EP1288578A1 - Agencement de chambre de combustion - Google Patents

Agencement de chambre de combustion Download PDF

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Publication number
EP1288578A1
EP1288578A1 EP01120992A EP01120992A EP1288578A1 EP 1288578 A1 EP1288578 A1 EP 1288578A1 EP 01120992 A EP01120992 A EP 01120992A EP 01120992 A EP01120992 A EP 01120992A EP 1288578 A1 EP1288578 A1 EP 1288578A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
lining elements
arrangement according
annular
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.)
Withdrawn
Application number
EP01120992A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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
Priority to EP01120992A priority Critical patent/EP1288578A1/fr
Priority to JP2002248491A priority patent/JP2003083084A/ja
Priority to US10/232,177 priority patent/US6725666B2/en
Priority to CN02141445.9A priority patent/CN1258661C/zh
Publication of EP1288578A1 publication Critical patent/EP1288578A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Definitions

  • the invention relates to a combustion chamber arrangement for gas turbines with one connected to at least one burner, in a turbine chamber opening annular combustion chamber, one of which Ring combustion chamber bounding ring combustion chamber wall, double-skin built up and an inner shell of the annular combustion chamber wall detachable from an outer shell of the annular combustion chamber wall arranged lining elements assembled and is between the inner shell and the outer Shell of the annular combustion chamber wall from a cooling medium flowable gap is formed.
  • the invention relates also a gas turbine with such a combustion chamber arrangement.
  • the rail-like rods of those known from the prior art Annular combustion chambers have a length of approximately half Meters so that one is in the axial direction of the combustion chamber in the flow direction in front of or behind the end of the rail-like Assembly room of at least half a bar Meter length must be present. Seen in the direction of flow however, the turbine blades are directly behind the combustion chamber arranged in front of the combustion chamber of the burners, so that neither in front nor behind the rail-like bars is sufficient Space to assemble or disassemble the lining elements remains.
  • the assembly and disassembly of the lining elements an expensive disassembly of the gas turbine.
  • the outer housing must be covered or it must be additionally the runner will be removed, which is an additional high workload for the exchange of the lining elements means.
  • the invention is therefore based on the object of developing a combustion chamber arrangement of the type mentioned at the outset such that an exchange of individual lining elements of the inner shell of the annular combustion chamber wall is possible with comparatively little effort.
  • the invention proposes that the lining elements are trapezoidal, each with an outwardly directed fastening structure formed in each of the longitudinal sides for releasably fastening to a corresponding counter structure of an adjacent lining element and / or a supporting structure connected to the outer shell.
  • the lining elements Due to the trapezoidal design of the lining elements, d. H. which at an angle other than 90 ° to the End edges of the lining elements, as well as those formed laterally on each of the long sides, fastening structures facing outwards are sufficient a slight shift around the trapezoidal liner element of the corresponding counter structures to solve and disassemble.
  • the lining element can do the other way round introduced and by means of a slight shift to be attached to the counter structures.
  • assembling or disassembling of the lining element required axial displacement only 0.1 to 0.05 meters, which is a clear one Shortening the space required compared to that from the State of the art known 0.5 meters. So needs for an assembly or disassembly of the lining elements at a Combustion chamber arrangement according to the invention the gas turbine not to be further disassembled. Neither is it necessary to remove the outer casing and the runner refer to.
  • the grooves can be used as a fastening structure on the long sides of the trapezoidal ones Lining elements can be arranged, the springs as a counter structure on an adjacent lining element or the supporting structure connected to the outer shell.
  • the trapezoidal lining element has a spring on its long side, which in a on an adjacent lining element or on one with longitudinal structure connected to the outer shell attacks.
  • a further relief for the assembly or disassembly of the Lining elements result if these do not overlap extend the entire axial length of the annular combustion chamber, but cover only part of this length, being complete Lining of the ring combustion chamber in the axial direction at least two lining elements arranged one behind the other are. With such a measure, the individual Lining elements are kept small and are easier to do handle.
  • the annular combustion chamber is opposite in its axial extent one due to the axial extension of the turbine space or the turbine shaft angled machine axis arranged.
  • Such an angle results in an In the direction of the turbine chamber, the diameter of the Annular combustion chamber, creating an axial division of the inner Shell of the annular combustion chamber wall inevitably leads trapezoidal segments. So can trapezoidal lining elements are used, all with their narrower end edge in the direction of the turbine space, with your wider front edge oriented towards the burner are arranged.
  • the lining elements each have additional fastening structures exhibit.
  • a fastening opening for the passage of a fixing element, such as a bolt there it is preferred that the mounting opening on a narrower Base side of the trapezoidal lining element arranged is.
  • the lining element can be one of the narrower Long groove arranged on the front opposite side be provided. This can also be done with a Screw bolts are attached. These bolts represent the only fixed points of the construction, the first in two Directions, the second in one direction.
  • a gas turbine is proposed with the invention, which a combustion chamber arrangement with or has several of the features described above.
  • the gas turbine has this an axially displaceable burner insert.
  • a axial displacement of the burner insert can be sufficient Space for moving the trapezoidal lining elements be created.
  • the axially displaceable burner insert is simply in the direction axially displaced away from the combustion chamber assembly, the the resulting space between the burner and the combustion chamber arrangement can be used to make the trapezoidal lining elements axially during assembly or disassembly move.
  • Fig. 1 is a section of a section of a Gas turbine shown, which has a combustion chamber arrangement according to the invention 1 contains.
  • the combustion chamber arrangement according to the invention 1 has an annular combustion chamber 2, which of a surrounded by a double-walled ring combustion chamber wall is.
  • the annular combustion chamber wall is composed of one inner shell 3 and an outer shell 4, being between the inner shell 3 and the outer shell 4 a gap 5 is trained.
  • the gap space 5 is during operation the gas turbine flows through a cooling fluid, which the Inner shell 3 of the annular combustion chamber cools convectively.
  • the inner shell 3 of the annular combustion chamber wall is made up of individual Lining elements 6a to 6d constructed. These are over Support structures releasably with the outer shell 4 of the annular combustion chamber wall connected.
  • At least one burner 18 is connected upstream of the annular combustion chamber, the annular combustion chamber opens into a turbine chamber 19. Die axial extension of the turbine chamber 19 or a turbine shaft defines a machine axis M. About this machine axis M the ring combustion chamber is positioned at an angle arranged.
  • the annular combustion chamber 2 is in the present case Embodiment shown double angled formed, whereby a in the circumferential direction of the annular combustion chamber 2 running dividing line 7 in the inner shell results. Along the dividing line 7 meet in the axial Towards the front, d. H. closer towards Brenner 18 and behind, d. H. closer to the turbine room 19 Lining elements 6a, 6c and 6b, 6d together.
  • the lining elements 6a to 6d are trapezoidal, as can be seen better in the following figures.
  • Fig. 2 shows a perspective view of a section seen from a combustion chamber arrangement 1 according to the invention from the direction of the turbine room.
  • the inner shell 3 of the wall of the annular combustion chamber 2 constructed from trapezoidal lining elements 6a, 6b is.
  • the dividing line can also be shown in this representation 7 are recognized in the circumferential direction of the annular combustion chamber runs and along which the front and rear Lining elements 6a, 6b collide.
  • the Annular combustion chamber starting from that assigned to the burner Side tapered towards the transition to the turbine space, so it is "funnel-shaped".
  • FIG. 3 is a perspective view Lining element 6 for building the inner shell 3 of the Wall of the annular combustion chamber 2 of the combustion chamber arrangement according to the invention 1 shown.
  • the lining element 6 has two opposite, essentially parallel running end faces 8 and 9 and the end faces connecting Long sides 10 and 11.
  • the width b1 of the in the The front face 8 shown in the drawing is smaller than the width b2 of the opposite face 9. This is due to the trapezoidal shape of the lining element 6.
  • the inner shell 3 of the annular combustion chamber wall is in the in the figures 1 and 2 shown ring combustion chamber 2 made of lining elements 6 constructed that the end faces 8 with the have a smaller width b1 in the direction of the turbine space 19, the end faces 9 with the larger width b2 in the direction the burner 18 are arranged.
  • Fig. 3 the principle of the suspension of the lining elements can well 6 can be recognized.
  • the lining element 6 has continuous longitudinal grooves 12 or 13, which with springs 14 on the side of the lining element attacking support structures 20 cooperate.
  • the support structures 20 are fixed to that in the FIGS. 1 and 2 shown outer shell 4 of the annular combustion chamber 2 connected and serve to attach the lining elements 6 under load of the gap space 5.
  • the lining element 6 is assembled or disassembled a short distance in the direction of the wide end face 9, So moved towards the burner, the side Longitudinal grooves 12 and 13 due to the trapezoidal shape resulting angular employment out of engagement with the springs 14 of the support structures 20 and the lining element 6 is therefore easy to remove.
  • additional attachment structures be provided. These are in the exemplary embodiment shown one in the area of the narrower end face 8 arranged opening 15 and one in the region of the wider End face 9 arranged long groove 16. In the area of the opening 15, a fixing bolt 17 is indicated, which for fixing of the lining element 6 through the opening 15 and be fixed to the outer shell of the housing wall can. Similarly, in the area of the long groove additional fixing bolt for fixing the lining element 6 Find use.
  • additional fixing bolt for fixing the Lining element 6 on the outer shell of the annular combustion chamber wall can be used on such structures if necessary be completely dispensed with.
  • the lining element 6 is trapezoidal with arranged on the long sides 10, 11 Fastening structures, which as shown in shape can be realized by longitudinal grooves 12, 13. This configuration enables easy assembly and disassembly the lining elements with compared to the prior art significantly reduced space requirements.
  • Burner 18 In order to assemble or disassemble the lining elements 6a to 6d to simplify an axial displacement of the Burner 18 can be provided opposite the annular combustion chamber 2. When the burner is axially displaced from the combustion chamber 2 way a free space is created, which to move the lining elements 6a to 6d during assembly or disassembly can be used.
  • the invention provides a combustion chamber arrangement in which the lining elements of the inner shell are one Annular combustion chamber with clearly compared to the prior art reduced effort can be assembled or disassembled. With the invention, a new type of gas turbine is created specified which the annular combustion chamber arrangement according to the invention used.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP01120992A 2001-08-31 2001-08-31 Agencement de chambre de combustion Withdrawn EP1288578A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP01120992A EP1288578A1 (fr) 2001-08-31 2001-08-31 Agencement de chambre de combustion
JP2002248491A JP2003083084A (ja) 2001-08-31 2002-08-28 燃焼器装置
US10/232,177 US6725666B2 (en) 2001-08-31 2002-08-28 Combustion-chamber arrangement
CN02141445.9A CN1258661C (zh) 2001-08-31 2002-08-30 燃烧室装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01120992A EP1288578A1 (fr) 2001-08-31 2001-08-31 Agencement de chambre de combustion

Publications (1)

Publication Number Publication Date
EP1288578A1 true EP1288578A1 (fr) 2003-03-05

Family

ID=8178497

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01120992A Withdrawn EP1288578A1 (fr) 2001-08-31 2001-08-31 Agencement de chambre de combustion

Country Status (4)

Country Link
US (1) US6725666B2 (fr)
EP (1) EP1288578A1 (fr)
JP (1) JP2003083084A (fr)
CN (1) CN1258661C (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20092346A1 (it) * 2009-12-30 2011-06-30 Ansaldo Energia Spa Metodo di manutenzione di una camera di combustione di un impianto a turbina a gas e telaio di montaggio di una piastrella di una camera di combustione

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7975487B2 (en) * 2006-09-21 2011-07-12 Solar Turbines Inc. Combustor assembly for gas turbine engine
EP2242916B1 (fr) * 2008-02-20 2015-06-24 Alstom Technology Ltd Turbine à gaz
EP2116770B1 (fr) * 2008-05-07 2013-12-04 Siemens Aktiengesellschaft Atténuation dynamique de chambre de combustion et agencement de refroidissement
CN101737805B (zh) * 2008-11-10 2013-03-27 北京航空航天大学 低成本可变内径燃烧室及其设计和试验方法
SE534008C2 (sv) * 2009-02-24 2011-03-29 Euroturbine Ab Förfarande för drift av en gasturbinkraftanläggning och gasturbinkraftanläggning
JP5821550B2 (ja) * 2011-11-10 2015-11-24 株式会社Ihi 燃焼器ライナ
WO2014137428A1 (fr) 2013-03-05 2014-09-12 Rolls-Royce Corporation Tuile de chambre de combustion à effusion, convexion, impact à double paroi
ITMI20131177A1 (it) * 2013-07-12 2015-01-13 Ansaldo Energia Spa Dispositivo di fissaggio reversibile
JP6239938B2 (ja) * 2013-11-05 2017-11-29 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
EP2952812B1 (fr) * 2014-06-05 2018-08-08 General Electric Technology GmbH Chambre de combustion annulaire d'une turbine á gaz et segment de manchon
CN114413284A (zh) * 2021-12-28 2022-04-29 北京动力机械研究所 一种与环形燃烧室头部匹配的异形旋流器

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
DE4114768A1 (de) * 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
US5319923A (en) * 1991-09-23 1994-06-14 General Electric Company Air staged premixed dry low NOx combustor
DE4309200A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Einhängung und Entfernung thermisch hoch belasteter Teile in Turbinenanlagen
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
DE19727407A1 (de) * 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
DE19751299A1 (de) * 1997-11-19 1999-06-02 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2544538A (en) * 1948-12-01 1951-03-06 Wright Aeronautical Corp Liner for hot gas chambers
US2651912A (en) * 1950-10-31 1953-09-15 Gen Electric Combustor and cooling means therefor
NL113358C (fr) * 1957-02-18
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
WO1997038914A1 (fr) 1996-04-13 1997-10-23 Wella Aktiengesellschaft Garniture permettant de melanger et de prelever des matieres coulantes contenues dans au moins un recipient
DE19623300A1 (de) * 1996-06-11 1997-12-18 Siemens Ag Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen, mit geschichtetem Aufbau

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
DE4114768A1 (de) * 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
US5319923A (en) * 1991-09-23 1994-06-14 General Electric Company Air staged premixed dry low NOx combustor
DE4309200A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Einhängung und Entfernung thermisch hoch belasteter Teile in Turbinenanlagen
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
DE19727407A1 (de) * 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
DE19751299A1 (de) * 1997-11-19 1999-06-02 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20092346A1 (it) * 2009-12-30 2011-06-30 Ansaldo Energia Spa Metodo di manutenzione di una camera di combustione di un impianto a turbina a gas e telaio di montaggio di una piastrella di una camera di combustione
EP2341287A1 (fr) * 2009-12-30 2011-07-06 Ansaldo Energia S.p.A. Méthode de maintenance d'une chambre de combustion d'une centrale de turbine à gaz et structure de montage pour un carreau d'une chambre de combustion

Also Published As

Publication number Publication date
US6725666B2 (en) 2004-04-27
US20040011059A1 (en) 2004-01-22
CN1407282A (zh) 2003-04-02
CN1258661C (zh) 2006-06-07
JP2003083084A (ja) 2003-03-19

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