EP1994260B1 - Brennkammer für eine gasturbine umfassend eine verstellvorrichtung - Google Patents

Brennkammer für eine gasturbine umfassend eine verstellvorrichtung Download PDF

Info

Publication number
EP1994260B1
EP1994260B1 EP07700252.5A EP07700252A EP1994260B1 EP 1994260 B1 EP1994260 B1 EP 1994260B1 EP 07700252 A EP07700252 A EP 07700252A EP 1994260 B1 EP1994260 B1 EP 1994260B1
Authority
EP
European Patent Office
Prior art keywords
mixing housing
housing
bolt
mixing
gas turbine
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
EP07700252.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1994260A2 (de
Inventor
Peter Dietrich
Milan Schmahl
Martin Stapper
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP07700252.5A priority Critical patent/EP1994260B1/de
Publication of EP1994260A2 publication Critical patent/EP1994260A2/de
Application granted granted Critical
Publication of EP1994260B1 publication Critical patent/EP1994260B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom

Definitions

  • the invention relates to a combustion chamber for a gas turbine with a mixing housing and a gas turbine with such a combustion chamber.
  • the mixing housing When mounting a mixing housing of a gas turbine, the mixing housing is first mounted in the combustion chamber to the flame tube.
  • the mixing housing must be precisely aligned so that the lower mixing housing connection fits into the connection of the inner housing of the fuselage turbine.
  • the mass, shapes and positions of the mixing housing and the inner casing of the fuselage turbine of a gas turbine have such large variances due to production that the mixing housing can not readily be positioned to the inner casing of the fuselage turbine.
  • the position of the inner housing is transferred to a template.
  • the mixing housing can be made with the cooling air ring and aligned at the inner housing position in the area of the pressure jacket flange.
  • Fig. 2 a template for positioning a mixing housing according to the prior art is shown.
  • the template 11 is fastened by six screws 21 on the pressure jacket flange 10 surrounding the mixing housing.
  • the cooling air ring 6 is aligned with the template 11.
  • Fig. 3 represents a detailed view of two alignment points between the template 11 and the cooling air ring 6.
  • the grooves 23 of the template 11 receive the pins 22 of the cooling air ring 6 and thus define the position of the cooling air ring 6.
  • the cooling air ring can be welded to the mixing housing.
  • a combustion chamber with a Mischgegäuse known, which in turn has a centering device.
  • the invention has for its object to provide an advantageous mixing housing arrangement and a gas turbine with an advantageous mixing housing arrangement available.
  • a combustion chamber according to the invention has a mixing housing with an outer housing surrounding the mixing housing, wherein the mixing housing is adjustable relative to the outer housing.
  • the mixing housing is provided with an adjusting device for adjusting the mixing housing relative to the outer housing.
  • the combustion chamber has an adjusting device which comprises a bolt, a pressure plate and a wedge disk.
  • the contact surfaces between the pin and the wedge disk and between the pin and the pressure plate can be made spherical be such that the flange portion of the bolt between the counterparts can be moved on a spherical surface.
  • the mixing housing moves with it, but maintains its concentric position to the flame tube.
  • the cooling air ring is welded to the mixing housing and then aligned with the inner housing position.
  • the spherical surface between the pin and the pressure plate enables quick and cost-effective retrofitting of existing machines. Due to the optimized dimensions of the bolt, even in the worst case, no critical shifts of the mixing housing during operation occur.
  • the adjustment is thus based on the variable position of the bearing bolts. This eliminates the individual transmission of the inner housing position of a gas turbine by means of a template, and it can be used, the statistical means of the inner housing position.
  • the bolts can be eccentrically installed, so that a height adjustment of the mixing housing is possible.
  • the bolts on the head can each have an eccentric bore with an eccentric pin inserted therein.
  • the bolts can also be slidably mounted in parallel vertically and horizontally to the outer housing. As a result, a gap adaptation of the mixing housing to the flame tube is possible.
  • the mixing housing can be tilted about the pin axis, whereby a further flexibility of the mixing housing is achieved.
  • the bolt can be located in a flange tube, which is arranged in the outer housing.
  • the flange tube can in particular be widened to a slot. This allows a horizontal adjustment of the mixing housing. The vertical adjustment is then also possible by tilting the mixing housing about the pin axis and the use of the eccentric.
  • the adjusting device can also be designed as a guide and rail system with the aid of which the mixing housing can be positioned more accurately. In this case, an arrangement of adjustable bolts is not required.
  • a gas turbine according to the invention comprises a combustion chamber according to the invention.
  • the combustion chamber may comprise a cooling air ring fixed to the mixing housing and facing the inner housing.
  • the gap between the inner housing and the cooling air ring is then advantageously 3 to 3.5 mm.
  • Fig. 1 shows first a combustion chamber 1 of a gas turbine with an outer housing, which is called pressure jacket 18, sometimes called combustion chamber jacket, executed, and with a disposed within the outer housing or pressure jacket 18 flame tube 2. Within the pressure jacket 18 are also a mixing housing 4 and a at the mixing housing 4 fixed cooling air ring. 6
  • the flame tube 2 extends vertically and is located in the upper region of the arrangement shown. It absorbs the flames generated by the burner 3 located at the upper end of the pressure jacket.
  • the conical and curved mixing housing 4 connects, which leads the combustion gases to an inner casing 8 of a fuselage turbine (not shown).
  • the cooling air ring 6 adjoins the mixing housing 4, which cools the transition between the mixing housing 4 and the inner housing 8.
  • the mixing housing 4 is fastened by two bolts 12 on the pressure jacket 18.
  • the bolts 12 are located in flange tubes 20 with Flanschrohrlteilsachsen 19, which are arranged in the pressure jacket 18, namely in the vicinity of a support 11 in the region of the lower part of the mixing housing 4. This go the Flanschrohrlteilsachsen 19 (see Fig. 5 ) through the intersection of a flame tube longitudinal axis 7 and an inner housing longitudinal axis 9 (s. Fig. 1 ).
  • the flange tubes can be arranged with their longitudinal axes 19 perpendicular to the plane defined by the flame tube longitudinal axis 7 and the inner housing longitudinal axis 9 surface. Within a horizontal elongated hole, the bolts and thus the mixing housing can then be moved well in the direction of the extended inner housing longitudinal axis 9.
  • the flanged pipes can but equally well positioned at any other location on the outer surface of the pressure jacket 18, but then not the optimal displaceability along the inner housing longitudinal axis 9 is achieved.
  • Fig. 4 shows an enlarged detail view X of the area within the pressure jacket flange 10 in FIG Fig. 1 , Within the Druckmantelflansches 10 of the pressure jacket 18 are the connection points between the mixing housing 4 and the cooling air ring 6 and between the cooling air ring 6 and inner housing 8.
  • the cooling air ring 6 is welded at one end to the mixing housing 4. The other end of the cooling air ring 6 is inserted into the connection cross section of the inner housing 8.
  • Fig. 5 is the adjustable arrangement between mixing housing 4, pressure jacket 18, and one of the two bolts 12 (see Fig. 1 ).
  • the bolt 12 is received at the unscrewed end in a mixing housing sleeve 5, while the flange 17 is located within the flange tube 20 of the pressure jacket 18.
  • the mixing housing sleeve 5 is located on the outside of the mixing housing 4.
  • the bolt 12 can be fixed to the flange 17 by a plurality of circumferentially distributed screws 16 on the pressure jacket 18.
  • the wedge plate 14 which is annular and surrounds the pin 12.
  • the wedge disk 14 has a spherical surface 15 on the surface adjoining the bolt.
  • the bolt also has a spherical surface 15 on the flange surface, which rests on the wedge disk in the installed state.
  • the concave sides of the two resting on each other spherical surfaces 15 show for Mixing housing 4. This results in the dissolved state of the bolt 12 a rotatable along the spherical surfaces bearing of the bolt 12 between Andschreibblech 13 and wedge disk 14th
  • the two spherical surfaces 15 between Andschreibblech 13, bolts 12 and wedge disk 14 allow the mixing housing 4 via the bolt 12 in its position relative to the inner housing 8 (see Fig. 4 ) of the hull turbine is adjustable.
  • the mixing housing 4 can be rotated by the bolts 12 with the bolt longitudinal axis 24 by the angle a relative to the Flanschrohrlteilsachse 19.
  • the mixing housing is rotated by ⁇ 0.15 °. After adjusting the mixing housing tighten the screws of the bearing bolts. The bolts and thus the mixing housing are then held in position by frictional force.
  • a bore 26 for screwing a mounting rod In the flange 17 of the bolt 12 is also a bore 26 for screwing a mounting rod.
  • Fig. 6 illustrates a single view of the bolt 12.
  • the bolt 12 has on both sides of its flange spherical surfaces 15 (s. Fig. 5 ).
  • the borehole can also be expanded to a slot.
  • the diameter A of the bolt flange holes (about 25 mm) is larger as the diameter B of the flange holes of the wedge plate 14 (s. Fig. 7 ) and the pressure plate 13 (s. Fig. 8 ), so that the fastening screws 16 of the bolt 12 have sufficient clearance during the movement of the bolt for adjusting the bolt position.
  • Fig. 7 shows a single view of a wedge plate 14 as already in the assembly in Fig. 5 shown.
  • the wedge disk 14 has a spherical surface 15 only on the side which rests on the flange of the bolt 12 during assembly to allow adjustment of the bolt 12.
  • Fig. 8 shows a single view of a Andschreibblechs 13, which is already in the assembly in Fig. 5 is shown.
  • the pressure plate 13 also has only on the side which rests on the flange of the bolt 12 in the assembly, a spherical surface 15 in order to allow adjustment of the bolt 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
EP07700252.5A 2006-03-15 2007-01-09 Brennkammer für eine gasturbine umfassend eine verstellvorrichtung Active EP1994260B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07700252.5A EP1994260B1 (de) 2006-03-15 2007-01-09 Brennkammer für eine gasturbine umfassend eine verstellvorrichtung

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06005259 2006-03-15
EP07700252.5A EP1994260B1 (de) 2006-03-15 2007-01-09 Brennkammer für eine gasturbine umfassend eine verstellvorrichtung
PCT/EP2007/050194 WO2007104587A2 (de) 2006-03-15 2007-01-09 Verfahren zur montage eines mischgehäuses in einer gasturbine sowie verstellvorrichtung hierfür

Publications (2)

Publication Number Publication Date
EP1994260A2 EP1994260A2 (de) 2008-11-26
EP1994260B1 true EP1994260B1 (de) 2017-09-20

Family

ID=38008336

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07700252.5A Active EP1994260B1 (de) 2006-03-15 2007-01-09 Brennkammer für eine gasturbine umfassend eine verstellvorrichtung

Country Status (4)

Country Link
EP (1) EP1994260B1 (ru)
CN (1) CN101548135B (ru)
RU (1) RU2444681C2 (ru)
WO (1) WO2007104587A2 (ru)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2993315B8 (en) * 2014-09-05 2017-07-19 Ansaldo Energia Switzerland AG Apparatus for an assembly tool for mounting or dismantling, replacement and maintenance of a component of an engine
FR3038699B1 (fr) * 2015-07-08 2022-06-24 Snecma Chambre de combustion coudee d'une turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB701099A (en) * 1950-05-22 1953-12-16 Lucas Ltd Joseph Improvements to combustion chambers
US3759038A (en) * 1971-12-09 1973-09-18 Westinghouse Electric Corp Self aligning combustor and transition structure for a gas turbine
DE2523449C3 (de) * 1975-05-27 1981-03-26 Kraftwerk Union AG, 45473 Mülheim Brennkammer für Gasturbinen
IT1216611B (it) * 1988-04-21 1990-03-08 Nuovo Pignone Spa Dispositivo per mantenere la bocca anulare di uscita del convogliatore dei gas sempre centrata rispetto al gruppo ugelli di una turbina agas.
FR2671857B1 (fr) * 1991-01-23 1994-12-09 Snecma Chambre de combustion, notamment pour turbine a gaz, a paroi deformable.
DE4223733C2 (de) * 1992-07-18 1995-05-18 Gutehoffnungshuette Man Verbindung von Mischrohr und Flammrohr einer Gasturbine
RU2100705C1 (ru) * 1993-02-03 1997-12-27 Акционерное общество открытого типа "Самарский научно-технический комплекс "Двигатели НК" Устройство для крепления жаровой трубы в корпусе камеры сгорания
RU2112181C1 (ru) * 1994-06-10 1998-05-27 Ставропольское высшее авиационное инженерное училище противовоздушной обороны им.Маршала авиации Судца В.А. Камера сгорания газотурбинного двигателя
US6442946B1 (en) * 2000-11-14 2002-09-03 Power Systems Mfg., Llc Three degrees of freedom aft mounting system for gas turbine transition duct
DE10348447B4 (de) * 2003-10-17 2014-04-03 Siemens Aktiengesellschaft Montage- und Wartungshilfsmittel für eine Gasturbine

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
CN101548135B (zh) 2011-06-08
WO2007104587A2 (de) 2007-09-20
EP1994260A2 (de) 2008-11-26
WO2007104587A3 (de) 2009-01-22
CN101548135A (zh) 2009-09-30
RU2444681C2 (ru) 2012-03-10
RU2008140723A (ru) 2010-04-20

Similar Documents

Publication Publication Date Title
EP2720907B1 (de) Befestigungselement mit toleranzausgleichsfunktion
EP1912764B1 (de) Andruckvorrichtung für ein spannsystem
EP3583061B1 (de) Halteeinrichtung
DE10302876A1 (de) Baueinheit mit einer Hülse für Kettensteuertriebe
EP1996439B1 (de) Gelenkkupplung für schienenfahrzeuge
EP1994260B1 (de) Brennkammer für eine gasturbine umfassend eine verstellvorrichtung
EP2636911A1 (de) Befestigungsanordnung
EP3524778B1 (de) Hebelanbindung einer leitschaufelverstellung für strömungsmaschinen und zugehöriges herstellungsverfahren
WO2020083434A1 (de) Lagervorrichtung für einen abgasturbolader und abgasturbolader
DE102013011106B4 (de) Abgasturbolader
WO2016034377A1 (de) Scheibenbremse eines kraftfahrzeugs, bremssattel, bremsbelag und anordnung wenigstens eines bremsbelags in einer belagschachtöffnung eines bremssattels
DE19631844C2 (de) Vorrichtung zum Einsetzen eines geschlitzten elastischen Sicherungsringes in eine Ringnut eines Werkstückes
DE102019132222A1 (de) Verbindungselement zur Verbindung eines Schalungsunterstützungskopfes mit einer Rohrstütze
EP2062689A1 (de) Rohrverbindungsvorrichtung
DE102009009365A1 (de) Verliersicherung zum Sichern eines Verbindungselementes
DE10115048A1 (de) Verbindungsstück zum Verbinden einer Brennstoffleitung mit einem Brennstoffeinspritzventil
DE102006050132B3 (de) Statisch überbestimmte Lagerung eines Antriebsaggregats eines Kraftfahrzeugs
EP3599388B1 (de) Ladeeinrichtung
CH712345B1 (de) Vorrichtung mit einer Halteeinrichtung für die Positionierung einer Schraubenmutter einer Schraubenverbindung bei Überkopfmontage.
DE1628441C3 (de) Vorrichtung zum Gießen eines zylindrischen Hohlkörpers, nämlich Mischrohr für eine Strahlpumpe
WO2008138678A1 (de) Hydraulik- und/oder pneumatikvorrichtung sowie hydraulik- und/oder pneumatiksystem
DE10257610B3 (de) Motorspindel mit Festhaltevorrichtung
EP1754619A2 (de) Vorrichtung zum Befestigen eines Aggregatelagers
EP1882878B1 (de) Universell einstellbare Halterungsvorrichtung
DE19948956A1 (de) Montagevorrichtung

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: 20080808

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

R17D Deferred search report published (corrected)

Effective date: 20090122

17Q First examination report despatched

Effective date: 20090406

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): DE IT

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170118

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20170407

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170628

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE IT

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502007015883

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502007015883

Country of ref document: DE

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: 20180621

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502007015883

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

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

Ref country code: IT

Payment date: 20230126

Year of fee payment: 17

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

Ref country code: DE

Payment date: 20240129

Year of fee payment: 18