EP2487417B1 - Boîtier de chambre de combustion - Google Patents

Boîtier de chambre de combustion Download PDF

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Publication number
EP2487417B1
EP2487417B1 EP11153769.2A EP11153769A EP2487417B1 EP 2487417 B1 EP2487417 B1 EP 2487417B1 EP 11153769 A EP11153769 A EP 11153769A EP 2487417 B1 EP2487417 B1 EP 2487417B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shell
wear
outer shell
projection
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.)
Active
Application number
EP11153769.2A
Other languages
German (de)
English (en)
Other versions
EP2487417A1 (fr
Inventor
Andreas Dr. Böttcher
Christopher Grandt
Thomas Kunadt
Wilhelm Scheidtmann
Holger Streb
Daniel Vogtmann
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 EP11153769.2A priority Critical patent/EP2487417B1/fr
Priority to HUE11153769A priority patent/HUE027667T2/en
Priority to CN201210026875.XA priority patent/CN102635875B/zh
Priority to RU2012104494/06A priority patent/RU2583327C2/ru
Publication of EP2487417A1 publication Critical patent/EP2487417A1/fr
Application granted granted Critical
Publication of EP2487417B1 publication Critical patent/EP2487417B1/fr
Active 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
    • F23R3/002—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
    • F23R3/50—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
    • F23R3/42—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
    • 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
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a combustion chamber housing which is formed by a combustion chamber outer shell with a shell interior and a combustion chamber inner shell with a shell interior.
  • a gas turbine has a rotor rotatably mounted about a rotation axis with a shaft.
  • a rotor rotatably mounted about a rotation axis with a shaft.
  • an intake housing a compressor
  • a combustion chamber for example an annular combustion chamber
  • a combustion chamber housing for guiding hot gas and with a plurality of coaxially arranged burners
  • a turbine and an exhaust housing.
  • the combustion chamber housing is formed by an annular combustion chamber outer shell and a combustion chamber inner shell.
  • these L-rings tend in operation to strong scaling.
  • wear between the L-rings and the Brennschau- ⁇ enschale or the combustion chamber inner shell takes place.
  • the pressure plate is also characterized by high susceptibility to wear and thus short life. Due to the high wear, therefore, the sealing plate with the L-rings on the combustion chamber housing must be frequently replaced. The assembly of these components on the combustion chamber housing is very tedious and very difficult.
  • Such a construction is for example from the document EP 1 312 865 A known.
  • the object of the invention is to provide a combustion chamber housing which avoids the disadvantages described above.
  • Combustor inner shell is formed with a shell interior, the combustion chamber outer shell and the inner combustion chamber each having an open, continuous, circumferential recess to the shell interior, wherein in these recesses, a two-part wear strip is provided, wherein the wear strip with the combustion chamber outer shell and the combustion chamber inner shell is detachably connected, the following is achieved:
  • the wear strip consists of a first wear ring and a second wear ring, wherein the first wear ring has a projection, and the second wear ring has a groove corresponding to the projection, so that the projection can be introduced into the groove, and the projection thereby fixable in the groove is.
  • combustion chamber inner shell and combustion chamber outer shell can be easily positioned in the assembly and connected because they can be centered by the projection and the groove easy to each other (self-centering connection).
  • a Dehnspalte is provided between the projection and the groove corresponding to the projection. As a result, temperature-induced expansions of the material can be better compensated.
  • the first wear ring is provided in the recess belonging to the combustion chamber outer shell, wherein the first wear ring is bolted to the combustion chamber outer shell and the second wear ring in the recess belonging to the combustion chamber inner shell, wherein the second wear ring bolted to the combustion chamber inner shell.
  • the first wear ring is provided in the recess belonging to the combustion chamber inner shell, wherein the first wear ring is bolted to the combustion chamber inner shell and the second wear ring in the recess belonging to the combustion chamber outer shell, wherein the second wear ring is bolted to the combustion chamber outer shell.
  • a gas turbine comprises a combustion chamber housing according to the invention.
  • a gas turbine plant 1 according to FIG. 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator, not shown.
  • the combustion chamber 4 is provided with a number of Burners 10 equipped for the combustion of a liquid or gaseous fuel. It also has a combustion chamber outer shell 20 and a combustion chamber inner shell 30, also called hub on.
  • the turbine 6 has a number of rotatable blades 12.
  • the rotor blades 6 serve to drive the turbine shaft 8 by momentum transfer from the turbine 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two in the flow direction of the working medium M. seen consecutive blade rows or blade rings.
  • the invention relates to the area designated 11 and is in the FIGS. 2 and 3 described.
  • Fig. 2 1 shows a detail of a combustion chamber outer shell 20 with a shell interior and a combustion chamber inner shell 30 with a shell interior.
  • the combustion chamber outer shell 20 and the combustion chamber inner shell 30 have open to one end face 5, continuous, circumferential recesses 27,37, which point to the shell interior.
  • a wear strip is provided in this recess 27,37 .
  • the wear strip consists of a first wear ring 25 and a second wear ring 35.
  • the first wear ring 25 has a projection 26, while the second wear ring 35 has a groove 36 corresponding to the projection 26.
  • the projection 26 can be introduced into the groove 36.
  • the projection 26 slips into the groove 36, so that a centering of the combustion chamber outer shell 20 takes place to the combustion chamber inner shell 30.
  • This simplified centering saves a lot of assembly time.
  • the protrusion 26 with the groove 36 fixes the combustion chamber outer shell 20 to the combustion chamber inner shell 30 during operation.
  • the wear strip 25 is attached with screws 40 in the recess 27 of the combustion chamber outer shell 20 that is open to the front side 5.
  • the wear strip 35 is also with screws 40 in the for End face 5 open recess 37 of the combustion chamber inner shell 30 is attached. Instead of screws 40 can also be used any other releasable connection.
  • the screws 40 can be loosened and the wear rings 25, 35 exchanged.
  • the wear rings 25 and 35 can be easily removed in the event of wear.
  • the wear rings 25 and 35 can have a large amount of material in their thickness and length, so that the wear rings 25 and 35 have a long service life.
  • the wear now also takes place only in the two wear rings 25 and 35 and no longer, as in the prior art, between the L-rings and the combustion chamber outer shell 20 and the combustion chamber inner shell 30. This also increases the life of the combustion chamber outer shell 20 and Combustor inner shell 30.
  • Between the projection 26 and the groove 36 may be an expansion column 41, which compensates for thermal expansion during operation.
  • FIG. 3 shows a detail of the end face 5 of a combustion chamber housing according to the invention.
  • Screws 40 are distributed equidistantly over the wear ring 25, as well as screws 40 are equidistantly distributed over the wear ring 35.
  • the screws 40 of the first wear ring 25 can be arranged offset to the screws 40 of the second wear ring 35.
  • any other releasable connections can be used.

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)
  • Solid-Fuel Combustion (AREA)
  • Gasket Seals (AREA)

Claims (6)

  1. Enveloppe de chambre de combustion, qui est formée d'une coque ( 20 ) extérieure de chambre de combustion ayant un intérieur de coque et d'une coque ( 30 ) intérieure de combustion ayant un intérieur de coque,
    caractérisée en ce que la coque ( 20 ) extérieure de chambre de combustion et la coque ( 30 ) intérieure de chambre de combustion ont respectivement, par rapport à l'intérieur de la coque, un évidement ( 27, 37 ) faisant le tour, continu et ouvert vers un côté ( 5 ) frontal, une baguette d'usure en deux parties étant prévue dans ces évidements ( 27, 37 ), la baguette d'usure étant reliée de manière amovible à la fois à la coque ( 20 ) extérieure de la chambre de combustion et à la coque ( 30 ) intérieure de la chambre de combustion.
  2. Enveloppe de chambre de combustion suivant la revendication 1,
    caractérisée en ce que la baguette d'usure est constituée d'une première bague ( 25 ) d'usure et d'une deuxième bague ( 35 ) d'usure, la première bague ( 25 ) d'usure ayant une saillie ( 26 ) et la deuxième bague ( 35 ) d'usure ayant une rainure correspondante à la saille ( 26 ), de manière à pouvoir introduire la saillie ( 26 ) dans la rainure ( 36 ) et à immobiliser ainsi la saillie ( 26 ) dans la rainure ( 36 ).
  3. Enveloppe de chambre de combustion suivant la revendication 2,
    caractérisée en ce qu'il est prévu une fente ( 41 ) de dilatation entre la saillie ( 26 ) et la rainure ( 36 ) correspondante à la saillie ( 26 ).
  4. Enveloppe de chambre de combustion suivant la revendication 2 ou 3,
    caractérisée en ce que la première bague ( 25 ) d'usure est prévue dans l'évidement ( 27 ) appartenant à la coque ( 20 ) extérieure de la chambre de combustion et la première bague ( 25 ) d'usure est vissée à la coque ( 20 ) extérieure de la chambre de combustion et la deuxième bague ( 35 ) d'usure est prévue dans l'évidement appartenant à la coque ( 30 ) intérieure de la chambre de combustion et la deuxième bague ( 35 ) d'usure est vissée à la coque ( 30 ) intérieure de la chambre de combustion.
  5. Enveloppe de chambre de combustion suivant la revendication 2 ou 3,
    caractérisée en ce que la première bague ( 25 ) d'usure est prévue dans l'évidement ( 37 ) appartenant à la coque ( 30 ) intérieure de la chambre de combustion et la première bague ( 25 ) d'usure est vissée à la coque ( 30 ) intérieure de la chambre de combustion et la deuxième bague ( 35 ) d'usure est prévue dans l'évidement ( 27 ) appartenant à la coque ( 20 ) extérieure de la chambre de combustion et la deuxième bague ( 35 ) d'usure est vissée à la coque ( 20 ) extérieure de la chambre de combustion.
  6. Turbine à gaz ayant une enveloppe de chambre de combustion suivant l'une des revendications précédentes.
EP11153769.2A 2011-02-09 2011-02-09 Boîtier de chambre de combustion Active EP2487417B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP11153769.2A EP2487417B1 (fr) 2011-02-09 2011-02-09 Boîtier de chambre de combustion
HUE11153769A HUE027667T2 (en) 2011-02-09 2011-02-09 Burner compartment cover
CN201210026875.XA CN102635875B (zh) 2011-02-09 2012-02-08 燃烧室机匣
RU2012104494/06A RU2583327C2 (ru) 2011-02-09 2012-02-08 Корпус камеры сгорания

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11153769.2A EP2487417B1 (fr) 2011-02-09 2011-02-09 Boîtier de chambre de combustion

Publications (2)

Publication Number Publication Date
EP2487417A1 EP2487417A1 (fr) 2012-08-15
EP2487417B1 true EP2487417B1 (fr) 2015-07-15

Family

ID=44146266

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11153769.2A Active EP2487417B1 (fr) 2011-02-09 2011-02-09 Boîtier de chambre de combustion

Country Status (4)

Country Link
EP (1) EP2487417B1 (fr)
CN (1) CN102635875B (fr)
HU (1) HUE027667T2 (fr)
RU (1) RU2583327C2 (fr)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB892890A (en) * 1958-11-25 1962-04-04 Joseph Thompson Purvis Annular combustion chamber reinforcing means
ES2126881T3 (es) * 1994-01-24 1999-04-01 Siemens Ag Camara de combustion para una turbina de gas.
EP1312865A1 (fr) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Chambre de combustion annulaire de turbine à gaz
EP1473517A1 (fr) * 2003-04-30 2004-11-03 Siemens Aktiengesellschaft Chambre de combustion
EP1521018A1 (fr) * 2003-10-02 2005-04-06 ALSTOM Technology Ltd Joint d'étanchéité haute températures
US20070119052A1 (en) * 2005-11-28 2007-05-31 General Electric Company Combustor dome repair method
FR2897923B1 (fr) * 2006-02-27 2008-06-06 Snecma Sa Chambre de combustion annulaire a fond amovible
RU2315911C1 (ru) * 2006-06-07 2008-01-27 Михаил Иванович Весенгириев Кольцевая камера сгорания газотурбинного двигателя
FR2906350B1 (fr) * 2006-09-22 2009-03-20 Snecma Sa Chambre de combustion annulaire d'une turbomachine
US7909300B2 (en) * 2007-10-18 2011-03-22 General Electric Company Combustor bracket assembly
US7874138B2 (en) * 2008-09-11 2011-01-25 Siemens Energy, Inc. Segmented annular combustor
US8327648B2 (en) * 2008-12-09 2012-12-11 Pratt & Whitney Canada Corp. Combustor liner with integrated anti-rotation and removal feature

Also Published As

Publication number Publication date
RU2012104494A (ru) 2013-08-20
HUE027667T2 (en) 2016-10-28
EP2487417A1 (fr) 2012-08-15
CN102635875B (zh) 2016-05-04
CN102635875A (zh) 2012-08-15
RU2583327C2 (ru) 2016-05-10

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