimeters of play positioned on the spark plug opening in the combustion chamber wall.
  • the web-shaped metallic support must not be in contact with the ceramic combustion chamber wall because the thermal expansion coefficients of metal and CMC differ drastically. If the web-shaped metallic holder would rest on the CMC combustion chamber in the cold state or have too little clearance, there would be a risk that the forces resulting from thermal distortion damage the holder or the combustion chamber. In addition, the CMC combustion chamber is in operation at very high temperatures, which could damage the web-shaped metallic support. In addition, the cooling air for the combustion chamber wall must have free access to the cooling air openings located in the CMC combustion chamber wall even below the web-shaped metallic support in order to fulfill its task.
  • the invention is applicable both to annular combustion chambers and also to tube combustion chambers with CMC combustion chamber walls.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • Fig. 2 to 4 show in axial section view respectively simplified representations of embodiments according to the invention.
  • Fig. 5a shows a 3D view of the device according to the invention and the Fig. 5b a 3D cut through the device.
  • a combustion chamber 107 comprises a CMC combustion chamber wall. Downstream of the combustion chamber 107, a burner 104 is arranged with an arm and a head which is supported by means of a metallic combustion chamber head 105. The supply of the flow via compressor outlet blades 101. The entire assembly is a combustion chamber outer casing 102 and a combustion chamber inner housing 105 is arranged.
  • the reference numeral 106 shows a combustion chamber holder, for example by means of three circumferentially distributed pins. Downstream of the combustor 107, turbine inlet blades 108 are disposed.
  • the figures each show a spark plug 109, which is sealed by means of a spark plug seal (seal) 110.
  • the spark plug is using a Spark plug adapter 112 is mounted, which is fixed to the combustion chamber outer housing 102.
  • a metallic web-shaped holder 111 is provided, which holds the spark plug seal.
  • the Fig. 2 shows an embodiment in which the metallic web-shaped holder 110 is attached to the metallic combustion chamber head 105.
  • the metallic web-shaped holder 111 is held on the outer combustion chamber housing 102 and a spark plug adapter 112, respectively.
  • the metallic web-shaped support 111 according to the in Fig. 3 embodiment shown is designed so that a radial relative movement is possible.
  • the shows Fig. 3 a feed hopper 113, which serves to insert the spark plug 109.
  • the metallic web-shaped holder is angled and mounted on the spark plug adapter 112 and the combustion chamber outer housing 102.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP12002558.0A 2011-04-13 2012-04-11 Chambre de combustion de turbine à gaz dotée d'un joint pour un élément de montage Withdrawn EP2511613A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011016917A DE102011016917A1 (de) 2011-04-13 2011-04-13 Gasturbinenbrennkammer mit einer Halterung einer Dichtung für ein Anbauteil

Publications (2)

Publication Number Publication Date
EP2511613A2 true EP2511613A2 (fr) 2012-10-17
EP2511613A3 EP2511613A3 (fr) 2015-01-21

Family

ID=45977130

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12002558.0A Withdrawn EP2511613A3 (fr) 2011-04-13 2012-04-11 Chambre de combustion de turbine à gaz dotée d'un joint pour un élément de montage

Country Status (3)

Country Link
US (1) US8677765B2 (fr)
EP (1) EP2511613A3 (fr)
DE (1) DE102011016917A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2511563A (en) * 2013-03-08 2014-09-10 Rolls Royce Plc A combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly
EP2938865A4 (fr) * 2012-12-29 2016-01-13 United Technologies Corp Retenue de composants par une sonde

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014214775A1 (de) 2014-07-28 2016-01-28 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit einer Dichtung zur Abdichtung einer Zündkerze an der Brennkammerwand einer Gasturbine
US20170176004A1 (en) * 2015-12-18 2017-06-22 Pratt & Whitney Canada Corp. Combustor floating collar assembly
US11125436B2 (en) * 2019-07-03 2021-09-21 Pratt & Whitney Canada Corp. Combustor floating collar mounting arrangement
FR3109430B1 (fr) * 2020-04-17 2022-12-02 Safran Aircraft Engines Bougie pour chambre de combustion monobloc

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6397603B1 (en) * 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner
JP2006010193A (ja) * 2004-06-25 2006-01-12 Japan Aerospace Exploration Agency ガスタービン燃焼器
GB2432198A (en) * 2005-11-15 2007-05-16 Rolls Royce Plc A sealing arrangement

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3910036A (en) * 1974-04-05 1975-10-07 Gen Motors Corp Igniter installation for combustor with ceramic liner
US3922851A (en) * 1974-04-05 1975-12-02 Gen Motors Corp Combustor liner support
US3911672A (en) * 1974-04-05 1975-10-14 Gen Motors Corp Combustor with ceramic liner
US4237389A (en) 1978-09-01 1980-12-02 Trw Inc. Charge coupled device channel crossover circuit
JP2726922B2 (ja) * 1994-09-21 1998-03-11 川崎重工業株式会社 ガスタービン用燃焼器
US6438940B1 (en) * 1999-12-21 2002-08-27 General Electric Company Methods and apparatus for providing uniform ignition in an augmenter
JP3478531B2 (ja) * 2000-04-21 2003-12-15 川崎重工業株式会社 ガスタービンのセラミック部品支持構造
GB2396687A (en) 2002-12-23 2004-06-30 Rolls Royce Plc Helmholtz resonator for combustion chamber use
US6993960B2 (en) * 2002-12-26 2006-02-07 Woodward Governor Company Method and apparatus for detecting combustion instability in continuous combustion systems
US6920762B2 (en) * 2003-01-14 2005-07-26 General Electric Company Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner
FR2856466B1 (fr) * 2003-06-20 2005-08-26 Snecma Moteurs Dispositif d'etancheite de bougie non soude sur la paroi de chambre
US7237389B2 (en) * 2004-11-18 2007-07-03 Siemens Power Generation, Inc. Attachment system for ceramic combustor liner
US7762076B2 (en) * 2005-10-20 2010-07-27 United Technologies Corporation Attachment of a ceramic combustor can
US8567197B2 (en) 2008-12-31 2013-10-29 General Electric Company Acoustic damper
US8522560B2 (en) * 2009-03-25 2013-09-03 United Technologies Corporation Fuel-cooled heat exchanger with thermoelectric device compression

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6397603B1 (en) * 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner
JP2006010193A (ja) * 2004-06-25 2006-01-12 Japan Aerospace Exploration Agency ガスタービン燃焼器
GB2432198A (en) * 2005-11-15 2007-05-16 Rolls Royce Plc A sealing arrangement

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2938865A4 (fr) * 2012-12-29 2016-01-13 United Technologies Corp Retenue de composants par une sonde
US9863261B2 (en) 2012-12-29 2018-01-09 United Technologies Corporation Component retention with probe
GB2511563A (en) * 2013-03-08 2014-09-10 Rolls Royce Plc A combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly
GB2511563B (en) * 2013-03-08 2015-06-24 Rolls Royce Plc A combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly
US9562474B2 (en) 2013-03-08 2017-02-07 Rolls-Royce Plc Combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly

Also Published As

Publication number Publication date
EP2511613A3 (fr) 2015-01-21
US8677765B2 (en) 2014-03-25
US20130055716A1 (en) 2013-03-07
DE102011016917A1 (de) 2012-10-18

Similar Documents

Publication Publication Date Title
DE102011052677B4 (de) Elastische Halterungsvorrichtung für ein Turbinengehäuse geringer Duktilität
EP2918913B1 (fr) Chambre de combustion d'une turbine à gaz
EP2511613A2 (fr) Chambre de combustion de turbine à gaz dotée d'un joint pour un élément de montage
EP2873921B1 (fr) Élément de protection contre la chaleur d'une chambre de combustion d'une turbine à gaz
EP1745245B1 (fr) Chambre de combustion pour une turbine a gaz
EP2503246A2 (fr) Tête de chambre de combustion segmentée
EP2503242B1 (fr) Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz
EP1334262A1 (fr) Turbocompresseur pour moteur a combustion interne, a geometrie de turbine variable
DE102014219552A1 (de) Leitschaufelverstellvorrichtung einer Gasturbine
EP2093487B1 (fr) Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur
EP2918914A1 (fr) Chambre de combustion d'une turbine à gaz
DE10311038A1 (de) Rotoreinsatzbaugruppe und Retrofit-Verfahren
EP2054587B1 (fr) Boîtier de turbine
EP1744016A1 (fr) Elément de carénage pour gaz chauds, chemise de protection de l'arbre et turbine à gaz
EP2966352A1 (fr) Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee
EP2194230A1 (fr) Agencement d'aube directrice pour une turbomachine axiale
WO2015022222A1 (fr) Écran thermique comportant un résonateur de helmholtz
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
EP3176386B1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP1731715A1 (fr) Transition d'une chambre de combustion à une turbine
EP2955336B1 (fr) Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire
EP3610135A1 (fr) Couronne directrice pour un turbocompresseur à gaz d'échappement
EP2730744B1 (fr) Turbosoufflante de gaz d'échappement
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP2611992B1 (fr) Structure de carter 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: 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 RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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 RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/60 20060101AFI20141212BHEP

Ipc: F23R 3/00 20060101ALI20141212BHEP

17P Request for examination filed

Effective date: 20150325

RBV Designated contracting states (corrected)

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 RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20180411