EP1288574A1 - Agencement de chambre de combustion - Google Patents

Agencement de chambre de combustion Download PDF

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Publication number
EP1288574A1
EP1288574A1 EP01121089A EP01121089A EP1288574A1 EP 1288574 A1 EP1288574 A1 EP 1288574A1 EP 01121089 A EP01121089 A EP 01121089A EP 01121089 A EP01121089 A EP 01121089A EP 1288574 A1 EP1288574 A1 EP 1288574A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbine
chamber arrangement
individual
arrangement according
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Withdrawn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
EP01121089A
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
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
Priority to EP01121089A priority Critical patent/EP1288574A1/fr
Priority to PCT/EP2002/009556 priority patent/WO2003021149A1/fr
Priority to DE50207662T priority patent/DE50207662D1/de
Priority to JP2003525188A priority patent/JP2005502020A/ja
Priority to CNA028150961A priority patent/CN1537212A/zh
Priority to US10/488,622 priority patent/US6968672B2/en
Priority to EP02767441A priority patent/EP1423647B1/fr
Publication of EP1288574A1 publication Critical patent/EP1288574A1/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Withdrawn legal-status Critical Current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
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • the invention relates to a combustion chamber arrangement for a gas turbine with a variety of in one, in one Individual combustion chambers leading to the annular space leading to the turbine space, with burners upstream of the individual combustion chambers are that with the individual combustion chambers through an outer casing are connected through.
  • the invention further relates to a Gas turbine with such a combustion chamber arrangement.
  • Such combustion chamber arrangements for gas turbines are in the state of the art.
  • a mixture ignited in the burners from an oxygen-containing fuel gas and a fuel is burned in the combustion chambers and the expanding ones Hot gases are released through the transition sections of the individual combustion chambers in the direction of the turbine chamber and the ones inside Arrangement of guide vanes and rotor blades deflected.
  • The are in the usually circular cylindrical built entrance sections of the individual combustion chambers generated hot gas flows with a circular cross section the transition sections into a hot gas stream with a circular segment Cross section transferred and finally to merged into a circular hot gas stream. This enters the turbine space through the annular gap and drives the blades of the gas turbine.
  • Cooling fluid flows open on the individual combustion chambers over and creates a cooling effect.
  • the cooling fluid flow is not directed and defined, which results in an overall lower cooling efficiency.
  • such a design of the individual combustion chambers structurally simpler and requires less effort.
  • the invention has for its object to further develop a combustion chamber arrangement of the type mentioned in such a way that the cooling efficiency can be increased considerably in the case of individual combustion chambers of simple design.
  • At least one connecting piece which is arranged on a side of the turbine outer casing facing the turbine space and extends radially in the direction of the turbine space and at least partially surrounds a section of at least one individual combustion chamber while leaving a gap space.
  • the arranged on the turbine outer casing according to the invention radially extending in the direction of the turbine space at least a nozzle surrounds one inside the turbine outer casing located section of at least one single combustion chamber and leaves between the wall of the single combustion chamber and the Trim a gap.
  • a cooling fluid can enter this gap flow in and due to the defined flow channel cause more effective convective cooling in this area.
  • the single combustion chamber itself remains unchanged simple in structure, a complication of the construction the single combustion chamber itself is not required. On in this way the quasi closed cooling area of the Single combustion chamber in the interior of the turbine outer casing extended towards the turbine chamber, the cooling efficiency is noticeably improved.
  • the nozzle can of the invention in the circumferential direction of the individual combustion chamber be closed so that it extends over the entire Circumferential area of the single combustion chamber in the section in which the nozzle according to the invention in the interior of the outer housing the gas turbine protrudes, is cooled virtually closed.
  • the invention settles the single combustion chamber from a substantially cylindrical shaped input section downstream of the burner and a transition section fading into a circular ring sector together, the nozzle at least the input section partially surrounds.
  • the entrance section is due its proximity to the burner is particularly thermally stressed Element of the single combustion chamber, so that the possibility of a quasi closed cooling, which is due to the invention provided neck in this area is a significant Improve the cooling of the individual combustion chamber with represents comparatively less expenditure on cooling fluid.
  • a low expenditure of cooling fluid increases the economy of the gas turbine as a whole, and in those cases where the cooling fluid is simultaneously used as fuel gas, the efficiency of the gas turbine is increased at the same time.
  • the nozzle has a circular cross-sectional area has and concentric around the circular cylindrical Input section is arranged. So there is an in The circumferential direction of the input section is more uniform Gap space, which is an even distribution of the cooling fluid flow and therefore even cooling in this area allows.
  • a gas turbine with a combustor arrangement according to the previous Embodiments are also the subject of the invention.
  • Figure 1 is a section of a section a gas turbine with a combustion chamber arrangement according to the invention 1 shown.
  • the combustion chamber arrangement 1 settles together from a large number of individual combustion chambers 3, which are arranged like a wreath and in a common annular gap 13 flow out.
  • the annular gap 13 in turn opens into a turbine chamber 2, in which there are schematically indicated guide vanes and blades of the turbine.
  • Burners 6 are connected upstream of the individual combustion chambers 3. These serve to ignite a mixture of an oxygen-containing Fuel gas and a fuel, which in the Single combustion chambers 3 continue to burn.
  • the single combustion chambers 3 consist of one adjoining the burner 6 Input section 4 and an input section 4 in the direction of the annular gap 13 transition section 5 together.
  • the burners 6 are with the individual combustion chambers 3 connected through an outer turbine housing 7. Starting from the turbine outer casing 7 in the direction of Turbine space 2, a nozzle 8 can be recognized, which concentrically around the circular cylindrical input section 4 of the single combustion chamber 3 extends. Between the nozzle 8 and the input section 4 of the single combustion chamber 3, a gap 9 is left, which by one Cooling fluid can be flowed through.
  • the individual combustion chamber 3 are distributed along the circumference Ribs 10 are formed, with which the individual combustion chamber 3 is supported on the nozzle 8.
  • the ribs 10 are shown in FIG Embodiment molded onto the individual combustion chamber 3, however, they can also be molded onto the connector 8 and extend in the direction of the single combustion chamber 3.
  • a recess 11 can be seen on the side of the nozzle 8, at which an adjacent nozzle of an adjacent Single combustion chamber connects.
  • the individual combustion chambers 3 are to be transferred into a common annular gap 13 the individual combustion chambers at an angle to each other arranged.
  • the distance between the individual combustion chambers starting from the burner 6 in the direction of Annular gap 13 reduced, so that the cylindrical neck 8 from a certain extent in the direction of the annular gap 13 collide.
  • the recesses 11 arranged to further in the nozzle 8 To be able to extend the direction of the annular gap 13 inwards. Adjacent ones lie along the edge of the recesses 11 Stub 8 to each other and can be used to seal each other connected, for example welded.
  • the nozzles 8 arranged according to the invention form with their Gap space 9 a flow channel for a cooling fluid.
  • This in the cooling channel carries cooling fluid guided in a quasi closed manner due to the defined flow channel effectively one convective cooling of the individual combustion chambers 3 in the Nozzle 8 covered area.
  • FIGs 2 and 3 are perspective from different Viewing directions excerpts from trained according to the invention Combustion chamber arrangements shown.
  • the individual combustion chamber 3 at least in the input section 4 surrounding nozzle 8 with the tongue-like extension 12a and 12b shown.
  • Figure 2 is also with help arrows the course of the flow 14 of a coolant fluid from the openly cooled area towards the gap spaces below the tongue-like extensions 12a and shown below the nozzle 8.
  • the tongue-like extensions 12a and 12b towards the exit leading into the gap space from the transition section 5 of the individual combustion chambers 3 rejuvenate. This creates a sufficiently large entrance area guaranteed for the cooling fluid flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01121089A 2001-09-03 2001-09-03 Agencement de chambre de combustion Withdrawn EP1288574A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP01121089A EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion
PCT/EP2002/009556 WO2003021149A1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion
DE50207662T DE50207662D1 (de) 2001-09-03 2002-08-27 Brennkammeranordnung
JP2003525188A JP2005502020A (ja) 2001-09-03 2002-08-27 燃焼器装置
CNA028150961A CN1537212A (zh) 2001-09-03 2002-08-27 燃烧室装置
US10/488,622 US6968672B2 (en) 2001-09-03 2002-08-27 Collar for a combustion chamber of a gas turbine engine
EP02767441A EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01121089A EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion

Publications (1)

Publication Number Publication Date
EP1288574A1 true EP1288574A1 (fr) 2003-03-05

Family

ID=8178516

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01121089A Withdrawn EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion
EP02767441A Expired - Lifetime EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP02767441A Expired - Lifetime EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Country Status (6)

Country Link
US (1) US6968672B2 (fr)
EP (2) EP1288574A1 (fr)
JP (1) JP2005502020A (fr)
CN (1) CN1537212A (fr)
DE (1) DE50207662D1 (fr)
WO (1) WO2003021149A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7155800B2 (en) 2005-02-24 2007-01-02 General Electric Company Automated seal strip assembly method and apparatus for rotary machines
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
EP2211023A1 (fr) 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
US8201412B2 (en) * 2010-09-13 2012-06-19 General Electric Company Apparatus and method for cooling a combustor
DE102011007562A1 (de) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Brennkammergehäuse und damit ausgerüstete Gasturbine
US8650852B2 (en) * 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system
CN117090688B (zh) * 2023-08-29 2025-09-09 清航空天(北京)科技有限公司 一种浮动式爆震涡轮发动机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
US4794753A (en) * 1987-01-06 1989-01-03 General Electric Company Pressurized air support for catalytic reactor
US5323600A (en) * 1993-08-03 1994-06-28 General Electric Company Liner stop assembly for a combustor
US6216442B1 (en) * 1999-10-05 2001-04-17 General Electric Co. Supports for connecting a flow sleeve and a liner in a gas turbine combustor

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
US3840332A (en) * 1973-03-05 1974-10-08 Stone Platt Crawley Ltd Combustion chambers
GB1492049A (en) * 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPS59229114A (ja) * 1983-06-08 1984-12-22 Hitachi Ltd ガスタ−ビン用燃焼器
GB9220937D0 (en) * 1992-10-06 1992-11-18 Rolls Royce Plc Gas turbine engine combustor
FR2710968B1 (fr) * 1993-10-06 1995-11-03 Snecma Chambre de combustion à double paroi.
US6182451B1 (en) * 1994-09-14 2001-02-06 Alliedsignal Inc. Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor
US5737913A (en) * 1996-10-18 1998-04-14 The United States Of America As Represented By The Secretary Of The Air Force Self-aligning quick release engine case assembly
JP3110338B2 (ja) * 1997-02-12 2000-11-20 東北電力株式会社 燃焼器の蒸気による冷却構造
GB2328011A (en) * 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
DE19801626B4 (de) * 1998-01-17 2010-08-12 Robert Bosch Gmbh Diagnose eines NOx-Speicherkatalysators beim Betrieb von Verbrennungsmotoren
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
US6354071B2 (en) * 1998-09-25 2002-03-12 General Electric Company Measurement method for detecting and quantifying combustor dynamic pressures

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
US4794753A (en) * 1987-01-06 1989-01-03 General Electric Company Pressurized air support for catalytic reactor
US5323600A (en) * 1993-08-03 1994-06-28 General Electric Company Liner stop assembly for a combustor
US6216442B1 (en) * 1999-10-05 2001-04-17 General Electric Co. Supports for connecting a flow sleeve and a liner in a gas turbine combustor

Also Published As

Publication number Publication date
EP1423647A1 (fr) 2004-06-02
EP1423647B1 (fr) 2006-07-26
WO2003021149A1 (fr) 2003-03-13
JP2005502020A (ja) 2005-01-20
US20040237500A1 (en) 2004-12-02
DE50207662D1 (de) 2006-09-07
CN1537212A (zh) 2004-10-13
US6968672B2 (en) 2005-11-29

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