EP2809994A2 - Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion - Google Patents

Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion

Info

Publication number
EP2809994A2
EP2809994A2 EP13712711.4A EP13712711A EP2809994A2 EP 2809994 A2 EP2809994 A2 EP 2809994A2 EP 13712711 A EP13712711 A EP 13712711A EP 2809994 A2 EP2809994 A2 EP 2809994A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
heat shield
height
shield element
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.)
Granted
Application number
EP13712711.4A
Other languages
German (de)
English (en)
Other versions
EP2809994B1 (fr
Inventor
Francois Benkler
Thomas Brandenburg
Olga Deiss
Thomas Grieb
Marco Link
Nicolas Savilius
Daniel Vogtmann
Jan Wilkes
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP2809994A2 publication Critical patent/EP2809994A2/fr
Application granted granted Critical
Publication of EP2809994B1 publication Critical patent/EP2809994B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • the invention relates to a heat shield element of a Brennkam ⁇ mer, in particular an annular combustion chamber of a gas turbine plant, and refers to the bypass of compressor air to the combustion chamber at part load.
  • the invention further relates to a combustion chamber and a corresponding gas turbine plant.
  • Object of the present invention is to expand by indicating a bypass the carbon monoxide compliant driving range of the gas turbine as far as possible in the direction of low power.
  • Another object of the present invention is to provide an improved combustor. Finally, it is an object of the present invention to provide an improved gas turbine.
  • the first object is achieved by a heat shield element according to claim 1, the second object by a combustion chamber according to claim 6 and the third object by a gas turbine according to claim 10.
  • a heat shield element in particular for lining a combustion chamber wall, comprising a first wall with a hot side to be acted upon by a hot medium, a cold side facing the hot side and a peripheral edge located at a first, a second and a third narrow side of the first wall on the cold side, in substance up to a first elevation extends, the environmentally running edge at a fourth narrow side up to a two ⁇ th height extends that is smaller than the first height, and in that a second wall of the cold side is located substantially opposite the second height and is adjacent over the width of the fourth narrow side from the fourth narrow side over a part of the length of the fourth narrow side
  • Narrow sides extends, wherein the second wall has at its end facing away from the fourth narrow side end an edge which extends to the first height.
  • the invention is based on the idea that, in an annular combustion chamber, which is largely lined with ceramic Hitzeschildele ⁇ elements and only the inlet is lined in the turbine with metallic heat shield elements, shield elements, the supply of the bypass air in the region of the metallic heat the combustion chamber wall is to be done, because the supply ⁇ as far as possible behind the combustion to prevent cooling of the flame, but in front of the turbine to achieve the highest possible gas turbine efficiency, suc- should be.
  • a new design of the metallic heat shield elements is needed. This design is the subject of this invention.
  • the heat shield element is subdivided into two superimposed regions which are dense to one another and form chambers in the installed state, ie with the combustion chamber wall.
  • a first chamber extends over the entire surface of the heat shield element and is used for normal cooling of the metallic heat shield.
  • a second chamber is located in the turbine facing portion of the heat shield element above the first chamber.
  • a heat shield element of a high temperature resistant metal or a high temperature resistant metal alloy since these materials have a lower brittleness than, for example, ceramic and a comparatively ⁇ as good heat and Temperaturleit .
  • a plurality of spaced circumferential edge cooling air openings from which the pre-cooling to the heat shield element provided ⁇ compressor discharge air can escape into the combustion chamber.
  • the cooling air openings are arranged at least in the region of the second wall between the first and the second wall.
  • thedeöffnun ⁇ gene in the region of the first chamber for the cooling of the heat shield element.
  • the heat shield element further comprises a mounting opening, the enclosure of which extends from the first wall to the first height.
  • the heat shield element is used to protect against overheating ei ⁇ ner hot gas component, in particular a combustion chamber, preferably an annular combustion chamber of a gas turbine, which has a combustion chamber wall, with a burner side and a turbine end, wherein the combustion chamber wall has a circumferential direction.
  • a number of heat shield elements is preferably arranged at the turbine end of the combustion chamber wall to form two chambers in the circumferential direction, wherein the fourth
  • Narrow side is aligned towards the turbine end.
  • the heat shield elements are preferably fixed with Fixed To ⁇ fixing bolts on the combustion chamber wall.
  • bores are introduced in the combustion chamber wall so that coolant can be supplied to the heat shield elements.
  • at least one supply channel per heat shield element is arranged in the region of the respective second wall in the combustion chamber wall, which opens into a plenum which revolves at least partially around the combustion chamber.
  • the combustion chamber to which heat shield elements are attached is preferably part of a gas turbine.
  • This gas turbine comprises at least one discharge for compressor air, which opens into the plenum via at least one line with a valve.
  • the invention enables the supply of bypass air in the hot gas path without far-reaching modifications to H synthgasbond ⁇ generating components.
  • the implementation is therefore likely to be comparatively inexpensive. It ensures that no hot gas is drawn in even when the bypass is switched off, since the second chamber is constantly purged and its outlet streamlined between heat shield element and turbine vane 1 is located.
  • FIG. 2 shows a metallic heat shield element according to the invention
  • FIG. 3 shows a section through an annular combustion chamber according to the invention with removal system for the compressor Lucasby- pass.
  • 1 shows schematically and exemplarily the Burn ⁇ recognition system 1 an annular combustion chamber according to the prior art in a housing 2.
  • the annular combustion chamber 1 is disposed about a rotor axis 3 of a closed ring.
  • Burner 4 are arranged in the upper region of the combustion chamber 1 in inlet openings 5. There, the mixing of the fuel 6 with the compressor air 7 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet at the turbine end 8 of the annular combustion chamber 1, the hot combustion gases enter the turbine 9, where they meet the first stationary vane 10.
  • the annular combustion chamber 1 is lined with ceramic heat shield elements 11 and metallic heat shield elements 12, which are fastened to the combustion chamber wall 13.
  • FIG. 2 shows a metallic heat shield element 14 according to the invention which is to be fastened to the combustion chamber wall 13 and forms with it a first chamber 15 and a second chamber 16 open in the direction of the turbine, which are sealed against each other.
  • the metallic heat shield member 14 itself includes a first wall 17 with a with a hot medium beaufschlag ⁇ cash hot side 18, one of the hot side 18 opposite the cold side 19, and four intermediate narrow sides 20,
  • a peripheral edge 24 extends from each narrow side 20, 21, 22, 23 beyond the cold side 19. At the first 20, the second 21 and the third narrow side 22, the edge 24 extends substantially to a first height 25 with respect to the cold side 19 of the first wall 17 and on the fourth narrow side 23 only to a smaller second height 26. This is the built-me ⁇ -metallic heat shield member 14 at the edges of three narrow ⁇ pages 20, 21, 22 on the combustion chamber wall 13 at.
  • a second wall 27 is located substantially opposite to the second height 26 of the cold side 19. It extends over the width of the fourth narrow side 23 and the fourth narrow ⁇ page 23 from a portion of the length of the fourth narrow side 23 adjacent narrow sides 20, 22. Furthermore, the second wall 27 at its fourth narrow side 23 make ⁇ turned end 28 on an edge 29, which extends from the second height 26 to the first height 25.
  • a plurality of cooling air openings 30 are provided in the peripheral edge 24 in the region of the first chamber 15.
  • the first chamber 15 is supplied as in heat shield elements 12 of the prior art via holes through the combustion chamber wall 13 with Ver Whyrend Kunststoff for cooling, which escapes from the metallic heat shield element 14 via these cooling air ⁇ openings 30.
  • the metallic heat shield element 14 has a Fixed To ⁇ restriction opening 31, the skirt 32 extends from the first wall 17 to the first height 25th By this Befes- actuating opening 31, the heat shield member 14 is secured by means of fastening bolts Be ⁇ on the combustion chamber wall. 13
  • the supply of open in the direction of the turbine 9 second chamber 16 with compressor air consists of two components. On the one hand, the second chamber 16 becomes permanent over some
  • the second chamber 16 can be actuated switchably with a bypass mass flow. This is done over comparatively large holes, i. compared to the holes for the flushing, fed in the combustion chamber wall 13.
  • the bypass mass flow then escapes via the opening at the trailing edge, i. the combustion chamber facing side of the heat shield element 14, on which the peripheral edge 24 extends only to the second height 26, in the gap between the metallic heat shield element 14 and the first stationary vane 10th
  • FIG. 3 shows how compressor air is first led out of the gas turbine via a removal 33 for the bypass. Outside of the gas turbine, the circuit via a Ven ⁇ til 34. Thereafter, the air is carried via a line 35 is recirculated to the gas turbine ⁇ and inputted in a ring around the combustion chamber 1 in order ⁇ running Plenum 36th From there lead stub lines 37 or tap holes to the respective second chamber 16 of the respective metallic heat shield element 14.
  • a valve 34, a line 35 and a plenum 36 are shown. However, solutions with more withdrawals, valves, pipes and plenums are also possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un élément écran thermique (14), en particulier pour garnir une paroi (13) de la chambre de combustion, qui comprend une première paroi (17) présentant un côté chaud (18) pouvant être soumis à l'action d'un milieu chaud, un côté froid (19) opposé au côté chaud (18) et un bord périphérique (24) qui s'étend au niveau d'un premier (20), d'un deuxième (21) et d'un troisième petit côté (22) de la première paroi (17) au-delà du côté froid (19), essentiellement jusqu'à une première hauteur (25). Le bord périphérique (24) s'étend au niveau d'un quatrième petit côté (23) jusqu'à une deuxième hauteur (26) inférieure à la première hauteur (25), et une deuxième paroi (27) est opposée au côté froid (19) sensiblement sur la deuxième hauteur (26) et s'étend sur l'ensemble de la largeur du quatrième petit côté (23), depuis ledit quatrième petit côté (23) sur une partie de la longueur des petits côtés (20, 22) adjacents au quatrième petit côté (23). La deuxième paroi (27) présente au niveau de son extrémité (28) opposée au quatrième petit côté (23) un bord (29) qui s'étend jusqu'à la première hauteur (25). L'invention concerne en outre une chambre de combustion ainsi qu'une turbine à gaz.
EP13712711.4A 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion Not-in-force EP2809994B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012204103A DE102012204103A1 (de) 2012-03-15 2012-03-15 Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
PCT/EP2013/055007 WO2013135702A2 (fr) 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion

Publications (2)

Publication Number Publication Date
EP2809994A2 true EP2809994A2 (fr) 2014-12-10
EP2809994B1 EP2809994B1 (fr) 2016-05-04

Family

ID=48013936

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13712711.4A Not-in-force EP2809994B1 (fr) 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion

Country Status (6)

Country Link
US (1) US20150027128A1 (fr)
EP (1) EP2809994B1 (fr)
CN (1) CN104169648B (fr)
DE (1) DE102012204103A1 (fr)
RU (1) RU2622590C2 (fr)
WO (1) WO2013135702A2 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012204162A1 (de) * 2012-03-16 2013-09-19 Siemens Aktiengesellschaft Ringbrennkammer-Bypass
US10408451B2 (en) 2013-09-11 2019-09-10 Siemens Aktiengesellschaft Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
EP3084310A4 (fr) * 2013-12-19 2017-01-04 United Technologies Corporation Ensemble paroi de moteur à turbine à gaz présentant une architecture de rails circonférentiels associés à des tiges filetées
US10645404B2 (en) 2014-03-24 2020-05-05 Qualcomm Incorporated Generic use of HEVC SEI messages for multi-layer codecs
DE102014206018A1 (de) * 2014-03-31 2015-10-01 Siemens Aktiengesellschaft Gasturbinenanlage
DE102014214981B3 (de) * 2014-07-30 2015-12-24 Siemens Aktiengesellschaft Seitenbeschichtetes Hitzeschildelement mit Prallkühlung an Freiflächen
DE102014221225A1 (de) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Hitzeschildelement und Verfahren zu seiner Herstellung
DE102015202097A1 (de) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ringbrennkammer mit Bypasssegment
CN104654359B (zh) * 2015-02-13 2017-12-19 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃烧室预混合燃料喷嘴的引流结构
CN104654358B (zh) * 2015-02-13 2017-09-15 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种带有引流结构的燃烧室预混合燃料喷嘴
DE102015205975A1 (de) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs-Hitzeschildelement
DE102015215207A1 (de) * 2015-08-10 2017-02-16 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine und Hitzeschildelement zum Auskleiden einer derartigen Brennkammer
WO2017032424A1 (fr) * 2015-08-27 2017-03-02 Siemens Aktiengesellschaft Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée
DE102015224524A1 (de) * 2015-12-08 2017-06-08 Siemens Aktiengesellschaft Brennkammer mit Resonatoren
US10237339B2 (en) * 2016-08-19 2019-03-19 Microsoft Technology Licensing, Llc Statistical resource balancing of constrained microservices in cloud PAAS environments
DE102018204453B4 (de) * 2018-03-22 2024-01-18 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit unterschiedlichen Krümmungen für eine Brennkammerwand und eine hieran fixierte Brennkammerschindel
DE102020116245B4 (de) * 2020-06-19 2024-03-07 Man Energy Solutions Se Baugruppe einer Gasturbine mit Brennkammerluftbypass

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2312654A1 (fr) * 1975-05-28 1976-12-24 Snecma Perfectionnements aux chambres de combustion pour moteurs a turbine a gaz
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
GB9018014D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
DE19730751A1 (de) * 1996-07-24 1998-01-29 Siemens Ag Keramisches Bauteil für eine Wärmeschutzschicht sowie Wärmeschutzschicht
FR2752916B1 (fr) * 1996-09-05 1998-10-02 Snecma Chemise de protection thermique pour chambre de combustion de turboreacteur
US6358041B1 (en) * 2000-04-21 2002-03-19 Eastman Chemical Company Threaded heat shield for burner nozzle face
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
EP1284390A1 (fr) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz
JP2003201863A (ja) * 2001-10-29 2003-07-18 Mitsubishi Heavy Ind Ltd 燃焼器及びこれを備えたガスタービン
RU2243448C2 (ru) * 2002-12-18 2004-12-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Камера сгорания
EP1482246A1 (fr) * 2003-05-30 2004-12-01 Siemens Aktiengesellschaft Chambre de combustion
EP1486730A1 (fr) * 2003-06-11 2004-12-15 Siemens Aktiengesellschaft Elément de bouclier thermique
EP1507116A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
US7363763B2 (en) * 2003-10-23 2008-04-29 United Technologies Corporation Combustor
GB0425794D0 (en) * 2004-11-24 2004-12-22 Rolls Royce Plc Acoustic damper
EP1715249A1 (fr) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Elément de bouclier thermique et chambre de combustion avec un bouclier thermique
ATE509236T1 (de) * 2007-10-26 2011-05-15 Siemens Ag Stützring für hitzeschildelemente eines flammenrohrs und eine brennkammeranordnung mit einem derartigen stützring
EP2182285A1 (fr) * 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
US9416970B2 (en) * 2009-11-30 2016-08-16 United Technologies Corporation Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel
US8499566B2 (en) * 2010-08-12 2013-08-06 General Electric Company Combustor liner cooling system
EP2960436B1 (fr) * 2014-06-27 2017-08-09 Ansaldo Energia Switzerland AG Structure de refroidissement pour un conduit de transition d'une turbine à gaz
DE102015205975A1 (de) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs-Hitzeschildelement

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2013135702A2 *

Also Published As

Publication number Publication date
WO2013135702A3 (fr) 2013-11-14
RU2014141355A (ru) 2016-05-10
EP2809994B1 (fr) 2016-05-04
WO2013135702A2 (fr) 2013-09-19
US20150027128A1 (en) 2015-01-29
CN104169648A (zh) 2014-11-26
DE102012204103A1 (de) 2013-09-19
RU2622590C2 (ru) 2017-06-16
CN104169648B (zh) 2016-03-02

Similar Documents

Publication Publication Date Title
EP2809994A2 (fr) Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion
EP3132202B1 (fr) Element de bouclier thermique avec contournement
DE102005025823B4 (de) Verfahren und Vorrichtung zum Kühlen einer Brennkammerauskleidung und eines Übergangsteils einer Gasturbine
EP2340397B1 (fr) Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
DE102014103085B4 (de) System mit Vielrohr-Brennstoffdüse mit Brennstoffdüsengehäuse
EP2808611B1 (fr) Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
EP2300686B1 (fr) Turbine à gaz pourvue d'une aube directrice
CH702825A2 (de) Turbinenbrennkammer-Einsatzanordnung.
DE102008002890A1 (de) Wechselseitig gekühltes Turbinenleitrad
DE112019000871B4 (de) Brennkammer und damit ausgestattete gasturbine
EP2812636B1 (fr) Dérivation de chambre de combustion annulaire
CH707842A2 (de) Verfahren und Vorrichtung zur Verbesserung der Wärmeübertragung in Turbinenabschnitten von Gasturbinen.
DE102015120128A1 (de) Turbinenradabdeckplattenmontierte Gasturbinen-Zwischenstufendichtung
DE102015113146A1 (de) Systeme und Vorrichtungen im Zusammenhang mit Gasturbinenbrennkammern
EP2852735A2 (fr) Turbine à gaz
EP3017253A1 (fr) Bouclier thermique céramique cunéiforme d'une chambre de combustion de turbine à gaz
EP2507557B1 (fr) Agencement de brûleur
CH708705A2 (de) Turbinenleitschaufelsegment mit Kühlung.
EP1904717B1 (fr) Element de carter conducteur de gaz chaud, enveloppe de protection d'arbre et systeme de turbine a gaz
DE102009044584B4 (de) Schaufelanordnung mit Kühlöffnungen für ein Turbinentriebwerk
EP1724526A1 (fr) Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
DE1278176B (de) Brennkammer
DE112015003797B4 (de) Gasturbine
DE112021000203T5 (de) Wärmeisolationsmaterialanordnung und Gasturbine
DE102004032062A1 (de) Verfahren und Vorrichtung zum Zuführen von Speiseluft in Turbinenbrennkammern

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: 20140905

AK Designated contracting states

Kind code of ref document: A2

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

AX Request for extension of the european patent

Extension state: BA ME

DAX Request for extension of the european patent (deleted)
REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502013002904

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23R0003000000

Ipc: F23R0003080000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/50 20060101ALI20151002BHEP

Ipc: F23R 3/08 20060101AFI20151002BHEP

Ipc: F23R 3/00 20060101ALI20151002BHEP

Ipc: F23R 3/60 20060101ALI20151002BHEP

INTG Intention to grant announced

Effective date: 20151106

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: 797259

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160515

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: 502013002904

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160504

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: 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: 20160504

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: 20160504

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: 20160804

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: 20160504

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: 20160504

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: 20160805

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: 20160504

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: 20160504

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: 20160504

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: 20160905

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: 20160504

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

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: 20160504

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: 20160504

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: 20160504

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: 20160504

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: 20160504

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013002904

Country of ref document: DE

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

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: 20160504

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: 20160504

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: 20170207

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: 20160504

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

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: CH

Ref legal event code: PL

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

Effective date: 20170312

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

Ref country code: MC

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

Effective date: 20160504

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20171130

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: 20170312

Ref country code: FR

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: GB

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

Effective date: 20170312

Ref country code: CH

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

Effective date: 20170331

Ref country code: LI

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

Effective date: 20170331

Ref country code: IE

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

Effective date: 20170312

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

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

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

Ref country code: DE

Payment date: 20180518

Year of fee payment: 6

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: 20160504

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: 20160504

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

Ref country code: IT

Payment date: 20190327

Year of fee payment: 7

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 797259

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180312

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: 20130312

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

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: 20160504

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502013002904

Country of ref document: DE

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: 20160504

Ref country code: AT

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

Effective date: 20180312

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: 20160504

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: 20191001

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: 20160504

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

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: 20160904

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: 20200312