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EP1431662A1 - 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
EP1431662A1
EP1431662A1 EP02028486A EP02028486A EP1431662A1 EP 1431662 A1 EP1431662 A1 EP 1431662A1 EP 02028486 A EP02028486 A EP 02028486A EP 02028486 A EP02028486 A EP 02028486A EP 1431662 A1 EP1431662 A1 EP 1431662A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
cooling fluid
discharge
hollow tile
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.)
Granted
Application number
EP02028486A
Other languages
German (de)
English (en)
Other versions
EP1431662B1 (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
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 ES02028486T priority Critical patent/ES2311046T3/es
Priority to EP02028486A priority patent/EP1431662B1/fr
Priority to DE50212796T priority patent/DE50212796D1/de
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 of an inner wall and surround an outer wall having a double wall, wherein one with one between the inner wall and the outer wall Cooling fluid, usually cooling air, more flowable Space is left.
  • a cooling fluid usually cooling air
  • the outer wall is often double-shelled Hollow tile formed, the hollow tile by urgent, in the space between the outer wall and the Cooling fluid supply pipes opening into the inner wall Hollow tile are formed. The one through the feed pipes interrupted cavity formed in the hollow tile is used to discharge the heated cooling fluid.
  • a closed-cooled combustor for a turbine with a combustion chamber defining inner wall and an outer wall, wherein a through-flow with a cooling fluid space is left between the inner wall and the outer wall, with an opening into the space the cooling fluid supply and a cooling fluid discharge for discharging the cooling fluid from the intermediate space, wherein the cooling fluid discharge has channel-like discharge structures running essentially along the axial alignment of the combustion chamber, which are interrupted by inlet structures of the cooling fluid supply arranged between the discharge structures.
  • the combustion chamber is the outer wall as a double-shell Hollow tile formed and the discharge structures inside the hollow tile are intermediate walls in the axial direction lined up in the combustion chamber, the hollow tile outstanding guide tubes for the supply of cooling fluid formed, the guide tubes at least in the Outer shell of the hollow tile one in the axial direction Combustion chamber have elongated opening cross-section.
  • the guide tubes in the axial direction the rows arranged at least in the combustion chamber Outer shell of the hollow tile with its narrow sides have a smaller distance from one another than the distance from Openings in adjacent rows.
  • This configuration will a further improved channeling of the outflow Cooling fluids in the channels formed between the rows achieved.
  • the guide tubes in the outer shell of the Hollow tile an opening cross-section with an elongated shape and a circular one in the inner shell of the hollow tile Have opening cross-section.
  • the advantage of the channel-like discharge structure achieved for the cooling fluid on the other hand, that for the Supply of cooling fluid favorable circular shape in the Maintain gap opening opening of the guide tube.
  • the guide tube is along its axial extent shaped so that it is avoiding an elevated Flow resistance from the elongated "slot shape" the opening in the outer shell of the hollow tile to the circular opening in the inner shell of the hollow tile superimposed.
  • the outer shell of the Hollow tile a detachably fastened, preferably screwed, sealing plate, which has an opening closes, through which a detachably fastened, preferably screwed, section of the inner shell is accessible.
  • a detachably fastened, preferably screwed, section of the inner shell is accessible.
  • This construction can be a simple one for example for maintenance and repair purposes required access to the one surrounding the combustion chamber Inner wall can be created. Is also on in this wall the location of the access openings in the hollow tile closable opening attached, is also the inside of the Combustion chamber accessible.
  • the solution of the sealing plate brings furthermore the advantage that the provision of an opening in the double-shell hollow tile without increased structural Effort can be made.
  • This construction is characterized by a small number of components that go beyond that can be designed in exactly the same way as the one surrounding the opening Rest of the hollow tile.
  • the derivation structures by the outer wall, formed in the axial direction of the Combustion chamber-extending discharge channels are formed between which are each arranged the inlet structures.
  • the outer wall of the Combustion chamber instead of a double-walled hollow tile generally single-walled wall used on the outside individual, extending in the axial direction of the combustion chamber Discharge channels are attached.
  • the making of one, is basically single-shell outer wall, since it is these parts are usually cast parts, clearly easier than in the case of the hollow tile.
  • this second embodiment provided that circular formed in the outer wall Discharge openings open into the discharge channels. To derive the the gap between the outer wall and the inner wall leaving cooling fluids are distributed over the outer wall circular discharge openings arranged.
  • the circular shape of the Discharge openings is of fluidic reasons from Advantage. Several circular discharge openings open into one the discharge channels in which the derived cooling fluid is collected and directed away.
  • the discharge channels on the Outer wall by on the outside of the outer wall trained, extending in the axial direction of the combustion chamber Ribs covers are formed.
  • a two-part design of the discharge channels still allows further simplified manufacturing process of the outer wall. This can be made as a simple, single-shell cast part become.
  • the ribs need to be formed the formation of cavities in the form of Discharge channels are not required. These are only later formed by putting on the covers.
  • the ribs can be on their base structures for blending circular Have openings on a linear channel.
  • the Outer wall 1 shows a first embodiment of an outer wall 1 a combustion chamber according to the invention in a detail, three-dimensional representation.
  • the Outer wall 1 is designed as a double-shell hollow tile. It has an outer shell 2 and one in the direction of Combustion chamber facing inner shell 3.
  • Guide tubes 4 connect the outer shell 2 and the inner shell 3 together for supplying a cooling fluid.
  • the guide tubes 4 point 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 lined up in a row that the narrow end faces of the elongated oval openings 5 almost meet and that between the oval openings 5 of guide tubes 4th adjacent rows a greater distance than between the Openings 5 remain in the rows.
  • Cooling fluid exits a space (not shown) between the outer wall 1 and a (not shown) Inner wall of the double-walled combustion chamber through openings 7 into the cavity 9. There it gets into the channel-like Diverter structures 8 and is targeted in the axial direction of the Brenner inside the hollow tile Outer wall 1 removed.
  • FIG. 1 shown outer wall.
  • a so-called manhole is in the outer shell 2 formed as a hollow tile outer wall 1 a circumferential Recess formed through which bolts 14 are accessible.
  • the bolts 14 With the bolts 14 is a removable segment 15 on the rest of the as a hollow tile trained outer wall 1 fixed.
  • the recess 10 through a screwed sealing plate 11 closed.
  • the sealing plate 11 has openings 13 on, passed through the bolts 12 and with the Outer shell 2 are screwed.
  • the removable segment 15 is structurally the same as the rest of the Outer shell 1.
  • the outer wall 1 shown here is not designed as a hollow tile, but consists of one single-shell wall 20, which in the axial direction of the Combustion chamber extending ribs 21.
  • covers 22 are placed to form discharge channels and welded to the ribs.
  • the so educated Discharge channels open into discharge openings 23 through which derived cooling fluid emerges.
  • openings 7 for draining cooling fluid.
  • the area between the ribs 21, not of covers 22 to form Discharge channels are covered, contains circular openings 6 for supplying cooling fluid.
  • the ribs 21 are at their base for transferring the circular openings 6 are wave-shaped. To this In this way, cooling fluid entering between the discharge channels can in a wide area, not shower-like in the shown space between the outer wall 1 and one Penetrate inner wall.
  • This embodiment shown also enables an in radial dimension of the combustion chamber reduced dimensioning the outer wall, it also offers the advantage of a easy manufacture of the outer wall, as this single-shell cast part with ribs is made and on the Ribs the covers are welded on.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Compositions Of Oxide Ceramics (AREA)
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
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
DE50212796T DE50212796D1 (de) 2002-12-19 2002-12-19 Geschlossen gekühlte Brennkammer für eine Turbine
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 true EP1431662A1 (fr) 2004-06-23
EP1431662B1 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114233516A (zh) * 2021-12-23 2022-03-25 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

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
CN113551258B (zh) * 2021-08-31 2025-02-11 西北工业大学 用于发动机燃烧室的桁架式双层壁隔热装置及冷气膜形成方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
US5467815A (en) * 1992-12-28 1995-11-21 Abb Research Ltd. Apparatus for impingement cooling
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
WO1999061841A1 (fr) * 1998-05-25 1999-12-02 Asea Brown Boveri Ab Systeme de refroidissement destine a une chambre de combustion
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

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5467815A (en) * 1992-12-28 1995-11-21 Abb Research Ltd. Apparatus for impingement cooling
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
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
WO1999061841A1 (fr) * 1998-05-25 1999-12-02 Asea Brown Boveri Ab Systeme de refroidissement destine a une chambre de combustion
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114233516A (zh) * 2021-12-23 2022-03-25 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
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

Also Published As

Publication number Publication date
CN1510251A (zh) 2004-07-07
ES2311046T3 (es) 2009-02-01
JP2004197748A (ja) 2004-07-15
US20040118123A1 (en) 2004-06-24
DE50212796D1 (de) 2008-10-30
CN100360851C (zh) 2008-01-09
US6925808B2 (en) 2005-08-09
EP1431662B1 (fr) 2008-09-17

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