EP0182570A2 - Brûleur à deux étages de gazéification pour un moteur à turbine à gaz - Google Patents

Brûleur à deux étages de gazéification pour un moteur à turbine à gaz Download PDF

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Publication number
EP0182570A2
EP0182570A2 EP85308188A EP85308188A EP0182570A2 EP 0182570 A2 EP0182570 A2 EP 0182570A2 EP 85308188 A EP85308188 A EP 85308188A EP 85308188 A EP85308188 A EP 85308188A EP 0182570 A2 EP0182570 A2 EP 0182570A2
Authority
EP
European Patent Office
Prior art keywords
cooling
combustion section
inlet air
burner
air
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Withdrawn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
EP85308188A
Other languages
German (de)
English (en)
Inventor
Sigmunn Strom
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.)
Kongsberg Gruppen ASA
Original Assignee
Kongsberg Vapenfabrikk AS
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 Kongsberg Vapenfabrikk AS filed Critical Kongsberg Vapenfabrikk AS
Publication of EP0182570A2 publication Critical patent/EP0182570A2/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Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/54—Reverse-flow combustion chambers

Definitions

  • the present invention relates to combustors for gas turbine engines and, in particular, to a convectionally-cooled 2-stage combustor with low pressure loss and uniform exhaust temperature.
  • the present invention is directed to a combustor for a gas turbine engine having low air velocity and two stage burning which provides an overall temperature distribution factor in the range of 0.07 to 0.12. This is achieved by use of convection cooling and avoidance of conventional film cooling of the combustor walls and a specific distribution of inlet air entering into the combustor.
  • the combustor for a gas turbine engine comprises a burner defining an axial fluid-flow path between upstream and downstream ends thereof, the burner including a first combustion section proximate the upstream end, a second combustion section axially downstream of the first combustion section, and an exhaust section proximate the downstream end; a burner casing coaxially surrounding the burner and defining an annular conduit for flow of inlet air from downstream to upstream ends of the burner, the inlet air flow convectionally cooling the burner; means at the upstream end of the burner for introducing fuel into the first combustion section; first primary means for introducing a first primary portion of the inlet air into the first combustion section to generate a combustible fuel-air mixture therein; first cooling means for introducing a first cooling portion of the inlet air into the first combustion section to generate a swirling flow of first cooling air therein, the swirling flow of first cooling air creating an annular cooling layer proximate the upstream end of the
  • the first primary means comprises a plurality of first primary openings at the upstream end of the burner disposed around the fuel introducing means
  • the first cooling means comprises a plurality of first cooling openings at the upstream end of the burner disposed in an annular array radially outward of the first primary openings
  • the second primary means comprises a plurality of radially oriented second primary openings circumferentially spaced about the burner proximate the downstream end of the first combustion section
  • the second cooling means comprises a plurality of axially oriented second cooling openings circumferentially spaced about the burner proximate the downstream end of the first combustion section
  • the dilution means comprises a plurality of radially oriented dilution openings circumferentially spaced about the burner proximate the downstream end of the second combustion section.
  • the first primary portion is approximately 18% of inlet air
  • the first cooling portion is approximately 12% of inlet air
  • the second primary portion is approximately 18% of inlet air
  • the second cooling portion is approximately 8X of inlet air
  • the dilution portion is approximately 44X of inlet air.
  • the combustor of the invention comprises a burner defining an axial fluid-flow path for gases between upstream and downstream ends thereof and including a first combustion section proximate the upstream end, a second combustion section axially downstream of the first combustion section and an exhaust section proximate the downstream end.
  • the combustor 10 includes a burner 12 defining an axial fluid-flow path A between an upstream end 14 and a downstream end 16.
  • the burner includes a first combustion section 18 proximate upstream end 14, a second combustion section 20 axially downstream of first combustion section 18 and an exhaust section 22 proximate downstream end 16.
  • the combustor includes a burner casing coaxially surrounding the burner and defining an annular conduit for flow of inlet air from downstream to upstream ends of the burner, the inlet air flow convectionally cooling the burner.
  • burner casing 24 coaxially surrounds burner 12 and defines an annular conduit 26 for flow of inlet air depicted by arrows 28 from downstream end 16 to upstream end 14.
  • Inlet air flow 28 convectionally cools burner 12 by flowing along the outside surface of the burner.
  • Inlet air 28 is generated by the compressor (not shown) of the gas turbine engine and conveyed to annular conduit 26 by conduit means (not shown).
  • the combustor includes means for introducing fuel into the burner proximate the upstream end thereof.
  • Fuel nozzle 30, as seen in Figures 1 and 2 projects through upstream end 14 of burner 12 to inject fuel into first combustion section 18.
  • the combustor includes a first primary means for introducing a first primary part of the inlet air into the first combustion section to generate a combustible fuel-air mixture therein.
  • the first primary means comprises a plurality of first primary openings 40 in upstream end 14 of burner 12 disposed around fuel nozzle 30.
  • About 18% of the inlet air 28 flowing through annular conduit 26 enters first combustion section 18 through first primary openings 40 and mixes with fuel injected into first combustion section 18 by fuel nozzle 30.
  • Various structural features may be incorporated within first combustion section 18 proximate fuel nozzle 30 to generate swirling and mixing action between inlet air and fuel.
  • the combustor includes a first cooling means for introducing a first cooling portion of the inlet air into the first combustion section to generate a swirling flow of first cooling air therein.
  • the swirling flow of first cooling air creates an annular cooling layer proximate the upstream end of the first combustion section which substantially mixes with the first primary portion downstream in the first combustion section.
  • first cooling means comprises a plurality of first cooling openings 42 in the upstream end 14 of the burner 12.
  • First cooling openings 42 are disposed in an annular array radially outward of first primary openings 40.
  • Approximately 12% of inlet air 28 flowing through annular conduit 26 enters first combustion section 18 through first cooling openings 42.
  • First cooling openings 42 are so arranged as to generate a swirling action of cooling air in the upstream end of first combustion section 18.
  • the swirling action of the cooling air generates an annular layer of cooling air at the upstream end of section 18 which is then mixed with the primary air downstream in section 18.
  • the annular layer of cooling air known as film cooling, does not extend to the downstream end of the first combustion section 18.
  • the combustor includes a second primary means for introducing a second primary part of inlet air into the second combustion section to generate a combustible fuel-air mixture therein.
  • second primary means comprises a plurality of radially-oriented second primary openings 44 circumferentially spaced about burner 12 proximate the downstream end of first combustion section 18. Approximately 18% of inlet air 28 enters first combustion section 18 at the downstream end thereof through openings 44 and mixes with combustion gases exiting from first combustion section 18 to generate a second stage of burning in second combustion section 20.
  • the combustor of the invention also includes second cooling means for introducing a second cooling portion of inlet air into the second combustion section to generate a swirling flow of second cooling air.
  • the swirling flow of second cooling air creates an annular cooling layer proximate the upstream end of the second combustion section which substantially mixes with the second primary portion downstream in the second combustion section.
  • second cooling means comprises a plurality of axially-oriented second cooling openings circumferentially spaced about the burner proximate the downstream end of the first combustion section.
  • second cooling openings 46 are axially-oriented and open toward the upstream end of the burner 12. The openings are circumferentially spaced about the burner proximate the downstream end of first combustion section 18 and communicate inlet air from annular conduit 26 to the upstream end of second combustion section 20.
  • Second cooling openings 46 are disposed to introduce approximately 8X of inlet air into second combustion chamger 20 in a swirling pattern which generates an annular cooling layer at the upstream end of section 20 which subsequently mixes with the second primary portion.
  • the annular cooling layer does not extend to the downstream end of second combustion section 20.
  • the combustor of the invention also includes a dilution means for introducing a dilution portion of the inlet air into the exhaust section to cool the exhaust gas from the burner.
  • dilution means comprises a plurality of radially oriented dilution openings 48 which receive approximately 44% of inlet air from annular conduit 26 and direct the inlet air into exhaust section 22 of burner 12 to reduce the average temperature of the exhaust gas prior to reaching the turbine.
  • the gas turbine engine cobustors of the invention are capable of high temperature operation with low pressure loss and uniform exhaust temperature.
  • a low air velocity approximately 150 ft/sec.
  • two-stage burning are used, the front end of the burner receives 30X of the inlet air providing a fuel-air ratio of 8.5 to 10X which is above stoichiometric, resulting in a low flame temperature.
  • This low flame temperature and two-stage burning provides low heat transfer to the burner wall which is then cooled by convection cooling through the reverse flow of inlet air.
  • the overall structure provides a temperature distribution factor of about 0.07 to 0.12.
  • the temperature distribution factor is defined as maximum temperature minus average temperature divided by average temperature minus inlet temperature.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
EP85308188A 1984-11-13 1985-11-11 Brûleur à deux étages de gazéification pour un moteur à turbine à gaz Withdrawn EP0182570A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US67060384A 1984-11-13 1984-11-13
US670603 1991-03-15

Publications (1)

Publication Number Publication Date
EP0182570A2 true EP0182570A2 (fr) 1986-05-28

Family

ID=24691070

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85308188A Withdrawn EP0182570A2 (fr) 1984-11-13 1985-11-11 Brûleur à deux étages de gazéification pour un moteur à turbine à gaz

Country Status (3)

Country Link
EP (1) EP0182570A2 (fr)
JP (1) JPS61159031A (fr)
NO (1) NO854511L (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100126174A1 (en) * 2006-09-07 2010-05-27 Rainer Brinkmann Gas turbine combustion chamber
CN101918764B (zh) * 2007-11-13 2012-07-25 欧普拉技术有限公司 冲击冷却型罐式燃烧器
CN106705075A (zh) * 2016-12-12 2017-05-24 深圳智慧能源技术有限公司 强制气膜冷却的火炬
CN107013912A (zh) * 2017-05-31 2017-08-04 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 自冷却引射式燃烧器
WO2023030467A1 (fr) * 2021-09-03 2023-03-09 永旭腾风新能源动力科技（北京）有限公司 Chambre de combustion à doubles tuyaux de carburant et turbine à gaz

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8307657B2 (en) * 2009-03-10 2012-11-13 General Electric Company Combustor liner cooling system
US9664390B2 (en) * 2012-07-09 2017-05-30 Ansaldo Energia Switzerland AG Burner arrangement including an air supply with two flow passages

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100126174A1 (en) * 2006-09-07 2010-05-27 Rainer Brinkmann Gas turbine combustion chamber
CN101918764B (zh) * 2007-11-13 2012-07-25 欧普拉技术有限公司 冲击冷却型罐式燃烧器
CN106705075A (zh) * 2016-12-12 2017-05-24 深圳智慧能源技术有限公司 强制气膜冷却的火炬
CN106705075B (zh) * 2016-12-12 2023-12-12 深圳智慧能源技术有限公司 强制气膜冷却的火炬
CN107013912A (zh) * 2017-05-31 2017-08-04 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 自冷却引射式燃烧器
CN107013912B (zh) * 2017-05-31 2023-09-19 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225B (zh) * 2017-05-31 2023-09-19 深圳智慧能源技术有限公司 自冷却引射式燃烧器
WO2023030467A1 (fr) * 2021-09-03 2023-03-09 永旭腾风新能源动力科技（北京）有限公司 Chambre de combustion à doubles tuyaux de carburant et turbine à gaz

Also Published As

Publication number Publication date
JPS61159031A (ja) 1986-07-18
NO854511L (no) 1986-05-14

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