EP2812636A2 - Dérivation de chambre de combustion annulaire - Google Patents

Dérivation de chambre de combustion annulaire

Info

Publication number
EP2812636A2
EP2812636A2 EP13710388.3A EP13710388A EP2812636A2 EP 2812636 A2 EP2812636 A2 EP 2812636A2 EP 13710388 A EP13710388 A EP 13710388A EP 2812636 A2 EP2812636 A2 EP 2812636A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
ring
outer shell
heat shield
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
EP13710388.3A
Other languages
German (de)
English (en)
Other versions
EP2812636B1 (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 EP2812636A2 publication Critical patent/EP2812636A2/fr
Application granted granted Critical
Publication of EP2812636B1 publication Critical patent/EP2812636B1/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
    • F23R3/26—Controlling the air flow
    • 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
    • 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

Definitions

  • the invention relates to an annular combustion chamber with a bypass for reducing the carbon monoxide emissions in part-load operation and to a gas turbine with such an annular combustion chamber.
  • the combustion temperature drops in the combustion chamber.
  • the primary zone temperature relevant for the carbon monoxide emissions also falls below a minimum value, whereby carbon monoxide is increasingly generated or expelled. Since this should be avoided, the usable partial load range of the gas turbine is limited.
  • the object of the invention is to provide an annular combustion chamber of the type mentioned, which allows a considerable increase in the usable partial load range.
  • the invention solves this problem by providing that in such an annular combustion chamber for a gas turbine with an outer shell which has at least one inlet opening for a burner and an outlet opening into a turbine chamber, closable in the outer shell in the region of the outlet and substantially parallel to Symmetryeachse the annular combustion chamber aligned channels are provided, can be guided by the Verêtrendluft into the annular combustion chamber.
  • compressor air can be introduced in a region at the end of the combustion chamber without participating in the combustion, that is, it is returned to the air-fuel mixture only after the combustion process. This causes the greasy mixture in the combustion chamber to become higher
  • the annular combustion chamber comprises a last row of heat shield plates arranged in the region of the outlet in the interior of the annular combustion chamber on the outer shell and a penultimate row of heat shield plates arranged in the direction of the at least one inlet opening next to the last row, between the last and penultimate Series of heat shield plates in the region of the channels a gap is provided. Through this gap, the compressor discharge air can flow undisturbed into the combustion chamber.
  • an adjusting device which comprises ring segments which form a ring which is aligned coaxially with the annular combustion chamber and axially displaceable relative to the annular combustion chamber.
  • the ring segments have the advantage of easier assembly and disassembly. It is expedient if the ring of the adjusting device is continuously displaceable in order to set as desired a desired gap size and thus to be able to remove a certain amount of air from the Verêtrendluft prior to combustion can.
  • the ring segments on their turbine side facing away from essays for engagement in the channels are trapezoidal.
  • the air to be passed through the channels can be set very precisely.
  • the channels can of course be completely closed.
  • the ring is moved by a mechanism only in the axial direction.
  • Such a mechanism for controlling and moving the ring segments So this can be done via motors, levers, hydraulic mechanisms, etc., the z. B. axially move the ring on rails or other motion elements.
  • these metrics also be mounted inside or outside of the housing.
  • the attachments of the ring segments have a thermal barrier coating (TBC) on their surfaces exposed to the hot gas of the combustion.
  • TBC thermal barrier coating
  • the interior of the outer shell in the region of the gap between see the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior towards a thermal barrier coating In prior art annular combustion chambers, the last and penultimate rows of heat shield plates still abut each other and the interior of the outer shell was sufficiently protected by the heat shield plates. Due to the gap caused by the invention, the outer shell in this area is more exposed to the combustion gases.
  • the invention can be implemented relatively easily, since the ring segments, for example two ring halves, are simple components which only have to be displaced axially.
  • FIG. 2 shows the turbine-facing side of the annular combustion chamber with adjusting device on the outer shell and bypass channels
  • FIG. 3 shows a half-ring of the adjusting device for the bypass
  • FIG. 4 shows a metal heat shield plate according to the prior art
  • Figure 5 shows a metallic heat shield plate for the annular combustion chamber according to the invention
  • FIG. 1 shows, schematically and by way of example, the combustion system of an annular combustion chamber 1 according to the invention.
  • the annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 2.
  • Burner 3 are arranged in the upper region of the combustion chamber 1 in inlet openings 4. There, the mixing of the fuel 5 with the compressor air 6 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet 7, the hot combustion gases pass into the turbine chamber 8, where they meet the first stationary vane 9.
  • the annular combustion chamber 1 is lined with ceramic heat shields 10 and metallic heat shields 11, which are attached to the outer shell 12.
  • an adjusting device 15 is provided on the outer side of the outer shell 12, as shown in FIG.
  • the adjusting device 15 has ring segments 16, for example, two half rings, as shown in Figure 3 one. With appropriate essays 17 certain gap sizes can be set in the channels 14, or they are even completely closed.
  • FIG. 4 shows such a heat shield plate 18 of the last row of a prior art annular combustion chamber as well as the dashed line cut around a metal heat shield plate 11 as shown in FIG. 5 and required for the present invention
  • Figure 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate 13 Hitzeschildplatten #2 and the openings 20 of the channels 14 in the outer shell 12 for the air bypass at partial load.
  • the attachments 17 of the ring segments 16 on their surfaces exposed to the hot gas of the combustion also have a thermal barrier coating.

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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une chambre de combustion annulaire (1) pour une turbine à gaz, qui présente une coque extérieure (12) comportant au moins une ouverture d'entrée (4) pour un brûleur (3) et une ouverture de sortie (7) débouchant dans l'espace turbine (8), des canaux (14) qui peuvent être fermés et sont orientés sensiblement parallèlement à l'axe de symétrie (2) de la chambre de combustion annulaire (1) étant prévus dans la coque extérieure (12), dans la zone de l'ouverture de sortie (7), canaux à travers lesquels peut être guidé de l'air de sortie de compresseur dans la chambre de combustion annulaire (1). L'invention concerne en outre une turbine à gaz.
EP13710388.3A 2012-03-16 2013-03-15 Dérivation de chambre de combustion annulaire Not-in-force EP2812636B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012204162A DE102012204162A1 (de) 2012-03-16 2012-03-16 Ringbrennkammer-Bypass
PCT/EP2013/055344 WO2013135859A2 (fr) 2012-03-16 2013-03-15 Dérivation de chambre de combustion annulaire

Publications (2)

Publication Number Publication Date
EP2812636A2 true EP2812636A2 (fr) 2014-12-17
EP2812636B1 EP2812636B1 (fr) 2016-06-29

Family

ID=47901090

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13710388.3A Not-in-force EP2812636B1 (fr) 2012-03-16 2013-03-15 Dérivation de chambre de combustion annulaire

Country Status (6)

Country Link
US (1) US20150007573A1 (fr)
EP (1) EP2812636B1 (fr)
KR (1) KR20140138710A (fr)
CN (1) CN104169649B (fr)
DE (1) DE102012204162A1 (fr)
WO (1) WO2013135859A2 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104807043A (zh) * 2014-11-29 2015-07-29 哈尔滨广瀚燃气轮机有限公司 天然气燃料燃气轮机环形燃烧室
CN104566463B (zh) * 2014-11-29 2016-12-07 哈尔滨广瀚燃气轮机有限公司 燃气轮机低排放燃烧室空气调节装置
DE102015202097A1 (de) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ringbrennkammer mit Bypasssegment
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
EP3320266B1 (fr) * 2015-08-27 2019-03-20 Siemens Aktiengesellschaft Élément d'écran thermique métallique à circulation d'air de refroidissement optimisée
CN108131399B (zh) * 2017-11-20 2019-06-28 北京动力机械研究所 一种发动机轴承座冷却结构
EP3499125A1 (fr) * 2017-12-12 2019-06-19 Siemens Aktiengesellschaft Chambre de combustion tubulaire pourvue de revêtement en céramique

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Publication number Priority date Publication date Assignee Title
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus
EP0660046B1 (fr) * 1993-12-22 1999-12-01 Siemens Westinghouse Power Corporation Système de dérivation pour une chambre de combustion d'une turbine à gaz
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
JP3846169B2 (ja) * 2000-09-14 2006-11-15 株式会社日立製作所 ガスタービンの補修方法
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
SE523082C2 (sv) * 2001-11-20 2004-03-23 Volvo Aero Corp Anordning vid en brännkammare hos en gasturbin för reglering av inflöde av gas till brännkammarens förbränningszon
US7631504B2 (en) * 2006-02-21 2009-12-15 General Electric Company Methods and apparatus for assembling gas turbine engines
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
US20110225947A1 (en) * 2010-03-17 2011-09-22 Benjamin Paul Lacy System and methods for altering air flow in a combustor
EP2423596A1 (fr) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Elément de bouclier thermique
GB201200237D0 (en) * 2012-01-09 2012-02-22 Rolls Royce Plc A combustor for a gas turbine engine
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer

Non-Patent Citations (1)

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Title
See references of WO2013135859A3 *

Also Published As

Publication number Publication date
DE102012204162A1 (de) 2013-09-19
WO2013135859A3 (fr) 2013-11-14
CN104169649B (zh) 2016-11-09
US20150007573A1 (en) 2015-01-08
CN104169649A (zh) 2014-11-26
KR20140138710A (ko) 2014-12-04
WO2013135859A2 (fr) 2013-09-19
EP2812636B1 (fr) 2016-06-29

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