EP2871419B1 - Chambre de combustion de turbine à gaz avec une tuile pour insérer une bougie d'allumage - Google Patents

Chambre de combustion de turbine à gaz avec une tuile pour insérer une bougie d'allumage Download PDF

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Publication number
EP2871419B1
EP2871419B1 EP14191950.6A EP14191950A EP2871419B1 EP 2871419 B1 EP2871419 B1 EP 2871419B1 EP 14191950 A EP14191950 A EP 14191950A EP 2871419 B1 EP2871419 B1 EP 2871419B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
tile
spark plug
projection
recess
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
EP14191950.6A
Other languages
German (de)
English (en)
Other versions
EP2871419A1 (fr
Inventor
Dr.-Ing. Miklós Gerendás
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2871419A1 publication Critical patent/EP2871419A1/fr
Application granted granted Critical
Publication of EP2871419B1 publication Critical patent/EP2871419B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a gas turbine combustor and, more particularly, to a gas turbine combustor shingle configured to pass a spark plug.
  • the combustion chambers of gas turbines in particular of aircraft gas turbines, usually have a combustion chamber wall, which forms a support structure for shingles.
  • the shingles are disposed on the inside of the combustion chamber wall to shield them from the hot gas and to thermally insulate the support structure.
  • a gap is formed between the shingles and the support structure through which cooling air is passed.
  • Such cradled combustors are for example from the EP 0 576 435 A1 , of the EP 0 741 268 A1 or the EP 1 710 501 A2 known.
  • the support and sealing structure of the combustion chamber wall is protected from the intense heat radiation of the flame.
  • the support and sealing structure remains at a lower temperature and retains its mechanical strength.
  • a gas turbine combustor shingle and a gas turbine combustor having such a shingle are previously known.
  • the shingle has a recess for performing a spark plug and is in this respect provided with a tubular extension which extends from the side facing away from a combustion chamber of the shingle.
  • Such a construction also shows the US 2010/212324 A1 ,
  • the GB 1 442 184 A shows a solution in which the combustion chamber shingle is provided with a recess into which a sealing ring is inserted.
  • the invention has for its object to provide a gas turbine combustor with a shingle for performing a spark plug and a gas turbine combustor shingles, which avoid the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and enable a safe and simple arrangement of a spark plug.
  • the invention thus provides to provide the shingle with a recess for performing a spark plug. It is a tubular, collar-like approach to the Shingle formed, which encloses the recess for the passage of the spark plug and extending from the combustion chamber interior side facing away from the shingle.
  • the tubular extension is thus according to the invention dimensioned so that it extends from the shingle through the combustion chamber wall (support structure) through the cold side of the combustion chamber wall.
  • the tubular extension is in particular designed and dimensioned such that it is guided with a tight fit through the recess formed in the combustion chamber wall or support structure.
  • the shingle itself is formed in a suitable manner to form the recess for the implementation of the spark plug so that the spark plug can be operated safely and easily and kept.
  • the inventively provided shingles as mentioned, formed integrally with the tubular extension.
  • the shingle can be manufactured as a casting or produced by means of a laser deposition welding process (DLD).
  • DLD laser deposition welding process
  • the tubular extension is provided with a spark plug seal at its free end region, which projects beyond the combustion chamber wall via the cold side of the combustion chamber wall.
  • the seal can in particular be designed so that it does not touch the combustion chamber wall (support structure), in order to create no heat transfer in this area.
  • the tubular projection or collar is provided with an annular abutment surface or a step in order to apply the annular projection against the hot side of the combustion chamber wall (support structure). This results, on the one hand, in a sealing of the cooling air gap formed between the combustion chamber wall and the shingel. On the other hand, this provides additional support and storage of the shingle.
  • the tubular extension is provided with at least one cooling air, through which cooling air can be supplied to the inner wall of the tubular extension and thus to the spark plug in order to cool them.
  • the solution according to the invention thus has the advantage that a safe installation and arrangement of the spark plug without a spark plug tower is possible. Since the shingle is made of a more wear-resistant material than the combustion chamber wall, a reliable storage and positioning of the spark plug is ensured. Furthermore, according to the invention, in order to further reduce component tolerances, the spark plug hole (recess of the tubular extension) can be introduced particularly precisely by positioning relative to the support of the combustion chamber in a later production step. In order to facilitate the assembly, the above-mentioned spark plug seal can be additionally attached to the holder of the spark plug.
  • the Fig. 1 shows in a schematic sectional view of a gas turbine combustor 1, as it is known from the prior art.
  • the combustion chamber 1 has a heat shield 2 and a combustion chamber head 3 and a burner seal 4.
  • On a cool air-side combustion chamber wall 6 a plurality of shingles 7 are attached at a distance from the combustion chamber wall 6.
  • combustion chamber wall 6 and the shingles 7 on Zumischlöcher 5 for supplying air.
  • the Fig. 2 shows a first embodiment of an inventive embodiment of a combustion chamber shingles 7. This has, as known from the prior art, effusion cooling holes 9 and is cooled by means of cooling air, which is supplied by impingement cooling holes 8 of the combustion chamber wall 6.
  • the shingle 7 is provided with a tubular extension 15 which extends in the direction of the combustion chamber wall 6 and is performed by a recess 23 of the combustion chamber wall 6.
  • the tubular extension 15 is formed integrally with the shingle 7, for example by means of a casting process.
  • the tubular projection 15 has a connecting web 10, which forms an annular contact surface 20, against which the combustion chamber wall 6 abuts.
  • the annular projection 15 is provided with a central recess 18, which forms a through hole for a spark plug.
  • the Fig. 2 further shows a spark plug seal 16, which, since the tubular projection 15 extends through the combustion chamber wall 6, has a distance from the combustion chamber wall 6.
  • the tubular extension 15 is further provided with a plurality of cooling air recesses 17 through which cooling air can be introduced into the recess 18 to cool the spark plug.
  • the Fig. 3 shows a further embodiment in an analogous representation, the same parts are provided with the same reference numerals. On a repeated description can therefore be omitted.
  • the shingle 7 is integrally formed with a portion of the combustion chamber wall 6 and made by a DLD method.
  • the region of the combustion chamber wall 6 formed on the shingle 7 is connected to the remaining combustion chamber wall by suitable means.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Claims (7)

  1. Bardeau de chambre de combustion d'une turbine à gaz comprenant un évidement (18) permettant le passage d'une bougie d'allumage, sachant que le bardeau (7) est muni d'un collet (15) tubulaire entourant l'évidement (18) et s'étendant à partir du côté du bardeau (7) opposé à un espace intérieur (19) de la chambre de combustion, caractérisé en ce que le collet (15) présente une surface d'appui (20) annulaire sur son pourtour extérieur.
  2. Bardeau selon la revendication n° 1, caractérisé en ce que le collet (15) est formé en une seule pièce avec le bardeau (7).
  3. Bardeau selon la revendication n° 1 ou n° 2, caractérisé en ce qu'à son extrémité libre, le collet (15) est muni d'un joint (16) de bougie d'allumage.
  4. Bardeau selon une des revendications n° 1 à n° 3, caractérisé en ce que le collet (15) est muni d'au moins un évidement d'air de refroidissement (17) s'étendant à travers la paroi du collet (15).
  5. Bardeau selon une des revendications n° 1 à n° 4, caractérisé en ce que le bardeau (7) avec le collet (15) est formé en tant que pièce moulée.
  6. Bardeau selon une des revendications n° 1 à n° 4, caractérisé en ce que le bardeau (7) avec le collet (15) est produit moyennant un procédé de soudage au laser de dépôt.
  7. Chambre de combustion de turbine à gaz, avec une paroi (6) de chambre de combustion sur laquelle sont disposés des bardeaux (7), ainsi qu'avec un évidement (18) s'étendant à travers la paroi (6) de chambre de combustion et un bardeau (7) pour permettre le passage d'une bougie d'allumage, caractérisée en ce que le bardeau (7) est conçu selon une des revendications n° 1 à n° 6.
EP14191950.6A 2013-11-11 2014-11-05 Chambre de combustion de turbine à gaz avec une tuile pour insérer une bougie d'allumage Not-in-force EP2871419B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013222932.1A DE102013222932A1 (de) 2013-11-11 2013-11-11 Gasturbinenbrennkammer mit Schindel zur Durchführung einer Zündkerze

Publications (2)

Publication Number Publication Date
EP2871419A1 EP2871419A1 (fr) 2015-05-13
EP2871419B1 true EP2871419B1 (fr) 2016-03-09

Family

ID=51868060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14191950.6A Not-in-force EP2871419B1 (fr) 2013-11-11 2014-11-05 Chambre de combustion de turbine à gaz avec une tuile pour insérer une bougie d'allumage

Country Status (3)

Country Link
US (1) US20150135719A1 (fr)
EP (1) EP2871419B1 (fr)
DE (1) DE102013222932A1 (fr)

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EP3077641B1 (fr) * 2013-12-06 2020-02-12 United Technologies Corporation Refroidissement d'un corps à ouverture pour un allumeur d'une paroi de chambre de combustion
GB201419053D0 (en) 2014-10-27 2014-12-10 Rolls Royce Plc Igniter Assembly
US20160209035A1 (en) * 2015-01-16 2016-07-21 Solar Turbines Incorporated Combustion hole insert with integrated film restarter
US10094564B2 (en) * 2015-04-17 2018-10-09 Pratt & Whitney Canada Corp. Combustor dilution hole cooling system
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10753283B2 (en) * 2017-03-20 2020-08-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling hole arrangement
US10619857B2 (en) * 2017-09-08 2020-04-14 United Technologies Corporation Cooling configuration for combustor attachment feature
US10670273B2 (en) 2017-09-08 2020-06-02 Raytheon Technologies Corporation Cooling configurations for combustor attachment features
US10670274B2 (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
FR3071908B1 (fr) 2017-09-29 2019-09-20 Safran Aircraft Engines Chambre de combustion de turbomachine a geometrie de cheminee fixe
US10330204B2 (en) * 2017-11-10 2019-06-25 Rolls-Royce Deutschland Ltd & Co Kg Burner seal of a gas turbine and method for manufacturing the same
GB201804656D0 (en) 2018-03-23 2018-05-09 Rolls Royce Plc An igniter seal arrangement for a combustion chamber
FR3088412B1 (fr) * 2018-11-12 2022-07-15 Safran Aircraft Engines Chambre de combustion de turbomachine, turbomachine associee
US11371701B1 (en) 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US11774098B2 (en) 2021-06-07 2023-10-03 General Electric Company Combustor for a gas turbine engine
US11885495B2 (en) 2021-06-07 2024-01-30 General Electric Company Combustor for a gas turbine engine including a liner having a looped feature
US11959643B2 (en) 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
CN115342383B (zh) * 2022-07-06 2023-07-07 哈尔滨工程大学 一种采用混合旋流器的燃气轮机低污染燃烧室头部结构

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Also Published As

Publication number Publication date
US20150135719A1 (en) 2015-05-21
EP2871419A1 (fr) 2015-05-13
DE102013222932A1 (de) 2015-05-28

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