EP2402659A1 - Coque extérieure pour chambre de combustion - Google Patents

Coque extérieure pour chambre de combustion Download PDF

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Publication number
EP2402659A1
EP2402659A1 EP10168147A EP10168147A EP2402659A1 EP 2402659 A1 EP2402659 A1 EP 2402659A1 EP 10168147 A EP10168147 A EP 10168147A EP 10168147 A EP10168147 A EP 10168147A EP 2402659 A1 EP2402659 A1 EP 2402659A1
Authority
EP
European Patent Office
Prior art keywords
outer shell
combustion chamber
chamber outer
connection
axial direction
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Withdrawn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
EP10168147A
Other languages
German (de)
English (en)
Inventor
Thomas Brandenburg
Olga Deiss
Giuseppe Gaio
Jens Kleinfeld
Andre Kluge
Thomas Alexis Schneider
Christian Scholz
Sabine Tüschen
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 EP10168147A priority Critical patent/EP2402659A1/fr
Publication of EP2402659A1 publication Critical patent/EP2402659A1/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Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to a combustion chamber outer shell.
  • Gas turbines have a combustion chamber with a combustion chamber outer shell.
  • a combustion chamber outer shell may be a combustion chamber upper shell and a lower combustion chamber shell.
  • the combustion chamber outer shell has been manufactured in one piece.
  • the combustion chamber outer shell of a gas turbine is fixed in the axial direction on a turbine vane support, which carries the vanes.
  • the axial fixation is realized by a tongue and groove connection (entanglement), wherein the groove is arranged in the combustion chamber outer shell. If there is a wear-related reduction in the hook wall thickness, there is a risk that component integrity will no longer be guaranteed. As a result, the security of the connection is no longer guaranteed. Thus, costly repairs are necessary, up to the exchange of the entire outer shell. Especially the latter is associated with downtime and high maintenance costs.
  • the object of the present invention is therefore to specify a combustion chamber outer shell for a gas turbine, which avoids the above disadvantages.
  • the object is achieved by specifying a combustion chamber outer shell according to claim 1.
  • connection is a flange connection.
  • This is advantageously screwed or releasably joined.
  • a flange, which is screwed or detachably joined, is particularly in a combustion chamber an advantageous connection, since it is very heat resistant.
  • the combustion chamber outer shell is equipped in the axial direction with heat shields, which are arranged at once uniformly spaced on the inside of the combustion chamber outer shell due to the hot gases.
  • the heat shield can also be a heat shield row.
  • the connection of the combustion chamber outer shell is provided in the axial direction immediately before the last heat shield, the last heat shield facing the turbine vane support out.
  • two combustion chamber shell outer parts namely one which extends from the first heat shield to the fifth heat shield inclusive, hereinafter referred to as the first combustion chamber outer shell part and one which extends only from the sixth heat shield to the end of the outer shell, ie the turbine vane support (second combustion chamber outer shell part).
  • a gas turbine has inside a rotor rotatably mounted about a rotation axis with a shaft, which is also referred to as a turbine runner.
  • the gas turbine has an axial direction A.
  • an intake housing Along the rotor follow one another an intake housing, a compressor, an example toroidal annular combustion chamber with a plurality of coaxially arranged burners, a turbine and the exhaust housing.
  • the annular combustion chamber communicates with an annular hot gas channel, for example.
  • the combustion chamber has a combustion chamber outer shell. When viewed in the axial direction, the turbine outer shell is followed by a turbine guide vane carrier 30.
  • the outer shell consists in the axial direction of different, arranged at almost equal intervals, heat shields 5,6;
  • the heat shields 5 and 6 may also be heat shield rows, which are arranged perpendicular to the axial direction.
  • these are six heat shields, with only the last two heat shields 5, 6 being shown for reasons of drawing.
  • This combustion chamber outer shell is axially fixed to the turbine vane support 30.
  • the axial fixation is realized by a tongue and groove connection 50.
  • the spring consisting of ring segments, is screwed to the turbine guide vane carrier 30 and engages from the outside into the groove located in the outer shell.
  • the fit between the tongue and groove secures the axial position of the outer shell to the turbine vane support 30.
  • the groove of the outer shell is over-turned. There is a risk that the component integrity is no longer guaranteed. As a result, costly repairs are necessary, up to the exchange of the entire outer shell. Especially the latter is associated with downtime and high maintenance costs.
  • the outer shell is divided into a first combustion chamber outer shell part 15 and a second combustion chamber outer shell part 10.
  • the second combustion chamber outer shell part 10 adjoins the turbine guide vane carrier 30.
  • the two outer shell parts 15, 10 are fastened to one another via a flange connection 60.
  • the flange 60 may be screwed or otherwise releasably joined.
  • the outer shell is in particular divided between the fifth heat shield 5 and the sixth heat shield 6. This results in a particularly small second combustion chamber outer shell part in its dimensions 10. Since especially the second combustion chamber outer shell part 10 because of the adjacent Turbinenleitschaufelani 30 tends to wear, so a particularly simple and cost-effective replacement of this second combustion chamber outer shell part 10 is possible. Thus, material costs can be saved. However, the outer shell can also be shared between other heat shields.

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)
EP10168147A 2010-07-01 2010-07-01 Coque extérieure pour chambre de combustion Withdrawn EP2402659A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10168147A EP2402659A1 (fr) 2010-07-01 2010-07-01 Coque extérieure pour chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10168147A EP2402659A1 (fr) 2010-07-01 2010-07-01 Coque extérieure pour chambre de combustion

Publications (1)

Publication Number Publication Date
EP2402659A1 true EP2402659A1 (fr) 2012-01-04

Family

ID=43383535

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10168147A Withdrawn EP2402659A1 (fr) 2010-07-01 2010-07-01 Coque extérieure pour chambre de combustion

Country Status (1)

Country Link
EP (1) EP2402659A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2634372A1 (fr) * 2012-03-02 2013-09-04 General Electric Company Agencement de cadre arrière de pièce de transition avec bouclier thermique et système associé de combustion
EP2918913A1 (fr) * 2014-03-11 2015-09-16 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion d'une turbine à gaz
US9335048B2 (en) 2014-03-11 2016-05-10 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1744014A1 (fr) * 2005-07-13 2007-01-17 Siemens Aktiengesellschaft Agencement de montage des aubes d'entrée d'une turbine à gaz
EP1767835A1 (fr) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Dispositif d'étanchéité résistant aux hautes températures, en particulier pour turbines à gaz
US20090260364A1 (en) * 2008-04-16 2009-10-22 Siemens Power Generation, Inc. Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1744014A1 (fr) * 2005-07-13 2007-01-17 Siemens Aktiengesellschaft Agencement de montage des aubes d'entrée d'une turbine à gaz
EP1767835A1 (fr) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Dispositif d'étanchéité résistant aux hautes températures, en particulier pour turbines à gaz
US20090260364A1 (en) * 2008-04-16 2009-10-22 Siemens Power Generation, Inc. Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2634372A1 (fr) * 2012-03-02 2013-09-04 General Electric Company Agencement de cadre arrière de pièce de transition avec bouclier thermique et système associé de combustion
CN103291457A (zh) * 2012-03-02 2013-09-11 通用电气公司 具有热护罩的过渡连接件后架组件
US9010127B2 (en) 2012-03-02 2015-04-21 General Electric Company Transition piece aft frame assembly having a heat shield
CN103291457B (zh) * 2012-03-02 2017-03-01 通用电气公司 具有热护罩的过渡连接件后架组件
EP2918913A1 (fr) * 2014-03-11 2015-09-16 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion d'une turbine à gaz
US9335048B2 (en) 2014-03-11 2016-05-10 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine
US9506653B2 (en) 2014-03-11 2016-11-29 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine

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