US20150007573A1 - Annular-combustion-chamber bypass - Google Patents

Annular-combustion-chamber bypass Download PDF

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Publication number
US20150007573A1
US20150007573A1 US14/382,918 US201314382918A US2015007573A1 US 20150007573 A1 US20150007573 A1 US 20150007573A1 US 201314382918 A US201314382918 A US 201314382918A US 2015007573 A1 US2015007573 A1 US 2015007573A1
Authority
US
United States
Prior art keywords
combustion chamber
annular combustion
ducts
outer shell
heat
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.)
Abandoned
Application number
US14/382,918
Other languages
English (en)
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SAVILIUS, NICOLAS, Link, Marco, WILKES, JAN, BENKLER, FRANCOIS, DEISS, OLGA, GRIEB, THOMAS, VOGTMANN, DANIEL, Brandenburg, Thomas
Publication of US20150007573A1 publication Critical patent/US20150007573A1/en
Abandoned legal-status Critical Current

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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 having a bypass for reducing carbon monoxide emissions in partial load operation, and to a gas turbine having such an annular combustion chamber.
  • the combustion temperature in the combustion chamber drops.
  • the primary zone temperature which is relevant for carbon monoxide emissions also falls, to below a minimum value, whereby an increased quantity of carbon monoxide is generated and/or emitted.
  • the useful partial load range of the gas turbine is limited.
  • the invention achieves this object by providing that, in such an annular combustion chamber for a gas turbine, having an outer shell which has at least one inlet opening for a burner and an outlet that opens into a turbine space, ducts are provided in the outer shell in the region of the outlet, which ducts are closable and are oriented substantially parallel to the axis of symmetry of the annular combustion chamber, and through these compressor outlet air can be guided into the annular combustion chamber.
  • the annular combustion chamber comprises a last row of heat-shield plates arranged in the circumferential direction on the outer shell in the region of the outlet in the interior of the annular combustion chamber, and a second-to-last row of heat-shield plates arranged next to the last row in the direction of the at least one inlet opening, wherein a gap is provided between the last and second-to-last rows of heat-shield plates, in the region of the ducts.
  • an adjustment device comprising ring segments which form a ring that is oriented coaxially with the annular combustion chamber and may be moved axially with respect to the annular combustion chamber, is provided on the exterior of the outer shell for closing and opening the ducts.
  • the ring segments have the advantage of simpler assembly and/or disassembly.
  • the ring of the adjustment device can be moved in a continuously variable manner in order to set, as required, a desired gap width and thus to be able to remove a determined quantity of air from the compressor outlet air prior to the combustion.
  • the ring segments have, on their side facing away from the turbine, projections for engaging in the ducts.
  • the projections are of trapezoidal design.
  • the quantity of air to be guided through the ducts can be set with particular precision.
  • the ducts may of course also be entirely closed.
  • the ring is moved only in the axial direction, by a mechanism.
  • a mechanism for controlling and moving the ring segments Specifically, this can be effected using motors, lever or hydraulic mechanisms, etc., which for example displace the ring axially on rails or other movement elements.
  • these mechanisms may also be installed inside or outside the housing.
  • the projections 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 also has a thermal barrier coating in the region of the gap, between the last and the second-to-last rows of the heat-shield plates, that is to say between the openings of the ducts into the interior of the combustion chamber.
  • the last and the second-to-last rows of the heat-shield plates still adjoin one another and the interior of the outer shell was sufficiently protected by the heat-shield plates.
  • the gap resulting from the invention increases the exposure of the outer shell, in this region, to the hot gases of the combustion.
  • the last row of heat-shield plates which is the furthest of all the heat-shield plates from the core region of the combustion, is metallic and the second-to-last row is ceramic as, on one hand, the service temperature of ceramic materials is substantially higher than the maximum service temperature of high-temperature metal alloys and, on the other hand, high-temperature metal alloys are less brittle and have better heat- and temperature-conducting behavior.
  • the invention also indicates a novel gas turbine in which an annular combustion chamber according to the invention is integrated.
  • the consumption of cold air in baseload operation is no greater than with current designs.
  • the invention is relatively easy to convert as the ring segments, for example two half rings, are simple components which need only be displaced axially.
  • FIG. 1 shows a combustion system having an annular combustion chamber according to the invention
  • FIG. 2 shows the turbine-facing side of the annular combustion chamber with adjustment device on the outer shell and bypass ducts
  • FIG. 3 shows a half ring of the adjustment device for the bypass
  • FIG. 4 shows a metallic heat-shield plate according to the prior art
  • FIG. 5 shows a metallic heat-shield plate for the annular combustion chamber according to the invention
  • FIG. 6 shows the interior of the annular combustion chamber in the region of the outlet.
  • 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 .
  • Burners 3 are arranged in inlet openings 4 in the upper region of the combustion chamber 1 . This is where the fuel 5 is mixed with the compressor air 6 .
  • the actual combustion takes place in the combustion chamber 1 .
  • the hot combustion gases enter the turbine space 8 through the outlet 7 and there impinge upon the first static guide vane 9 .
  • the annular combustion chamber 1 is clad with ceramic heat-shields 10 and metallic heat-shields 11 which are attached to the outer shell 12 .
  • the combustion chamber outer shell 12 is provided with ducts 14 between the last ceramic heat-shield row 13 (i.e. the second-to-last heat-shield row) and the metallic intake shell plate (i.e. the last heat-shield row 11 ), in the region of the outlet 7 , which ducts are oriented substantially parallel to the axis 2 of the annular combustion chamber 1 .
  • an adjustment device 15 is provided on the exterior of the outer shell 12 , as shown in FIG. 2 .
  • the adjustment device 15 has ring segments 16 , for example two half rings, one of which is shown in FIG. 3 .
  • ring segments 16 for example two half rings, one of which is shown in FIG. 3 .
  • the metallic intake shell plates that is to say the plates of the last heat-shield row 11 are shorter than a heat-shield plate 18 of the last row of an annular combustion chamber according to the prior art.
  • FIG. 4 shows such a heat-shield plate 18 of the last row of an annular combustion chamber according to the prior art and the shortening undertaken at the broken line so as to obtain a metallic heat-shield plate 11 as shown in FIG. 5 and as required for the present invention.
  • FIG. 6 shows a view of the interior of the annular combustion chamber 1 with last 11 and second-to-last 13 heat-shield plate rows and the openings 20 of the ducts 14 in the outer shell 12 for the air bypass during partial load.
  • the last row 11 of the heat-shield plates is shorter than the heat-shield plates according to the prior art and is arranged on the outer shell 12 of the annular combustion chamber 1 such that it no longer directly adjoins the second-to-last row of the heat-shield plates 13 , there results a gap 19 in the circumferential direction of the annular combustion chamber 1 without the heat protection which exists hitherto.
  • the ducts 14 open into the interior of the annular combustion chamber 1 in this gap 19 .
  • the interior of the outer shell 12 is provided with a thermal barrier coating in the region of the gap 19 between the last 11 and the second-to-last row 13 of the heat-shield plates, that is to say between the openings 20 of the ducts 14 toward the combustion chamber interior.
  • the projections 17 of the ring segments 16 also have a thermal barrier coating on their surfaces exposed to the hot gas of the combustion.

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)
US14/382,918 2012-03-16 2013-03-15 Annular-combustion-chamber bypass Abandoned US20150007573A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012204162.1 2012-03-16
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 (1)

Publication Number Publication Date
US20150007573A1 true US20150007573A1 (en) 2015-01-08

Family

ID=47901090

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/382,918 Abandoned US20150007573A1 (en) 2012-03-16 2013-03-15 Annular-combustion-chamber bypass

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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016124348A1 (fr) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Chambre de combustion annulaire comprenant un segment de dérivation

Families Citing this family (7)

* 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
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

Citations (6)

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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
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
US7096675B2 (en) * 2001-11-20 2006-08-29 Volvo Aero Corporation Device for a combustion chamber in a gas turbine for controlling the intake of gas to a combustion zone
US7631504B2 (en) * 2006-02-21 2009-12-15 General Electric Company Methods and apparatus for assembling gas turbine engines
US8726626B2 (en) * 2012-01-09 2014-05-20 Rolls-Royce Plc Combustor for a gas turbine engine
US20150027128A1 (en) * 2012-03-15 2015-01-29 Siemens Aktiengesellschaft Heat-shield element for a compressor-air bypass around the combustion chamber

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Publication number Priority date Publication date Assignee Title
DE69421896T2 (de) * 1993-12-22 2000-05-31 Siemens Westinghouse Power Umleitungsventil für die Brennkammer einer Gasturbine
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
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

Patent Citations (6)

* 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
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
US7096675B2 (en) * 2001-11-20 2006-08-29 Volvo Aero Corporation Device for a combustion chamber in a gas turbine for controlling the intake of gas to a combustion zone
US7631504B2 (en) * 2006-02-21 2009-12-15 General Electric Company Methods and apparatus for assembling gas turbine engines
US8726626B2 (en) * 2012-01-09 2014-05-20 Rolls-Royce Plc Combustor for a gas turbine engine
US20150027128A1 (en) * 2012-03-15 2015-01-29 Siemens Aktiengesellschaft Heat-shield element for a compressor-air bypass around the combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016124348A1 (fr) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Chambre de combustion annulaire comprenant un segment de dérivation

Also Published As

Publication number Publication date
CN104169649A (zh) 2014-11-26
EP2812636A2 (fr) 2014-12-17
CN104169649B (zh) 2016-11-09
EP2812636B1 (fr) 2016-06-29
KR20140138710A (ko) 2014-12-04
WO2013135859A2 (fr) 2013-09-19
WO2013135859A3 (fr) 2013-11-14
DE102012204162A1 (de) 2013-09-19

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AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BENKLER, FRANCOIS;DEISS, OLGA;GRIEB, THOMAS;AND OTHERS;SIGNING DATES FROM 20140805 TO 20140901;REEL/FRAME:033669/0710

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION