EP2918915B1 - Bardeaux de chambre de combustion d'une turbine à gaz - Google Patents

Bardeaux de chambre de combustion d'une turbine à gaz Download PDF

Info

Publication number
EP2918915B1
EP2918915B1 EP15158450.5A EP15158450A EP2918915B1 EP 2918915 B1 EP2918915 B1 EP 2918915B1 EP 15158450 A EP15158450 A EP 15158450A EP 2918915 B1 EP2918915 B1 EP 2918915B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
bolt
chamber tile
accordance
mounting
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.)
Not-in-force
Application number
EP15158450.5A
Other languages
German (de)
English (en)
Other versions
EP2918915A1 (fr
Inventor
Carsten Clemen
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 EP2918915A1 publication Critical patent/EP2918915A1/fr
Application granted granted Critical
Publication of EP2918915B1 publication Critical patent/EP2918915B1/fr
Not-in-force 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
    • F23R3/42—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
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to gas turbine combustors with combustor shingles, wherein the combustor shingles are attached to a supporting structure of the combustion chamber outer walls.
  • the combustion chamber shingles have any (very high, often several thousand) number of Effusionskühllöchern on the side facing the combustion chamber side. These effusion cooling holes serve to cool the shingle from the high temperatures in the combustion chamber.
  • located on the combustion chamber shingle at least one mixing air hole, which serves to air from the outer chamber surrounding the combustion chamber (annulus) in the combustion chamber for the purpose of cooling and Abmagerns combustion and thus the reduction of NOx formation in the combustion chamber conduct.
  • the shingles are often still provided with a ceramic coating, which acts as an insulating layer against the high temperatures in the combustion chamber.
  • the FIG. 2 schematically shows a combustion chamber 15.
  • the combustion chamber 15 includes a fuel nozzle 29, which is supported in a conventional manner to a combustion chamber head. Furthermore, a combustion chamber outer housing 30 and a combustion chamber inner housing 31 are provided.
  • a combustion chamber wall 32 encloses the actual combustion chamber 15 and carries combustion chamber shingles 34.
  • the reference numeral 33 schematically shows a Turbinenvorleit Herbert. By Zumischlöcher 35 air is supplied in the usual manner. The inflow direction is designated by the reference numeral 36.
  • FIG. 3 shows a shingle 34 with effusion cooling holes 37 according to the prior art.
  • the geometry (diameter, shape) of the mixing hole 35 can be suitably formed as known in the art. The same applies to the size and arrangement of the effusion cooling holes 37.
  • the training of Zumischlöcher 35 often takes place so that they are constructive as a funnel or a tube which projects into the combustion chamber 15, are formed.
  • the shingles 34 are usually formed either by casting, coating with a ceramic layer and drilling the effusion cooling holes 37 (e.g., laser), or by casting, drilling, and coating, or by an additive manufacturing method, such as a laser. Selective laser sintering, direct laser depositioning or by electron beam welding. In the additive process, the effusion cooling holes 37 are introduced directly into the shingle 34 and the costly drilling is eliminated.
  • the effusion cooling holes 37 e.g., laser
  • the construction of the shank with integrated threaded pin is only conditionally for an additive manufacturing, e.g. Selective laser sintering, direct laser deposition or electron beam deposition welding, suitable because either the costly horizontal production must be selected or a complex substructure must be provided to support the threaded pin.
  • an additive manufacturing e.g. Selective laser sintering, direct laser deposition or electron beam deposition welding
  • Such a substructure has significant disadvantages. It is a) material-intensive, b) it extends the manufacturing process and c) it has to be removed from the shingle after production. This is very expensive.
  • the EP 2 270 395 A1 shows a heat shield element arrangement for gas turbines, in which heat shield elements by means of spring elements and screws from the hot Side of the heat shield element from being attached to a support structure.
  • the screw used for this purpose can be provided with a centric air channel.
  • the invention has for its object to provide a combustion chamber shingle gas turbine and a mounting option such a combustion chamber, which avoid the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and ensure good fastenability.
  • the shingle is formed substantially plate-shaped and on one side (namely at the combustion chamber wall facing side) has at least one bearing element which is integrally formed on the shingle.
  • the bearing element is designed so that a bolt, which is made as a separate component, can be anchored or fastened in a form-fitting manner.
  • the combustion chamber shingle according to the invention is thus designed so that a separate bolt, which according to the invention may be a threaded bolt or a bolt to be fastened with a securing element, is anchored in a form-fitting manner to the shingle.
  • a separate bolt which according to the invention may be a threaded bolt or a bolt to be fastened with a securing element, is anchored in a form-fitting manner to the shingle.
  • the bolt is preferably made for the bolt to be provided at its end region with a bearing area arranged at right angles to the bolt axis, which bearing area is arranged in a recess of the bearing element.
  • the bolt is thus similar to a hook, and is inserted into the recess of the bearing element.
  • the storage area of the bolt can be dimensioned in a suitable manner, for example plate-shaped or with any other cross-sections, for example round, oval, square or rectangular.
  • the combustion chamber shingle thus has by the bearing element and the recess provided therein a receptacle for the bolt, so that it can be hooked in a form-fitting manner in the shingle. It is inventively possible to include the storage area with play or without play in the recess, in particular to take into account different thermal expansions or the like.
  • the recess of the bearing element is designed so that the storage area of the bolt can be inserted laterally.
  • the recesses open to different directions. As a result, a release of the bolt is prevented.
  • the bolt according to the invention is inserted in a conventional manner through a hole of the combustion chamber outer wall, so that the actual attachment of the bolt does not differ significantly from the prior art. Thus, it is possible to unscrew a nut in a conventional manner in a threaded bolt.
  • the embodiment of the invention also makes it possible to support the shingle relative to the combustion chamber wall or, in an alternative embodiment, to apply the shingle directly to the combustion chamber wall.
  • different cooling concepts can be formed, as is known from the prior art.
  • the outer contour of the bearing element which is attached to the combustion chamber shingle aerodynamic form, for example, to provide with bevelled edges.
  • effusion cooling holes may be formed to ensure the cooling of the combustion chamber shingles.
  • the bolt has a central passage opening through which cooling air can be introduced.
  • the recess of the bearing element is designed and dimensioned such that when the bolt or mounted combustion chamber shingles a cavity between the bearing portion of the bolt and the surface of the combustion chamber shingles results, which is traversed by cooling air. This also leads to a particularly good cooling.
  • the bearing element is provided with additional cooling holes. These may be formed as impact cooling holes to additionally cool the lower portion of the bolt and its storage area.
  • the inventive bolt with the storage area formed on it can be cast, milled or produced by an additive process.
  • the combustion chamber shingle is designed such that it can be produced by means of an additive method.
  • additive methods are, for example, selective laser sintering, direct laser depositioning (DLD) or electron beam deposition welding.
  • DLD direct laser depositioning
  • the shingle is so manufacturable that neither a costly horizontal production, nor a complex substructure are required. Thus, the shingle can be inexpensively and easily manufactured.
  • 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 formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, a medium 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 comprise a plurality of stages, each of which has a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward 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 high pressure turbine 16 and mid 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.
  • the Fig. 4 shows different side views according to the prior art, in which a support 41 of the combustion chamber shingle 34 is shown against the combustion chamber wall 32.
  • the Fig. 5 shows a simplified plan view of a combustor shingle 34 according to the invention.
  • rims 51 are provided at the edge, which, as well as from Fig. 6 can be seen, are formed in the form of a web-like edge.
  • a bearing element 40 is provided in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 each have a bearing element 40 is provided, which is provided with a slot-like or pocket-like recess 44. It can be seen that the opening directions of the recesses 44 are oriented differently, so that inserted bolts 38 in the assembled state can not slip out, even if the nuts 39 solve, since the bolts 38 are located in recesses or holes of the associated combustion chamber wall 32.
  • a bearing element 40 is arranged in the central area of the Fig. 5 in the central area of the Fig. 5 in the central area of the Fig.
  • Fig. 6 shows in a greatly simplified form a mounted side view, analogous to the representation of Fig. 5 ,
  • the Fig. 7 shows in the upper and lower rows respectively threaded bolts 38. These each have a central through-hole 48 in the form of a hole through which the through-hole cooling air can pass. From the pictures of Fig. 7 It can be seen that each bolt 38 is provided with a perpendicular to its central axis aligned bearing portion 47, which is insertable into a suitable recess 44 of the bearing member 40, as shown in FIG Fig. 10 is shown. From the Fig. 7 It turns out that different forms of Storage areas 47 may be provided, namely round, square, rectangular, rounded or trapezoidal. Other shapes are also possible. The Fig. 7 shows that the storage area 47 may be provided with at least one cooling air hole 50 to cool the storage area 47 and thus the lower area of the bolt 38.
  • the Fig. 8 shows a wide variety of design variants of bolts 38 with bearing areas 47, analogous to the representations of Fig. 7 ,
  • associated bearing elements 40 are shown with suitable recesses 44.
  • the bearing elements 40 may also be provided with cooling holes 52. It follows that the recesses 44 of the bearing elements 40 are each dimensioned so that the bolts 38 can be inserted laterally with the bearing areas 47.
  • Fig. 9 arise in a variety of design variants in the assembled state, in particular it can be seen how the storage areas 47 are respectively inserted into the slot-like or pocket-like recesses 44 of the bearing elements 40.
  • the bearing areas 47 rest against the upper limbs or surfaces of the bearing elements 40, so that a cavity 49 forms below the bearing areas 47, in which cooling air is introduced on the one hand through the through-hole 48 of the bolt 38 and on the other hand through additional cooling holes 52.
  • additional cooling holes 52 for cooling air flow are also lateral recesses 53, which on the two right below in Fig. 9 shown embodiment variants are shown.
  • the Fig. 10 shows in a simplified sectional view of an assembled state of the bolt 38 according to the invention with its storage area 47 in a recess 44 of a bearing element 40. Again, the cavity 49 is clarified, which is filled with cooling air. Furthermore, cooling air can flow through effusion cooling holes 37.
  • the Fig. 11 shows a further embodiment variant, in which the storage areas 40 are each provided with lateral cooling holes 52, which are provided in rows or in regular arrangements to introduce cooling air to the lower portion of the bolt 38.
  • the Fig. 12 shows in different perspective partial views again possible embodiments of the bearing elements 40. It follows that these may be bell-like or bow-shaped and each having a lateral slot or a lateral opening to insert the bolt 38.

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)

Claims (9)

  1. Bardeau de chambre de combustion d'une turbine à gaz avec un boulon (38) destiné à loger le bardeau de chambre de combustion (34) à une paroi de chambre de combustion (32), sachant que le bardeau de chambre de combustion (34) est pour l'essentiel conçu en forme de plaque et présente sur un côté au moins un élément de logement (40) auquel est ancré par complémentarité de forme le boulon (38) conçu en tant que composant distinct, que dans sa zone terminale le boulon (38) est muni d'une zone de logement (47) disposée perpendiculairement à l'axe du boulon (46) et placée dans un évidement (44) de l'élément de logement (40), que l'évidement (44) de l'élément de logement (40) est dimensionné plus grand que la zone de logement (47) du boulon (38) afin de former une cavité (49) entre la surface du bardeau de chambre de combustion (34) et la zone de logement (37) du boulon (38), caractérisé en ce que le boulon (38) présente un évidement de passage (48) centrique et que l'élément de logement (40) est muni de trous de refroidissement par effusion (37).
  2. Bardeau de chambre de combustion selon la revendication n° 1, caractérisé en ce que l'élément de logement (40) est muni de trous de refroidissement (52).
  3. Bardeau de chambre de combustion selon une des revendications n° 1 ou n° 2, caractérisé en ce que l'évidement (44) de l'élément de logement (40) est ouvert latéralement.
  4. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 3, caractérisé en ce que l'élément de logement (40) est conçu en forme d'arceau ou de cloche.
  5. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 4, caractérisé en ce que le boulon (38) avec la zone de logement (47) peut être inséré dans l'évidement (44) perpendiculairement à l'axe de boulon (46) du boulon (38).
  6. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 5, caractérisé en ce que sur le bardeau de chambre de combustion (34) sont formés plusieurs éléments de logement (40) dont les évidements (44) sont ouverts suivant différentes directions.
  7. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 6, caractérisé en ce que la zone de logement (47) est conçue en forme de plaque ou de barre.
  8. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 7, caractérisé en ce que l'élément de logement (40) est intégré dans un bord marginal (51) du bardeau de chambre de combustion (34).
  9. Bardeau de chambre de combustion selon une des revendications n° 1 à n° 8, caractérisé en ce que le boulon (38) est conçu en tant que boulon fileté.
EP15158450.5A 2014-03-11 2015-03-10 Bardeaux de chambre de combustion d'une turbine à gaz Not-in-force EP2918915B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014204472.3A DE102014204472A1 (de) 2014-03-11 2014-03-11 Brennkammerschindel einer Gasturbine

Publications (2)

Publication Number Publication Date
EP2918915A1 EP2918915A1 (fr) 2015-09-16
EP2918915B1 true EP2918915B1 (fr) 2016-12-28

Family

ID=52705989

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15158450.5A Not-in-force EP2918915B1 (fr) 2014-03-11 2015-03-10 Bardeaux de chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US20150260400A1 (fr)
EP (1) EP2918915B1 (fr)
DE (1) DE102014204472A1 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3022424B1 (fr) * 2013-07-16 2019-10-09 United Technologies Corporation Ensemble de panneau en céramique de moteur de turbine à gaz et procédé de fabrication d'un ensemble de panneau en céramique de moteur de turbine à gaz
EP3139090B1 (fr) * 2015-09-04 2018-06-13 Rolls-Royce Deutschland Ltd & Co KG Composant comprenant un bardeau de chambre de combustion pour une turbine a gaz
DE102015217161A1 (de) * 2015-09-04 2017-03-09 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe mit einer Brennkammerschindel für eine Gasturbine
DE102015225505A1 (de) * 2015-12-16 2017-06-22 Rolls-Royce Deutschland Ltd & Co Kg Wand eines mittels Kühlluft zu kühlenden Bauteils, insbesondere einer Gasturbinenbrennkammerwand
EP3540314B1 (fr) * 2016-11-11 2023-07-12 Kawasaki Jukogyo Kabushiki Kaisha Chemise de chambre de combustion pour une turbine à gaz
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
DE102017203326A1 (de) * 2017-03-01 2018-09-06 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel-Anordnung einer Gasturbine
US10533747B2 (en) * 2017-03-30 2020-01-14 General Electric Company Additively manufactured mechanical fastener with cooling fluid passageways
US10670273B2 (en) 2017-09-08 2020-06-02 Raytheon Technologies Corporation Cooling configurations for combustor attachment features
US10670275B2 (en) 2017-09-08 2020-06-02 Raytheon Technologies Corporation Cooling configurations for combustor attachment features
US10619857B2 (en) * 2017-09-08 2020-04-14 United Technologies Corporation Cooling configuration for combustor attachment feature
US10670274B2 (en) 2017-09-08 2020-06-02 Raytheon Technologies Corporation Cooling configurations for combustor attachment features
DE102018213925A1 (de) 2018-08-17 2020-02-20 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Schindelbauteil und Positonierungshilfe
DE102019202466B4 (de) * 2019-02-22 2023-03-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Schindelbauteil und hieran zueinander ausgerichteten, je ein Befestigungselement tragenden Grundkörpern sowie Herstellungsverfahren
CN116772238A (zh) * 2022-03-08 2023-09-19 通用电气公司 圆顶-导流器接头冷却布置
CN117917530A (zh) * 2022-10-20 2024-04-23 通用电气公司 用于涡轮发动机的联接组件
JP2024091029A (ja) * 2022-12-23 2024-07-04 川崎重工業株式会社 ガスタービンの燃焼器

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
US4749298A (en) * 1987-04-30 1988-06-07 United Technologies Corporation Temperature resistant fastener arrangement
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
US6145319A (en) 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6389813B2 (en) * 2000-03-31 2002-05-21 Quiet Systems International, Llc Passive mounted lining system
EP1381811A1 (fr) * 2001-04-27 2004-01-21 Siemens Aktiengesellschaft Chambre de combustion, en particulier d'une turbine a gaz
GB2380236B (en) * 2001-09-29 2005-01-19 Rolls Royce Plc A wall structure for a combustion chamber of a gas turbine engine
DE10214570A1 (de) 2002-04-02 2004-01-15 Rolls-Royce Deutschland Ltd & Co Kg Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln
DE50209166D1 (de) * 2002-08-16 2007-02-15 Siemens Ag Innenkühlbare Schraube
US8171634B2 (en) * 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
EP2261564A1 (fr) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Agencement d'élément d'un bouclier thermique doté d'un moyen de guidance de vis et procédé de montage d'un élément d'un bouclier thermique
ES2531099T3 (es) * 2009-06-09 2015-03-10 Siemens Ag Disposición de elemento de escudo térmico y procedimiento para el montaje de un elemento de escudo térmico
GB0913580D0 (en) * 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
US8943835B2 (en) * 2010-05-10 2015-02-03 General Electric Company Gas turbine engine combustor with CMC heat shield and methods therefor
DE102010027204A1 (de) * 2010-07-06 2012-01-12 Newfrey Llc Mutter, Befestigungsanordnung und Befestigungsverfahren
FR2976974B1 (fr) * 2011-06-24 2016-09-30 Safran Dispositif d'assemblage de panneaux acoustiques d'une nacelle de turbomachine
US9309834B2 (en) * 2012-05-31 2016-04-12 United Technologies Corporation Liner hanger cable
US20140003880A1 (en) * 2012-06-30 2014-01-02 General Electric Company Ceramic matrix composite and metal attachment configurations
GB201317006D0 (en) * 2013-09-25 2013-11-06 Rolls Royce Plc Component for attaching to a wall

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
DE102014204472A1 (de) 2015-09-17
EP2918915A1 (fr) 2015-09-16
US20150260400A1 (en) 2015-09-17

Similar Documents

Publication Publication Date Title
EP2918915B1 (fr) Bardeaux de chambre de combustion d'une turbine à gaz
EP2873921B1 (fr) Élément de protection contre la chaleur d'une chambre de combustion d'une turbine à gaz
EP2730843A1 (fr) Bardeaux de chambre de combustion d'une turbine à gaz
EP2770260B1 (fr) Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion
EP2886961B1 (fr) Rondelle de bardeaux de chambre de combustion d'une turbine à gaz
EP2738470B1 (fr) Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
EP2829804B1 (fr) Bardeaux de chambre de combustion d'une turbine à gaz et leur procédé fabrication
EP3369996B1 (fr) Dispositif formant bardeau de la chambre de combustion d'une turbine à gaz
EP2927594B1 (fr) Chambre de combustion d'une turbine à gaz
EP2921778A1 (fr) Chambre de combustion d'une turbine à gaz
DE102014114556A1 (de) Verriegelnde Abstandshalteranordnung
EP2730844B1 (fr) Bardeau de chambre de combustion d'une turbine à gaz et son procédé de fabrication
DE102015225505A1 (de) Wand eines mittels Kühlluft zu kühlenden Bauteils, insbesondere einer Gasturbinenbrennkammerwand
DE102014204468A1 (de) Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
DE102012016493A1 (de) Gasturbinenbrennkammer mit prallgekühlten Bolzen der Brennkammerschindeln
DE102014219552A1 (de) Leitschaufelverstellvorrichtung einer Gasturbine
CH708769A2 (de) Verriegelnde Abstandshalteranordnung zur Einführung in einen umlaufenden Befestigungsschlitz zwischen Plattformen benachbarter Laufschaufeln.
DE102014114553A1 (de) Verriegelnde Abstandshalteranordnung
EP2628900A1 (fr) Aube directrice de turbine dotée d'un élément d'étranglement
DE102009044584B4 (de) Schaufelanordnung mit Kühlöffnungen für ein Turbinentriebwerk
DE102016101168A1 (de) Strömungsmaschine mit einer in einer Ausnehmung einer Wandung anordenbaren Einsetzeinrichtung
DE102013222863A1 (de) Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
DE102012200539A1 (de) Abschirmeinrichtung für ein Turbinengehäuse einer thermischen Gasturbine
EP3022395B1 (fr) Elément d'insertion et turbine à gaz
DE102014222320A1 (de) Brennkammerwand einer Gasturbine mit Kühlung für einen Mischluftlochrand

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): 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

17P Request for examination filed

Effective date: 20150827

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

17Q First examination report despatched

Effective date: 20151218

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160727

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 RS 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: AT

Ref legal event code: REF

Ref document number: 857633

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170115

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: DE

Ref legal event code: R096

Ref document number: 502015000425

Country of ref document: DE

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: 20161228

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 3

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161228

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: 20170329

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: 20161228

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: 20170328

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161228

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: 20161228

Ref country code: RS

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: 20161228

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: 20161228

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: 20161228

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: 20161228

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: 20170428

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: 20161228

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: 20161228

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: 20161228

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

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: 20170428

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: 20161228

Ref country code: IT

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: 20161228

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: 20161228

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: 20161228

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: 20170328

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015000425

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

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: 20161228

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: 20161228

26N No opposition filed

Effective date: 20170929

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20170310

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: 20161228

Ref country code: IE

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

Effective date: 20170310

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

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

Ref country code: BE

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

Effective date: 20170331

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: 20161228

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: 20180331

Ref country code: CH

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

Effective date: 20180331

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

Ref country code: FR

Payment date: 20190325

Year of fee payment: 5

Ref country code: DE

Payment date: 20190327

Year of fee payment: 5

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: 20150310

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

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: 20161228

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

Ref country code: GB

Payment date: 20190404

Year of fee payment: 5

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161228

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: 20161228

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502015000425

Country of ref document: DE

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

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: 20161228

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502015000425

Country of ref document: DE

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: 20201001

Ref country code: FR

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

Effective date: 20200331

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

Effective date: 20200310

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: 20200310

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 857633

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200310

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: 20200310