EP2812636B1 - Dérivation de chambre de combustion annulaire - Google Patents

Dérivation de chambre de combustion annulaire Download PDF

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Publication number
EP2812636B1
EP2812636B1 EP13710388.3A EP13710388A EP2812636B1 EP 2812636 B1 EP2812636 B1 EP 2812636B1 EP 13710388 A EP13710388 A EP 13710388A EP 2812636 B1 EP2812636 B1 EP 2812636B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
outer shell
annular
ducts
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
EP13710388.3A
Other languages
German (de)
English (en)
Other versions
EP2812636A2 (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
Original Assignee
Siemens AG
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 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

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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
    • F23R3/02—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 a gas turbine with such an annular combustion chamber.
  • 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 achieves this object by providing an annular combustor for a gas turbine according to claim 1.
  • compressor air can be introduced in a region at the end of the combustion chamber, without participating in the combustion, that is, it is fed back to the air-fuel mixture after the combustion process.
  • 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.
  • the ring segments have the advantage of easier assembly and disassembly.
  • 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.
  • 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 mechanisms can also be mounted inside or outside 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 the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior has a heat-insulating layer.
  • 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 last row of heat shield plates which is the farthest from all heat shield plates of the core zone of combustion, metallic and the penultimate row is ceramic, because on the one hand, the operating temperature of ceramic materials is well above the maximum operating temperature of high temperature metal alloys and on the other hand, the high temperature metallic alloys have less brittleness and better thermal and thermal conductivity.
  • the infinitely adjustable actuator according to the invention for introducing compressor discharge air into a zone at the end of the combustion chamber, ie after the combustion has taken place, permits carbon monoxide emissions to be carried out in part-load operation reduce, because set due to a richer mixture higher combustion temperatures.
  • 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. 1 shows schematically and exemplarily 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. To protect against scaling 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 outside of the outer shell 12, as in FIG. 2 is shown.
  • the adjusting device 15 has ring segments 16, for example, two half rings, as in FIG. 3 one is shown. With appropriate essays 17 certain gap sizes can be set in the channels 14, or they are even completely closed.
  • the metallic inlet shell plates ie the plates of the last heat shield row 11 are shortened relative to a heat shield plate 18 of the last row of a ring combustion chamber of the prior art.
  • FIG. 4 shows such a heat shield plate 18 of the last row of a ring combustion chamber of the prior art, as well as the dashed line cut to a metallic heat-shaving plate 11 to obtain, as FIG. 5 shows and how it is needed for the present invention.
  • FIG. 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate heat shield plate row 13 and the openings 20 of the channels 14 in the outer shell 12 for the air bypass at partial load.
  • the last row 11 of the heat shield plates is shortened compared to the heat shield plates of the prior art and is arranged on the outer shell 12 of the annular combustion chamber 1 so that it no longer directly adjoins the penultimate row of the heat shield plates 13, there is a gap 19 in the circumferential direction of the annular combustion chamber 1 without the previous heat protection.
  • the channels 14 open into the interior of the annular combustion chamber 1.
  • the outer shell 12 between these openings 20 is exposed to very high temperatures during operation of the annular combustion chamber 1.
  • the interior of the outer shell 12 is in the region of the gap 19 between the last 11 and the penultimate row 13 of the heat shield plates, ie between the openings 20 of the channels 14 to the combustion chamber interior out with a thermal barrier coating Mistake.
  • the attachments 17 of the ring segments 16 on their exposed to the hot gas combustion surfaces 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)

Claims (9)

  1. Chambre de combustion (1) annulaire pour une turbine à gaz, comprenant une coque (12) extérieure, qui a au moins une ouverture (4) d'entrée pour un brûleur et une sortie (7) débouchant dans un espace (8) de turbine, caractérisé en ce qu'il est prévu dans la coque (12) extérieure, dans la zone de la sortie (7), des conduits (14) qui peuvent être fermés, qui sont dirigés sensiblement parallèlement à l'axe (2) de symétrie de la chambre de combustion (1) annulaire et par lesquels de l'air final de compresseur peut être envoyé dans la chambre de combustion (1) annulaire, caractérisé en ce que, pour fermer et ouvrir les conduits (14), il est prévu sur la faaace extérieure de la coque (12) extérieure un dispositif (15) de réglage, comprenant des segments (16) annulaires, qui forment un anneau dirigé coaxialement à la chambre de combustion (1) annulaire et pouvant coulisser axialement par rapport à la chambre de combustion (1) annulaire.
  2. Chambre de combustion (1) annulaire suivant la revendication 1, comprenant une dernière rangée de plaques (11) formant bouclier thermique disposée, dans la zone de la sortie (7) à l'intérieur de la chambre de combustion (1) annulaire, sur la coque (12) extérieure dans la direction périphérique et une avant-dernière rangée de plaques (13) formant bouclier thermique, disposée à côté de la dernière rangée (11) dans la direction de la au moins une ouverture (4) d'entrée, un intervalle (19) étant prévu entre la dernière (11) et l'avant-dernière (13) rangée de plaques formant bouclier thermique dans la région de l'ouverture (20) des conduits (14) à l'intérieur de la chambre de combustion (1) annulaire.
  3. Chambre de combustion (1) annulaire suivant l'une des revendications précédentes, dans laquelle l'anneau peut coulisser de manière continue.
  4. Chambre de combustion (1) annulaire suivant l'une des revendications précédentes, dans laquelle les segments (16) annulaires ont, sur leur côté éloigné de la turbine, des pions (17) de pénétration dans les conduits (14).
  5. Chambre de combustion (1) annulaire suivant la revendication 4, dans laquelle les pions (17) ont une forme trapézoïdale.
  6. Chambre de combustion (1) annulaire suivant l'une des revendications 4 ou 5, dans laquelle les pions (17) ont une couche de calorifugeage sur des surfaces soumises à du gaz chaud.
  7. Chambre de combustion (1) annulaire suivant l'une des revendications 2 à 6, dans laquelle l'intérieur de la coque (12) extérieure a une couche de calorifugeage dans la zone de l'intervalle (19).
  8. Chambre de combustion (1) annulaire suivant l'une des revendications précédentes, dans laquelle la dernière rangée de plaques (11) formant bouclier thermique est métallique et l'avant-dernière rangée (13) est céramique.
  9. Turbine à gaz ayant une chambre de combustion (1) annulaire suivant l'une des revendications précédentes.
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 EP2812636A2 (fr) 2014-12-17
EP2812636B1 true 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
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
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
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
WO2017032424A1 (fr) * 2015-08-27 2017-03-02 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

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus
DE69421896T2 (de) * 1993-12-22 2000-05-31 Siemens Westinghouse Power Umleitungsventil für die Brennkammer einer Gasturbine
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

Also Published As

Publication number Publication date
CN104169649A (zh) 2014-11-26
EP2812636A2 (fr) 2014-12-17
CN104169649B (zh) 2016-11-09
KR20140138710A (ko) 2014-12-04
WO2013135859A2 (fr) 2013-09-19
WO2013135859A3 (fr) 2013-11-14
US20150007573A1 (en) 2015-01-08
DE102012204162A1 (de) 2013-09-19

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