EP2871419A1 - Chambre de combustion de turbine à gaz à bardeau destiné à réaliser une bougie d'allumage - Google Patents
Chambre de combustion de turbine à gaz à bardeau destiné à réaliser une bougie d'allumage Download PDFInfo
- Publication number
- EP2871419A1 EP2871419A1 EP20140191950 EP14191950A EP2871419A1 EP 2871419 A1 EP2871419 A1 EP 2871419A1 EP 20140191950 EP20140191950 EP 20140191950 EP 14191950 A EP14191950 A EP 14191950A EP 2871419 A1 EP2871419 A1 EP 2871419A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- shingle
- spark plug
- chamber wall
- projection
- 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
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
- F23R3/02—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.
- 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.
- a tubular, collar-like approach to the shingle is formed, which surrounds the recess for the implementation 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) on 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.
- tubular projection or collar is provided with an annular bearing surface or a step 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)
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 true EP2871419A1 (fr) | 2015-05-13 |
EP2871419B1 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) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2531918A (en) * | 2014-10-27 | 2016-05-04 | Rolls Royce Plc | Igniter assembly |
FR3071908A1 (fr) * | 2017-09-29 | 2019-04-05 | Safran Aircraft Engines | Chambre de combustion de turbomachine a geometrie de cheminee fixe |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10968829B2 (en) * | 2013-12-06 | 2021-04-06 | Raytheon Technologies Corporation | Cooling an igniter body of a combustor wall |
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 |
US10670275B2 (en) | 2017-09-08 | 2020-06-02 | Raytheon Technologies Corporation | Cooling configurations for combustor attachment features |
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 |
US10619857B2 (en) * | 2017-09-08 | 2020-04-14 | United Technologies Corporation | Cooling configuration for combustor attachment feature |
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 |
US11959643B2 (en) | 2021-06-07 | 2024-04-16 | 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 |
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 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1442184A (en) * | 1972-10-02 | 1976-07-07 | Gen Electric | Gas turbine engine igniter assembly |
EP0576435A1 (fr) | 1991-03-22 | 1994-01-05 | Rolls Royce Plc | Bruleur de turbine a gaz. |
EP0741268A1 (fr) | 1995-05-03 | 1996-11-06 | United Technologies Corporation | Ecran segmenté pour la paroi d'une chambre de combustion d'une turbine à gaz |
US7093441B2 (en) | 2003-10-09 | 2006-08-22 | United Technologies Corporation | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
EP1710501A2 (fr) | 1999-11-06 | 2006-10-11 | Rolls-Royce plc | Eléments de paroi pour turbomachine |
US20100212324A1 (en) * | 2009-02-26 | 2010-08-26 | Honeywell International Inc. | Dual walled combustors with impingement cooled igniters |
EP2330350A1 (fr) * | 2009-11-23 | 2011-06-08 | Honeywell International Inc. | Chambres de combustion à double paroi dotées d'allumeurs refroidis par projection |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6557350B2 (en) * | 2001-05-17 | 2003-05-06 | General Electric Company | Method and apparatus for cooling gas turbine engine igniter tubes |
US6715279B2 (en) * | 2002-03-04 | 2004-04-06 | General Electric Company | Apparatus for positioning an igniter within a liner port of a gas turbine engine |
GB0227842D0 (en) * | 2002-11-29 | 2003-01-08 | Rolls Royce Plc | Sealing Arrangement |
US20060231535A1 (en) * | 2005-04-19 | 2006-10-19 | Fuesting Timothy P | Method of welding a gamma-prime precipitate strengthened material |
US7546739B2 (en) * | 2005-07-05 | 2009-06-16 | General Electric Company | Igniter tube and method of assembling same |
FR2891350A1 (fr) * | 2005-09-29 | 2007-03-30 | Snecma Sa | Dispositif de guidage d'un element dans un orifice d'une paroi de chambre de combustion de turbomachine |
GB0610800D0 (en) * | 2006-06-01 | 2006-07-12 | Rolls Royce Plc | Combustion chamber for a gas turbine engine |
US8479490B2 (en) * | 2007-03-30 | 2013-07-09 | Honeywell International Inc. | Combustors with impingement cooled igniters and igniter tubes for improved cooling of igniters |
JPWO2009122474A1 (ja) * | 2008-03-31 | 2011-07-28 | 川崎重工業株式会社 | ガスタービン燃焼器の冷却構造 |
US8739546B2 (en) * | 2009-08-31 | 2014-06-03 | United Technologies Corporation | Gas turbine combustor with quench wake control |
US8201412B2 (en) * | 2010-09-13 | 2012-06-19 | General Electric Company | Apparatus and method for cooling a combustor |
EP2583784A1 (fr) * | 2011-10-21 | 2013-04-24 | Siemens Aktiengesellschaft | Préparation d'au moins un poste à souder avant le soudage et composant |
-
2013
- 2013-11-11 DE DE102013222932.1A patent/DE102013222932A1/de not_active Withdrawn
-
2014
- 2014-11-05 EP EP14191950.6A patent/EP2871419B1/fr not_active Not-in-force
- 2014-11-11 US US14/538,294 patent/US20150135719A1/en not_active Abandoned
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1442184A (en) * | 1972-10-02 | 1976-07-07 | Gen Electric | Gas turbine engine igniter assembly |
EP0576435A1 (fr) | 1991-03-22 | 1994-01-05 | Rolls Royce Plc | Bruleur de turbine a gaz. |
EP0741268A1 (fr) | 1995-05-03 | 1996-11-06 | United Technologies Corporation | Ecran segmenté pour la paroi d'une chambre de combustion d'une turbine à gaz |
EP1710501A2 (fr) | 1999-11-06 | 2006-10-11 | Rolls-Royce plc | Eléments de paroi pour turbomachine |
US7093441B2 (en) | 2003-10-09 | 2006-08-22 | United Technologies Corporation | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
US20100212324A1 (en) * | 2009-02-26 | 2010-08-26 | Honeywell International Inc. | Dual walled combustors with impingement cooled igniters |
EP2330350A1 (fr) * | 2009-11-23 | 2011-06-08 | Honeywell International Inc. | Chambres de combustion à double paroi dotées d'allumeurs refroidis par projection |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2531918A (en) * | 2014-10-27 | 2016-05-04 | Rolls Royce Plc | Igniter assembly |
GB2531918B (en) * | 2014-10-27 | 2018-01-31 | Rolls Royce Plc | Igniter assembly for a combustor of a gas turbine engine |
US10167781B2 (en) | 2014-10-27 | 2019-01-01 | Rolls-Royce Plc | Igniter assembly |
FR3071908A1 (fr) * | 2017-09-29 | 2019-04-05 | Safran Aircraft Engines | Chambre de combustion de turbomachine a geometrie de cheminee fixe |
US11391462B2 (en) | 2017-09-29 | 2022-07-19 | Safran Aircraft Engines | Turbine engine combustion chamber with fixed duct geometry |
Also Published As
Publication number | Publication date |
---|---|
DE102013222932A1 (de) | 2015-05-28 |
US20150135719A1 (en) | 2015-05-21 |
EP2871419B1 (fr) | 2016-03-09 |
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