EP1431662B1 - Chambre de combustion de turbine avec système de refroidissement à circuit fermé - Google Patents

Chambre de combustion de turbine avec système de refroidissement à circuit fermé Download PDF

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Publication number
EP1431662B1
EP1431662B1 EP02028486A EP02028486A EP1431662B1 EP 1431662 B1 EP1431662 B1 EP 1431662B1 EP 02028486 A EP02028486 A EP 02028486A EP 02028486 A EP02028486 A EP 02028486A EP 1431662 B1 EP1431662 B1 EP 1431662B1
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EP
European Patent Office
Prior art keywords
combustion chamber
wall
cooling fluid
hollow tile
shell
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.)
Expired - Lifetime
Application number
EP02028486A
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German (de)
English (en)
Other versions
EP1431662A1 (fr
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
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE50212796T priority Critical patent/DE50212796D1/de
Priority to ES02028486T priority patent/ES2311046T3/es
Priority to EP02028486A priority patent/EP1431662B1/fr
Priority to CNB2003101188594A priority patent/CN100360851C/zh
Priority to US10/724,810 priority patent/US6925808B2/en
Priority to JP2003421132A priority patent/JP2004197748A/ja
Publication of EP1431662A1 publication Critical patent/EP1431662A1/fr
Application granted granted Critical
Publication of EP1431662B1 publication Critical patent/EP1431662B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M7/00—Doors
    • F23M7/04—Cooling doors or door frames
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a closed-cooled combustion chamber for a turbine.
  • Such combustion chambers are surrounded by a double wall having an inner wall and an outer wall, wherein a gap traversed by a cooling fluid, usually cooling air, is left between the inner wall and the outer wall.
  • a cooling fluid usually cooling air
  • the outer wall is often formed as a double-shell hollow tile, the hollow tile are formed by urgent, opening into the space between the outer wall and the inner wall cooling fluid supply tubes in the hollow tile.
  • the interrupted by the supply pipes, formed in the hollow tile cavity serves to dissipate the heated cooling fluid.
  • the cooling fluid is usually discharged in the interior of the hollow tile in the axial direction of the combustion chamber.
  • the problem with this construction is that the tubes formed with a circular cross-section and guided through the hollow tile with their walls intersecting the hollow tile obstruct the flow path for the outflowing cooling fluid and thus cause an increased flow resistance for the outflowing cooling fluid.
  • a closed-cooled combustion chamber according to the preamble of claim 1 is in US 5,737,922 disclosed.
  • the inlet structures are designed to supply the cooling fluid in the radial direction of the combustion chamber in such a way that, starting from the outer wall, they blend radially outwards from a round cross-section into an elongated opening cross-section.
  • the cooling fluid discharge in the axial direction of the combustion chamber extending, channel-like Ableit Modellen has, in which there are no flow obstacles, the cooling fluid in these Ableit Modellen without high Flow resistance to be dissipated.
  • the cooling fluid to be derived is channeled through the channel-like Ableit Modellen in the construction according to the invention and discharged at a constant radial extent of the combustion chamber with reduced flow resistance. This finally allows a reduction of the radial extent of the combustion chamber.
  • the outer wall is formed as a double-shell hollow tile and the Ableit Modellen inside the hollow tile are intermediate walls lined in the axial direction of the combustion chamber in a row, the hollow tile protruding guide tubes for supplying cooling fluid, wherein the guide tubes at least in the outer shell of the Hollow tile have an elongated opening in the axial direction of the combustion chamber opening cross-section.
  • the guide tubes in the outer shell of the hollow tile on an opening cross-section with elongated shape and in the inner shell of the hollow tile on a circular opening cross-section are provided.
  • the guide tubes in the arranged in the axial direction of the combustion chamber rows at least in the outer shell of the hollow tile with their narrow sides have a smaller distance from each other than the distance between the openings of adjacent rows. This embodiment achieves a further improved channeling of the outflowing cooling fluid in the channels formed between the rows.
  • the outer shell of the hollow tile has a releasably secured, preferably screwed, sealing plate which closes an opening through which a releasably secured, preferably screwed, section of the inner shell is accessible.
  • a required, for example, for maintenance and repair access to the combustion chamber enclosing the inner wall can be created in a simple manner. If a closable opening is also provided in this wall at the location of the access openings in the hollow tile, the interior of the combustion chamber is also accessible.
  • the solution of the sealing plate also brings the advantage that the provision of an opening in the double-shell hollow tile can be done without increased design complexity. This design is characterized by a small number of components, which can also be designed in the same way as the surrounding the opening rest of the hollow tile.
  • the discharge structures are formed by drainage channels formed on the outer wall and extending in the axial direction of the combustion chamber, between each of which the inlet structures are arranged.
  • this embodiment is used as the outer wall of the combustion chamber instead of a double-walled hollow tile a generally einschalige wall on the outside of individual, extending in the axial direction of the combustion chamber discharge channels are placed.
  • the production of such, in principle einschaligen outer wall is, since these parts are usually castings, much easier than in the case of hollow tile.
  • circular discharge openings formed in the outer wall open into the discharge channels.
  • circular discharge openings are arranged distributed over the outer wall.
  • the circular shape of the discharge is advantageous for flow reasons. Several circular discharge openings open into one of the discharge channels, in which the derived cooling fluid is collected and directed discharged.
  • the drainage channels are formed on the outer wall by means of covers placed on the outside of the outer wall and extending in the axial direction of the combustion chamber.
  • Such a two-part design of the discharge channels allows a further simplified production method of the outer wall. This can be made as a simple, single-shell casting. When casting only the ribs must be formed, the formation of cavities in the form of Ableitkanälen is not required. These are formed later by placing the covers.
  • the ribs may have structures for cross-section of circular openings on a linear channel at their base.
  • the outer wall is formed as a single-shell casting, and that the covers are welded onto the ribs.
  • Fig. 1 shows a first embodiment of an outer wall 1 of a combustion chamber according to the invention in a partial, three-dimensional representation.
  • the outer wall 1 is formed as a double-shell hollow tile. It has an outer shell 2 and an inner shell 3 pointing in the direction of the combustion chamber.
  • Guide tubes 4 connect the outer shell 2 and the inner shell 3 with each other for supplying a cooling fluid.
  • the guide tubes 4 have in the outer shell 2 elongated oval openings 5 and in the inner shell 3 circular openings 6.
  • the guide tubes 4 in the axial direction of the combustion chamber are lined up in succession, that the narrow end faces of the elongated oval openings 5 almost abut each other and that between the oval openings 5 of guide tubes 4 adjacent rows a greater distance than between the openings 5 remains in the rows ,
  • channel-like Ableit Scheme 8 are provided for discharging cooling fluid.
  • the cooling fluid to be discharged enters the cavity 9 from a gap (not shown) between the outer wall 1 and an inner wall (not shown) of the double-walled combustion chamber through openings 7. There it gets into the channel-like Ableit Scheme 8 and is selectively dissipated in the axial direction of the burner inside the outer wall formed as a hollow tile 1.
  • the guide tubes 4 Through the guide tubes 4, the walls of which fade from the oval opening 5 to a circular opening 6, fresh cooling fluid is passed into the space between the outer wall 1 and the inner wall, not shown. Due to the configuration and arrangement of the shown Guide tubes 4, the channel-like Ableit Weg 8 are formed in the interior of the hollow tile, which allow a flow resistance and directed discharge of cooling fluid. This allows a reduced expansion of the outer wall in the radial direction compared to known hollow tile variants, ie in the direction of the axial alignment of the guide tubes 4.
  • Fig. 2a and 2b is a possible further education in Fig. 1 shown outer wall shown.
  • a peripheral recess is formed in the outer shell 2 of the outer wall 1 designed as a hollow tile through which threaded bolts 14 are accessible.
  • a removable segment 15 is fixed to the rest of the outer wall formed as a hollow tile 1.
  • the recess 10 is closed by a screwed-on sealing plate 11.
  • the sealing plate 11 openings 13 passed through the bolts 12 and bolted to the outer shell 2.
  • the removable segment 15 has the same structure as the rest of the outer shell 1.
  • the outer wall 1 shown here is not formed as a hollow tile, but consists of a single-walled 20, which has in the axial direction of the combustion chamber extending ribs 21.
  • covers 22 are placed to form Ableitkanälen and welded to the ribs.
  • the discharge channels thus formed open into discharge openings 23, through which discharged cooling fluid emerges.
  • open openings 7 for discharging cooling fluid.
  • the ribs 21 are wave-shaped at their base for passing on the circular openings 6. In this way, between the Ableitkanälen entering cooling fluid in a wide area, shower-like penetrate into the space between the outer wall 1 and an inner wall, not shown.
  • this embodiment shown allows a reduced in the radial direction of the combustion chamber dimensioning of the outer wall, it also offers the advantage of ease of manufacture of the outer wall, since this is manufactured as a single-shell cast with ribs and the covers are welded to the ribs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Compositions Of Oxide Ceramics (AREA)

Claims (10)

  1. Chambre de combustion fermée et refroidie pour une turbine, comprenant une paroi intérieure délimitant l'espace de combustion et une paroi ( 1 ) extérieure, un espace intermédiaire dans lequel peut passer un fluide de refroidissement étant laissé entre la paroi intérieure et la paroi ( 1 ) extérieure, un conduit d'apport de fluide de refroidissement débouchant dans l'espace intermédiaire et un conduit d'évacuation de fluide de refroidissement pour évacuer le fluide de refroidissement hors de l'espace intermédiaire, le conduit d'évacuation du fluide de refroidissement ayant des structures ( 8 ; 21, 22 ) de dérivation en forme de canal s'étendant sensiblement le long de la direction axiale de la chambre de combustion, ces structures étant interrompues par des structures ( 4 ; 6 ) d'entrée du conduit d'apport de fluide de refroidissement disposées entre les structures ( 8 ; 21, 22 ) de dérivation, caractérisée en ce que les structures d'entrée pour l'apport du fluide de refroidissement sont formées dans la direction radiale de la chambre de combustion, de manière à ce qu'elles passent, en partant de la paroi ( 1 ) extérieure vers l'extérieur radialement, d'une section transversale circulaire à une section ( 5 ) transversale d'ouverture s'étendant en longueur.
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que la paroi ( 1 ) extérieure est constituée sous la forme d'un pot creux à double coquille et en ce que les structures ( 8 ) de dérivation sont formées à l'intérieur du pot creux entre des parois de tubes ( 4 ) pour l'apport de fluide de refroidissement, rangés les uns derrière les autres dans la direction axiale de la chambre de combustion et traversant le pot creux, les tubes ( 4 ) de guidage ayant au moins dans la coquille ( 2 ) extérieure du pot creux une section ( 5 ) transversale d'ouverture s'étendant en longueur dans la direction axiale de la chambre de combustion.
  3. Chambre de combustion suivant la revendication 2, caractérisée en ce que les tubes ( 4 ) de guidage ont, dans les rangées disposées dans la direction axiale de la chambre de combustion, au moins dans la coquille ( 2 ) extérieure du pot creux, par leurs petits côtés une moindre distance entre eux que la distance entre les ouvertures de rangées voisines.
  4. Chambre de combustion suivant l'une des revendications 2 ou 3, caractérisée en ce que les tubes ( 4 ) de guidage, dans la coquille ( 2 ) extérieure du pot creux, ont une section ( 5 ) transversale d'ouverture ayant une forme s'étendant en longueur et, dans la coquille ( 3 ) intérieure du pot creux, une section ( 6 ) transversale d'ouverture circulaire.
  5. Chambre de combustion suivant l'une des revendications 2 à 4, caractérisée en ce que la coquille ( 2 ) extérieure du pot creux a une tôle ( 11 ) d'étanchéité fixée de manière à amovible, de préférence vissée, qui ferme une ouverture ( 10 ) par laquelle une partie fixée de manière amovible, de préférence vissée, de la coquille intérieure est accessible.
  6. Chambre de combustion suivant la revendication 1, caractérisée en ce que les structures de dérivation sont formées par des canaux ( 21, 22 ) de dérivation qui sont formés sur la paroi ( 1 ) extérieure, qui s'étendent dans la direction axiale de la chambre de combustion et entre lesquels sont disposées respectivement les structures ( 6 ) d'entrée.
  7. Chambre de combustion suivant la revendication 6, caractérisée en ce que des ouvertures ( 7 ) de dérivation circulaires formées dans la paroi ( 1 ) extérieure débouchent dans les canaux ( 21, 22 ) de dérivation.
  8. Chambre de combustion suivant l'une des revendications 6 ou 7, caractérisée en ce que les canaux ( 21, 22 ) de dérivation sont formés sur la paroi ( 1 ) extérieure par des recouvrements ( 22 ) formés sur la face extérieure de la paroi ( 1 ) extérieure et mis sur des nervures ( 21 ) s'étendant dans la direction axiale de la chambre de combustion.
  9. Chambre de combustion suivant la revendication 8, caractérisée en ce que les nervures ( 21 ) ont, à leur base ( 24 ), des structures de passage d'ouvertures ( 6 ) circulaires à un canal linéaire.
  10. Chambre de combustion suivant l'une des revendications 8 ou 9, caractérisée en ce que la paroi ( 1 ) extérieure est formée d'une pièce coulée en une seule coquille et en ce que les recouvrements ( 22 ) sont soudés aux nervures ( 21 ).
EP02028486A 2002-12-19 2002-12-19 Chambre de combustion de turbine avec système de refroidissement à circuit fermé Expired - Lifetime EP1431662B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50212796T DE50212796D1 (de) 2002-12-19 2002-12-19 Geschlossen gekühlte Brennkammer für eine Turbine
ES02028486T ES2311046T3 (es) 2002-12-19 2002-12-19 Camara de combustion cerrada refrigerada para una turbina.
EP02028486A EP1431662B1 (fr) 2002-12-19 2002-12-19 Chambre de combustion de turbine avec système de refroidissement à circuit fermé
CNB2003101188594A CN100360851C (zh) 2002-12-19 2003-11-28 用于透平机的封闭式冷却的燃烧室
US10/724,810 US6925808B2 (en) 2002-12-19 2003-12-01 Combustion chamber with a closed cooling system for a turbine
JP2003421132A JP2004197748A (ja) 2002-12-19 2003-12-18 タービンにおける密閉冷却形燃焼器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02028486A EP1431662B1 (fr) 2002-12-19 2002-12-19 Chambre de combustion de turbine avec système de refroidissement à circuit fermé

Publications (2)

Publication Number Publication Date
EP1431662A1 EP1431662A1 (fr) 2004-06-23
EP1431662B1 true EP1431662B1 (fr) 2008-09-17

Family

ID=32338050

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02028486A Expired - Lifetime EP1431662B1 (fr) 2002-12-19 2002-12-19 Chambre de combustion de turbine avec système de refroidissement à circuit fermé

Country Status (6)

Country Link
US (1) US6925808B2 (fr)
EP (1) EP1431662B1 (fr)
JP (1) JP2004197748A (fr)
CN (1) CN100360851C (fr)
DE (1) DE50212796D1 (fr)
ES (1) ES2311046T3 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US20080072566A1 (en) * 2006-09-27 2008-03-27 Pratt & Whitney Canada Corp. Bleed holes oriented with gaspath and flared for noise reduction
US8522557B2 (en) * 2006-12-21 2013-09-03 Siemens Aktiengesellschaft Cooling channel for cooling a hot gas guiding component
EP2116770B1 (fr) * 2008-05-07 2013-12-04 Siemens Aktiengesellschaft Atténuation dynamique de chambre de combustion et agencement de refroidissement
US8166764B2 (en) * 2008-07-21 2012-05-01 United Technologies Corporation Flow sleeve impingement cooling using a plenum ring
US8291711B2 (en) 2008-07-25 2012-10-23 United Technologies Corporation Flow sleeve impingement cooling baffles
US9603629B2 (en) * 2008-09-09 2017-03-28 Intelligent Implant Systems Llc Polyaxial screw assembly
US9085981B2 (en) 2012-10-19 2015-07-21 Siemens Energy, Inc. Ducting arrangement for cooling a gas turbine structure
KR101556532B1 (ko) * 2014-01-16 2015-10-01 두산중공업 주식회사 냉각슬리브를 포함하는 라이너, 플로우슬리브 및 가스터빈연소기
GB201501971D0 (en) 2015-02-06 2015-03-25 Rolls Royce Plc A combustion chamber
US20180066539A1 (en) * 2016-09-06 2018-03-08 United Technologies Corporation Impingement cooling with increased cross-flow area
US10935243B2 (en) * 2016-11-30 2021-03-02 Raytheon Technologies Corporation Regulated combustor liner panel for a gas turbine engine combustor
US11346253B2 (en) * 2019-03-22 2022-05-31 Raytheon Technologies Corporation Liner apparatus and method of inspecting and/or cleaning a liner annular region
CN114233516B (zh) * 2021-12-23 2023-05-09 南京航空航天大学 一种具有再生冷却功能的复合材料爆震发动机燃烧室结构

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
JP3415663B2 (ja) * 1992-12-28 2003-06-09 アルストム 冷却面を衝撃式に冷却するための装置
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US5737922A (en) * 1995-01-30 1998-04-14 Aerojet General Corporation Convectively cooled liner for a combustor
DE19809568A1 (de) * 1998-03-05 1999-08-19 Siemens Ag Ringbrennkammer, Verwendung einer Ringbrennkammer und Einsatz für eine Öffnung in einer Brennkammer
SE9801822L (sv) * 1998-05-25 1999-11-26 Abb Ab Förbränningsanordning
US6384373B1 (en) * 2000-10-03 2002-05-07 Illinois Tool Works Welding power supply having improved supplemental power circuit
US6388232B1 (en) * 2000-11-27 2002-05-14 Lincoln Global, Inc. Starting and welding device for DC TIG welder and method of operating same
EP1271056A1 (fr) * 2001-06-20 2003-01-02 Siemens Aktiengesellschaft Chambre de combustion de turbine à gaz et méthode pour y amener de l'air

Also Published As

Publication number Publication date
CN100360851C (zh) 2008-01-09
US6925808B2 (en) 2005-08-09
DE50212796D1 (de) 2008-10-30
CN1510251A (zh) 2004-07-07
EP1431662A1 (fr) 2004-06-23
US20040118123A1 (en) 2004-06-24
ES2311046T3 (es) 2009-02-01
JP2004197748A (ja) 2004-07-15

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