EP2024684B1 - Turbine à gaz avec composants de machine blindé - Google Patents

Turbine à gaz avec composants de machine blindé Download PDF

Info

Publication number
EP2024684B1
EP2024684B1 EP07728485A EP07728485A EP2024684B1 EP 2024684 B1 EP2024684 B1 EP 2024684B1 EP 07728485 A EP07728485 A EP 07728485A EP 07728485 A EP07728485 A EP 07728485A EP 2024684 B1 EP2024684 B1 EP 2024684B1
Authority
EP
European Patent Office
Prior art keywords
armor
gas turbine
components
machine
segments
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
EP07728485A
Other languages
German (de)
English (en)
Other versions
EP2024684A1 (fr
Inventor
Birgit Grüger
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 EP07728485A priority Critical patent/EP2024684B1/fr
Publication of EP2024684A1 publication Critical patent/EP2024684A1/fr
Application granted granted Critical
Publication of EP2024684B1 publication Critical patent/EP2024684B1/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
    • F23R3/005—Combined with pressure or heat exchangers
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05001—Preventing corrosion by using special lining materials or other techniques

Definitions

  • the invention relates to a gas turbine with a number of machine components provided with a basic body made of a base material, which is provided in a portion of its surface with an armor made of a coating material with a greater hardness compared to the base material.
  • Turbines in particular gas turbines, are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or blade rows, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • a turbine of this type comprises a plurality of components or machine components which are positioned in the turbine in accordance with predetermined dimensions, shapes and / or tolerances. In many cases, it may be desirable to contact the neighboring machine components or components minimize each other, so as to keep wear of the affected components particularly low. Nevertheless, during operation of the turbine, for example as a result of thermal expansion or as a result of operating vibrations or the like, there may always be undesirable contact between such components, so that some wear of such components occurs. For example, as such machine components in the region of the combustion chamber of the gas turbine usually a so-called flame tube, a mixing housing and an inner housing adjacent to each other.
  • the machine components can be manufactured in what is referred to as an armored version, the areas particularly affected by the expected wear or expected contacts with neighboring components being coated with a protective coating, also referred to as armor ,
  • a protective coating also referred to as armor
  • Such an armor can be formed from an application material which has a greater mechanical hardness compared to the base material of the respective component, so that a contact-related wear can already be reduced by such a suitable choice of material.
  • a segmented armor applied to a squeal ring of a gas turbine for example, in the document GB 2061 397 A a segmented armor applied to a squeal ring of a gas turbine.
  • the invention is therefore based on the object to provide a gas turbine with a number of machine components of the type mentioned above, which is also particularly suitable for use in a thermally comparatively highly loaded area of a working machine.
  • the invention is based on the consideration that the machine component should be provided with a suitable armor for a fundamental usability while maintaining wear-resistant working conditions.
  • the lateral extent of the armor should be kept particularly low.
  • individual zones of the armor should be executed decoupled from one another, in order thus to allow sufficient resilience to thermal deformation and the like. For this, the armor should be executed segment by segment.
  • each other positioned components or machine components should be armored in this way be executed, wherein the armored portion of the surface of a first machine component adjacent to the armored portion of the surface of a second machine component is arranged.
  • the application material of the first machine component has a different hardness than the application material of the second machine component.
  • the armor segments may be applied by suitable techniques on the body of the machine component.
  • the armor segments are applied by build-up welding on the base body, so that a particularly intimate connection to the body and thus a high stability of the machine component is achieved overall.
  • the armor segments may be applied to an outer surface of the body so that the resulting contour has substantially a plurality of bulges provided by the armor segments on the surface of the rail component.
  • the armor segments are advantageously introduced or embedded respectively in associated recesses in the body.
  • an overall surface of the machine component that is virtually flat overall is advantageously achievable overall, with the outer surface of the armor segments in particular and the outer surface of the webs of the base body extending between the armor segments forming a continuous surface.
  • machine components of the type mentioned are used in a gas turbine, in particular as a flame tube of a combustion chamber, as a mixing housing of a burner and / or as an inner housing of a combustion chamber.
  • the advantages achieved by the invention are in particular that by the segmented design of the armor of the machine component even with only small tolerance ranges attaching the armor on the body is made possible in the first place, especially with regard to the segmented execution of the armor distortion of the body can be largely avoided due to the high operating temperatures during build-up welding.
  • the segmented design of the armor also avoids cracking when applying the armor, which could occur with continuous welding of the armor.
  • a subsequent bending of the component is made possible without the order material would be too stressed.
  • deformations and joint welds are comparatively easy to carry out during assembly and in operation, without any critical effects on the component to be feared.
  • the surface of the machine component can be homogenized in retrospect, with a possible supernatant after the deposition welding can also be subsequently removed. In this case, compliance with externally predetermined dimensions can be ensured in particular with adapted component geometry.
  • the segmented application of the armor also reduces the load on the component during manufacture, assembly and operation.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed vanes 14, which are also annular in shape to form Guide vanes are attached to an inner housing 16 of the turbine 6.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from a turbine 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component that forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine 6.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
  • each guide ring 21 on the inner housing 16 of the turbine 6 is arranged.
  • the inner surface of each guide ring 21 is also exposed to the hot, the turbine 6 flowing through the working medium M and spaced in the radial direction from the outer end 22 of the opposed blades 12 a blade row through a gap 24.
  • each of the combustion chamber 4 is in its inflow, to which a number of unspecified supply lines for media, such as fuel and combustion air are connected, equipped in its interior with a so-called flame tube 30, within which the combustion of the fuel takes place.
  • a so-called flame tube 30 is connected on the output side to a mixing housing 34 of the combustion chamber. 4
  • the flame tube 30, the transition piece 34 and the inner housing 36 are connected to each other in the manner of nested tubes together, so that a reliable media flow guidance of the flame tube 30 is ensured in the inner housing 36 of the combustion chamber 4.
  • the respectively nested tube ends are positioned as possible contact-free from each other while maintaining the predetermined dimensions and tolerances, so that wear due to in contact with each other components and rubbing components is avoided as possible.
  • a recurrent contact of these components with each other can not be avoided, so that residual wear is to be expected in every case.
  • regular inspection and replacement of these components is required as part of maintenance and inspection work.
  • each of the engine components flame tube 30, transition piece 34 and inner housing 36 is constructed from a base made of base material 40, which in each case in the FIG. 3 to 6 shown portion of its surface with an armor 42 is provided from a job material.
  • the application material is chosen such that it has a greater hardness compared to the base material, so that an increased resistance to mechanical and thermal stress is given.
  • the application material is applied to the base body 40 in each case by build-up welding.
  • the armor 42 comprises a plurality of armor segments 44, wherein the dimensioning with regard to the dimensioning of the actual machine component and the materials used is chosen such that the laterally limited extent the respective armor segments 44 too great impairment of the base body 40 by different thermal Expansion behavior and the like is avoided.
  • the armor segments 44 are each introduced into associated recesses in the base body 40.
  • the recesses may have been introduced by suitable machining methods, such as by milling, turning or grinding.
  • the dimensioning can in principle be made such that the armor segments 44 are applied to a flat surface of the base body 40 and correspondingly their thickness corresponding recesses arise between them.
  • the preparation can also, as in the FIG. 3 6, such that the outer surface of the armor segments 44 engage with the outer surface of the webs 46 of the armor 44 extending between the outer armor segments 44
  • Base body 40 form a continuous and thus planar surface.
  • a finished machine component thereby creates a component which largely corresponds to an originally provided component in terms of its shape, dimensioning and dimensional stability and in particular has a correspondingly smooth and planar surface.
  • a bent cooling air ring 50 can be embodied as an at least partially armored machine component of the type mentioned.
  • the cooling air ring 50 is also provided on its surface with armor segments 44, which are incorporated into corresponding recesses of the cooling air ring 50 forming base body 40.
  • cooling air channels 52 are additionally provided, which are formed by corresponding holes. Due to the shape of the wells, also referred to as pockets, in which the armor segments 44 are arranged, the desired geometry of the cooling air ring 50 can be maintained. Nevertheless, an almost even surface and a smooth transition to the base body 40 is created even when using the armor segments 44. This ensures increased wear reduction and improved bonding between the materials used.
  • FIG. 5 It is shown that as such armored machine components in particular the transition piece 34 and the flame tube 30 of the gas turbine 1 are designed in their overlapping region. Armor 42 of these machine components are provided in each case on the facing surface segments. In such an adjacent arrangement of two such machine armored components is also, as provided for the transition piece 34 and the flame tube 30, by a suitable choice of material for the armor 42 targeted focusing the wear on one of the two machine components, in particular on the easier exchangeable Machine component, enabled. For this purpose, in the present case specifically provided, the application material for the armor 42 of the flame tube 30 of lower hardness than the material for the armor 42 of the transition piece 34th

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Claims (5)

  1. Turbine ( 1 ) à gaz ayant un certain nombre de composants de machine, comprenant un corps ( 40 ) de base en un matériau de base, qui est muni dans une sous-partie de sa surface d'un blindage ( 42 ) en un matériau de dépôt ayant une dureté plus grande que celle du matériau de base, le blindage ( 42 ) étant segmenté et étant formé d'un certain nombre de segments ( 44 ) de blindage, la sous-partie blindée de la surface d'un premier composant de machine étant disposée au voisinage de la sous-partie blindée de la surface d'un deuxième composant de machine, le matériau de dépôt du premier composant de machine ayant une dureté autre que celle du matériau de dépôt du deuxième composant de machine.
  2. Turbine ( 1 ) à gaz suivant la revendication 1, dans laquelle, pour au moins l'un d'entre eux, les segments ( 44 ) de blindage sont déposés par soudage avec apport sur le corps ( 40 ) de base.
  3. Turbine ( 1 ) à gaz suivant la revendication 1 ou 2, dans laquelle, pour au moins l'un d'entre eux, les segments ( 44 ) de blindage sont incorporés respectivement dans des cavités associées du corps ( 40 ) de base.
  4. Turbine ( 1 ) à gaz suivant la revendication 3, dans laquelle, pour au moins l'une d'entre elles, les surfaces extérieures des segments ( 44 ) de blindage et les surfaces extérieures des parties pleines du corps ( 40 ) de base s'étendant entre les segments ( 44 ) de blindage forment une surface continue.
  5. Turbine à gaz suivant l'une des revendications précédentes, dans laquelle un tube ( 30 ) de flamme d'une chambre de combustion ( 4 ), un carter ( 34 ) de mélange d'une chambre de combustion ( 4 ) et/ou un carter extérieur d'une chambre de combustion sont conformés en composants de machine.
EP07728485A 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé Active EP2024684B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07728485A EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06011629A EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz
PCT/EP2007/054029 WO2007141091A1 (fr) 2006-06-06 2007-04-25 Composant de machine blindé et turbine à gaz
EP07728485A EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé

Publications (2)

Publication Number Publication Date
EP2024684A1 EP2024684A1 (fr) 2009-02-18
EP2024684B1 true EP2024684B1 (fr) 2009-12-09

Family

ID=37560775

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06011629A Withdrawn EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz
EP07728485A Active EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06011629A Withdrawn EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz

Country Status (7)

Country Link
US (1) US8091366B2 (fr)
EP (2) EP1865258A1 (fr)
CN (1) CN101473171B (fr)
AT (1) ATE451581T1 (fr)
DE (1) DE502007002275D1 (fr)
RU (1) RU2451241C2 (fr)
WO (1) WO2007141091A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2068082A1 (fr) 2007-12-04 2009-06-10 Siemens Aktiengesellschaft Composants de machines et turbine à gaz
EP2899464B1 (fr) * 2014-01-22 2017-01-11 Siemens Aktiengesellschaft Turbine à gaz avec une chambre de combustion de type silo
DE102017207392A1 (de) * 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silobrennkammer und Verfahren zum Umrüsten einer solchen

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3476283A (en) * 1968-07-05 1969-11-04 Universal Oil Prod Co Internally insulated and lined pressure vessel
GB1450894A (en) * 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
JPS55107310U (fr) * 1979-01-23 1980-07-26
US4289447A (en) * 1979-10-12 1981-09-15 General Electric Company Metal-ceramic turbine shroud and method of making the same
US4688310A (en) * 1983-12-19 1987-08-25 General Electric Company Fabricated liner article and method
FR2572394B1 (fr) * 1984-10-30 1986-12-19 Snecma Procede de fabrication d'un anneau de turbine en ceramique integre a un support metallique annulaire
DE3664374D1 (en) * 1985-12-02 1989-08-17 Siemens Ag Heat shield arrangement, especially for the structural components of a gas turbine plant
US4706453A (en) * 1986-11-12 1987-11-17 General Motors Corporation Support and seal assembly
US5024058A (en) * 1989-12-08 1991-06-18 Sundstrand Corporation Hot gas generator
UA27772C2 (uk) * 1990-11-29 2000-10-16 Сіменс Аг Теплозахисний екран на несучій структурі
DE4238369C2 (de) * 1992-11-13 1996-09-26 Mtu Muenchen Gmbh Bauteil aus einem metallischen Grundsubstrat mit keramischer Beschichtung
RU2088764C1 (ru) * 1993-12-02 1997-08-27 Яков Петрович Гохштейн Турбинная лопатка
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
JP3801452B2 (ja) * 2001-02-28 2006-07-26 三菱重工業株式会社 耐摩耗性コーティング及びその施工方法
US6703137B2 (en) * 2001-08-02 2004-03-09 Siemens Westinghouse Power Corporation Segmented thermal barrier coating and method of manufacturing the same
DE10326541A1 (de) * 2003-06-12 2005-01-05 Mtu Aero Engines Gmbh Verfahren zur Schaufelspitzenpanzerung der Laufschaufeln eines Gasturbinentriebwerkes und Vorrichtung zur Durchführung des Verfahrens
DE102004001722A1 (de) * 2004-01-13 2005-08-04 Mtu Aero Engines Gmbh Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln

Also Published As

Publication number Publication date
RU2008152379A (ru) 2010-07-20
ATE451581T1 (de) 2009-12-15
US20090180873A1 (en) 2009-07-16
WO2007141091A1 (fr) 2007-12-13
EP2024684A1 (fr) 2009-02-18
CN101473171B (zh) 2011-04-06
CN101473171A (zh) 2009-07-01
RU2451241C2 (ru) 2012-05-20
EP1865258A1 (fr) 2007-12-12
US8091366B2 (en) 2012-01-10
DE502007002275D1 (de) 2010-01-21

Similar Documents

Publication Publication Date Title
EP1443275B1 (fr) Chambre de combustion
EP1636526B1 (fr) Chambre a combustion
EP1947293B1 (fr) Aube directrice pour turbine à gaz
WO2009115437A2 (fr) Ensemble grille directrice pour un turbocompresseur à gaz d'échappement, turbocompresseur à gaz d'échappement et procédé de fabrication d'un ensemble grille directrice
EP2184445A1 (fr) Support d'aubes statorique axialement segmenté d'une turbine à gaz
EP2411631B1 (fr) Plaque d'étanchéité et système d'aube tournante
EP2024684B1 (fr) Turbine à gaz avec composants de machine blindé
EP2206885A1 (fr) Turbine à gaz
EP1731715A1 (fr) Transition d'une chambre de combustion à une turbine
EP2347100B1 (fr) Turbine à gaz avec insert de refroidissement
EP2871418B1 (fr) Chambre de combustion d'une turbine à gaz et son procédé de fabrication
EP1429077B1 (fr) Turbine à gaz
EP2362142A1 (fr) Agencement de brûleur
EP1588102B1 (fr) Element de bouclier thermique, chambre de combustion et turbine a gaz
EP2215405B1 (fr) Élément de machine et turbine à gaz
EP3921577B1 (fr) Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes
DE102012204777B4 (de) Verfahren zur Herstellung eines Verkleidungselementes sowie Verkleidungselement
EP1914382B1 (fr) Procédé de réparation d'une aube de turbine
WO2004109187A1 (fr) Element de protection thermique
EP3113901A1 (fr) Procédé de réparation d'un corps d'aube et manchon de refroidissement
EP3029267A1 (fr) Procédé de fabrication d'un amortisseur d'oscillations pour une aube de turbine au moyen de rechargement par soudage laser
EP1624156B1 (fr) Turbine à gaz ou à vapeur avec composant résistant aux contraintes
EP1398462A1 (fr) Turbine à gaz et pièce de transition
DE102020201448A1 (de) Additiv hergestellte Turbinenschaufel mit Verdrehsicherung und Justageverfahren
EP1329594A1 (fr) Réglage du jeu d'aubes pour une turbine à gas

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: 20081111

AK Designated contracting states

Kind code of ref document: A1

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 MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17Q First examination report despatched

Effective date: 20090318

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RTI1 Title (correction)

Free format text: GAS TURBINE COMPRISING ARMOR-PLATED MACHINE COMPONENTS

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

Representative=s name: SIEMENS SCHWEIZ AG

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 502007002275

Country of ref document: DE

Date of ref document: 20100121

Kind code of ref document: P

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: VDEP

Effective date: 20091209

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

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: 20091209

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20091209

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

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: 20091209

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: 20091209

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: 20091209

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

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: 20100320

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: 20100409

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: 20091209

Ref country code: IE

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: 20091209

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: 20091209

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: 20100409

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: 20100309

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: 20091209

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

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: 20091209

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: 20091209

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: 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: 20100310

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: 20091209

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20100430

26N No opposition filed

Effective date: 20100910

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 NON-PAYMENT OF DUE FEES

Effective date: 20100430

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

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: 20091209

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

Ref country code: IT

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

Effective date: 20100425

Ref country code: BE

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

Effective date: 20100430

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: 20091209

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: 20100425

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

Effective date: 20100610

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: 20091209

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 451581

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120425

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: 20120425

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

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

Ref country code: FR

Payment date: 20150415

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161230

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: 20160502

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502007002275

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: CH

Payment date: 20210705

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: 20220408

Year of fee payment: 16

Ref country code: GB

Payment date: 20220519

Year of fee payment: 16

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

Ref country code: FI

Payment date: 20220421

Year of fee payment: 16

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20220811 AND 20220817

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LI

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

Effective date: 20220430

Ref country code: CH

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

Effective date: 20220430

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

Ref country code: IT

Payment date: 20230421

Year of fee payment: 17

Ref country code: DE

Payment date: 20220617

Year of fee payment: 17

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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

Effective date: 20230425

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: 20230425

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

Ref country code: SE

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

Effective date: 20230426

Ref country code: GB

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

Effective date: 20230425

Ref country code: FI

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

Effective date: 20230425