US3751911A - Air inlet arrangement for gas turbine engine combustion chamber - Google Patents

Air inlet arrangement for gas turbine engine combustion chamber Download PDF

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Publication number
US3751911A
US3751911A US00133492A US3751911DA US3751911A US 3751911 A US3751911 A US 3751911A US 00133492 A US00133492 A US 00133492A US 3751911D A US3751911D A US 3751911DA US 3751911 A US3751911 A US 3751911A
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US
United States
Prior art keywords
air
combustion chamber
air inlet
flame tube
end wall
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
US00133492A
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English (en)
Inventor
Tartaglia P De
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
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Expired - Lifetime legal-status Critical Current

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    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • 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

  • ABSTRACT A combustion chamber to gas turbine engines equipped with a flame tube provided with air inlet openings for combustion and mixing air; further air inlet openings are provided in the flame tube at the level of the combustion chamber end wall, through which small quantities of air are adapted to be blown radially inwardly toward the discharge point of the fuel injection nozzle.
  • FIG 2 INVENTOR PETER DE TARTAGLIA BY cmz QM, am a NJSL.
  • This invention relates to a combustion chamber for gas turbine engines, whose flame tube contains air inlet openings for the supply of combustion and mixing air.
  • the ratio of the cross-sectional areas of the primary and secondary air inlet openings is so chosen that the fuel-air mixture in the combustion zone of the combustion chamber is approximately stoichiometric.
  • the purpose of this invention is, therefore, to eliminate the above-mentioned drawbacks of the known types of combustion chambers and to provide a combustion chamber which offers, in addition to a high degree of combustion at partial load and a good LEAN extinction limit, a combustion which produces neither carbon deposits nor a pollution of the exhaust gases.
  • the flame tube may be equipped with tubes and/or ribs arranged coaxially to the air inlet openings in the flame tube.
  • a zone of high turbulence will be created adjacent to the combustion chamber end wall, which will have a favorable effect on the combustion process
  • FIG. 1 is a longitudinal sectional view of a reverse flow combustion chamber incorporating a flameholder
  • FIG. 2 is a cross-section taken along line A B of FIG. 1, and
  • FIG. 3 is a modified embodiment for the crosssection taken along line A B of FIG. 1.
  • FIG. I this figure illustrates the invention in connection with a reverse flow combustion chamber whose outer casing terminates at the righthand portion of the drawing, in a flameholder 2 with the fuel injection nozzle 3 installed in its center.
  • the outer casing 1 houses coaxially to its longitudinal axis 4 the flame tube 5 which terminates, in the right-hand portion of the drawing, between the outer casing I and the flameholder 2, in a rim-like or bulge-like deflector 6 which produces a favorable flow reversing section 7 for the primary air duct.
  • Secondary air is supplied through air inlet ports 8 of circular area.
  • the primary air enters through the primary air reversing duct 7 in the direction of arrow E (downstream direction with respect to the flow of combustion chamber products) between the flameholder 2 and the flame tube 5 into the primary zone 9 of the combustion chamber, producing the reverse flow zone 10 in which the fuel 11 injected by the fuel injector nozzle 3 is combusted.
  • the air inlet openings 12 are arranged at the level of the conically flaring rear wall 15 of the combustion chamber formed by flameholder 2. Any deflection of the airstreams from the direction of arrows F under the influence of the primary air inlet stream in the direction of arrow E will be prevented by tubes 13 (FIGS. 1 and 2) and/or ribs 14 (FIG. 3) suitably welded into the flame tube 5.
  • Thetubes l3 and the ribs 14 further assist the directional flow of the air towards the discharge tip of the fuel injector nozzle 3 by their radially inward arrangement inclined in the direction of the fuel injector nozzle 3.
  • the invention can also be applied to annular combustion chambers as well as to combustion chambers having an annular outer casing housing several individual combustion chambers.
  • a combustion chamber arrangement for a gas turbine engine comprising: a flame tube and an end wall forming a combustion chamber space, fuel injector nozzle means having a fuel discharge point located centrally of said end wall for injecting fuel into said combustion chamber space in a downstream direction, air introducing means for supplying combustion and mixing air to said combustion chamber space, said air introducing means including first air inlet means arranged in the flame tube for introducing air in an upstream direction parallel to and along said end wall toward said discharge point and second air inlet means for introducing air into said combustion chamber space in a downstream direction, said end wall being tapered conically outwardly in the downstream direction from said discharge point to adjacent the first air inlet means, and an outer casing surrounding said flame tube with an annular space between said outer casing and said flame tube for conducting mixing and combustion air to said air introducing means, said second air inlet means being constructed as an annular opening between said end wall and said flame tube, said end wall being formed by an extension of said outer casing.
  • said first air inlet means includes a plurality of cylindrical inlet tubes extending from said annular space across said annular opening inwardly into said combustion chamber space.
  • said first air inlet means includes a plurality of partcylindrical rib means extending from openings leading from said annular space and across said annular opening.
  • said air introducing means includes third air inlet means for introducing air into said combustion chamber space, said third air inlet means including a plurality of openings in said flame tube means which communicate with said annular space and said combustion chamber space at a position downstream of said first and second air inlet means.
  • said air introducing means includes third air inlet means for introducing air into said combustion cham ber space, said third air inlet means including a plurality of openings in said flame tube means which communicate with said annular space and said combustion chamber space at a position downstream of said first and second air inlet means.
  • a combustion chamber arrangement for a gas turbine engine comprising: a flame tube and an end wall forming a combustion chamber space, fuel injector nozzle means having a fuel discharge point located centrally of said end wall for injecting fuel into said combustion chamber space in a downstream direction, said end wall being tapered conically outwardly in the downstream direction from said discharge point to adjacent the downstream end of said end wall, and air introducing means for supplying combustion and mixing air to said combustion chamber space, said air introducing means including first air inlet means arranged in the flame tube for introducing air in an upstream direction parallel to and along said end wall toward said discharge point and second air inlet means for introducing air into said combustion chamber space in a downstream direction, said second air inlet means being formed by an annular opening between said flame tube and said downstream end of said end wall, said first air inlet means including means extending across said annular opening for precluding intermixing of the flow from said first and second air inlet means, whereby flow from said first air inlet means is not interrupted by flow from said second inlet means such that it
  • said means extending across said annular opening includes a plurality of cylindrical inlet tubes extending inwardly into the combustion chamber space through said flame tube means.
  • said means extending across said annular opening includes a plurality of part-cylindrical rib means extending inwardly into the combustion chamber space from openings in said flame tube means.
  • said means extending across said annular opening includes a plurality of cylindrical inlet tubes extending from said annular space across said annular opening inwardly into said combustion chamber space.
  • said air introducing means includes third air inlet means for introducing air into said combustion chamber space, said third air inlet means including a plurality of openings in said flame tube means which communicate with said annular space and said combustion chamber space at a position downstream of said first and second air inlet means.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Air Supply (AREA)
US00133492A 1970-04-18 1971-04-13 Air inlet arrangement for gas turbine engine combustion chamber Expired - Lifetime US3751911A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19702018641 DE2018641C2 (de) 1970-04-18 1970-04-18 Umkehrbrennkammer fuer gasturbinentriebwerke

Publications (1)

Publication Number Publication Date
US3751911A true US3751911A (en) 1973-08-14

Family

ID=5768415

Family Applications (1)

Application Number Title Priority Date Filing Date
US00133492A Expired - Lifetime US3751911A (en) 1970-04-18 1971-04-13 Air inlet arrangement for gas turbine engine combustion chamber

Country Status (6)

Country Link
US (1) US3751911A (cs)
JP (1) JPS4946665B1 (cs)
DE (1) DE2018641C2 (cs)
FR (1) FR2086180B1 (cs)
GB (1) GB1347697A (cs)
SE (1) SE368258B (cs)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1982000334A1 (en) * 1980-07-10 1982-02-04 Bailey J Vaporizing combustor tube
US6145296A (en) * 1998-09-25 2000-11-14 Alm Development, Inc. Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines
US6189311B1 (en) 1999-03-11 2001-02-20 Alm Development, Inc. Gas turbine engine
US6193502B1 (en) * 1997-02-08 2001-02-27 Ruhrgas Aktiengesellschaft Fuel combustion device and method
US6212871B1 (en) 1999-03-11 2001-04-10 Alm Development, Inc. Method of operation of a gas turbine engine and a gas turbine engine
US6272844B1 (en) 1999-03-11 2001-08-14 Alm Development, Inc. Gas turbine engine having a bladed disk
US6305157B1 (en) 1998-09-25 2001-10-23 Alm Development, Inc. Gas turbine engine
US6363708B1 (en) 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6438959B1 (en) * 2000-12-28 2002-08-27 General Electric Company Combustion cap with integral air diffuser and related method
US6442945B1 (en) 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US6460324B1 (en) 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
US6460343B1 (en) 1998-09-25 2002-10-08 Alm Development, Inc. Gas turbine engine
US6557337B1 (en) 1998-09-25 2003-05-06 Alm Development, Inc. Gas turbine engine
EP1482244A1 (en) * 2003-05-31 2004-12-01 Aqua-Chem, Inc. Counterflow fuel injection nozzle in a burner-boiler system
EP1489359A1 (fr) * 2003-06-17 2004-12-22 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110265483A1 (en) * 2009-10-28 2011-11-03 Man Diesel & Turbo Se Combustor For A Turbine, and Gas Turbine Outfitted With A Combustor of This Kind
CN102997281A (zh) * 2011-09-14 2013-03-27 通用电气公司 用于调节燃烧器中的工作流体的系统和方法
EP2775208A3 (en) * 2013-03-08 2015-10-21 Pratt & Whitney Canada Corp. Combustor heat shield with carbon avoidance feature
US20160146464A1 (en) * 2014-11-25 2016-05-26 General Electric Technology Gmbh Combustor with annular bluff body
US20160146467A1 (en) * 2014-11-25 2016-05-26 General Electric Technology Gmbh Combustor liner
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US10830198B2 (en) * 2015-08-27 2020-11-10 Westpoint Power Inc. Deposit mitigation for gaseous fuel injectors

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1532636A (en) * 1975-10-02 1978-11-15 Secr Defence Combustion apparatus
RU2052145C1 (ru) * 1993-08-08 1996-01-10 Анатолий Михайлович Рахмаилов Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель (варианты)
CN113154456B (zh) * 2021-04-15 2022-06-21 中国航发湖南动力机械研究所 回流燃烧室机匣头部结构及其制造方法和发动机燃烧室
CN114858427B (zh) * 2022-03-23 2025-07-11 中国联合重型燃气轮机技术有限公司 一种用于检测燃气轮机燃烧室喷嘴性能的试验装置

Citations (10)

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Publication number Priority date Publication date Assignee Title
US2555965A (en) * 1950-03-24 1951-06-05 Gen Electric End cap for fluid fuel combustors
US2657531A (en) * 1948-01-22 1953-11-03 Gen Electric Wall cooling arrangement for combustion devices
AU205220B2 (en) * 1955-11-10 1956-05-17 Joseph Lucas Industries ) Limited Combustion chambers for jet-propulsion engines, gas turbines andother prime movers
CA545787A (en) * 1957-09-03 Rolls-Royce Limited Combustion equipment of gas-turbine engines
GB836117A (en) * 1956-02-02 1960-06-01 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
US3064424A (en) * 1959-09-30 1962-11-20 Gen Motors Corp Flame tube
US3306334A (en) * 1965-04-26 1967-02-28 Goubsky Gregory Michael Space heaters
US3306333A (en) * 1964-03-31 1967-02-28 Bendix Corp Air spray combustor
US3321912A (en) * 1962-11-14 1967-05-30 Saurer Ag Adolph Gas turbine plant
US3671171A (en) * 1970-11-27 1972-06-20 Avco Corp Annular combustors

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB819065A (en) * 1955-11-16 1959-08-26 Rolls Royce Improvements in or relating to combustion equipment for example of gas turbine engines
US2821067A (en) * 1956-05-28 1958-01-28 Boeing Co Combustion chamber construction in a gas turbine engine
GB1036677A (en) * 1965-05-17 1966-07-20 Rolls Royce Combustion equipment for a gas turbine engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA545787A (en) * 1957-09-03 Rolls-Royce Limited Combustion equipment of gas-turbine engines
US2657531A (en) * 1948-01-22 1953-11-03 Gen Electric Wall cooling arrangement for combustion devices
US2555965A (en) * 1950-03-24 1951-06-05 Gen Electric End cap for fluid fuel combustors
AU205220B2 (en) * 1955-11-10 1956-05-17 Joseph Lucas Industries ) Limited Combustion chambers for jet-propulsion engines, gas turbines andother prime movers
GB836117A (en) * 1956-02-02 1960-06-01 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
US3064424A (en) * 1959-09-30 1962-11-20 Gen Motors Corp Flame tube
US3321912A (en) * 1962-11-14 1967-05-30 Saurer Ag Adolph Gas turbine plant
US3306333A (en) * 1964-03-31 1967-02-28 Bendix Corp Air spray combustor
US3306334A (en) * 1965-04-26 1967-02-28 Goubsky Gregory Michael Space heaters
US3671171A (en) * 1970-11-27 1972-06-20 Avco Corp Annular combustors

Cited By (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1982000334A1 (en) * 1980-07-10 1982-02-04 Bailey J Vaporizing combustor tube
US6193502B1 (en) * 1997-02-08 2001-02-27 Ruhrgas Aktiengesellschaft Fuel combustion device and method
US6460343B1 (en) 1998-09-25 2002-10-08 Alm Development, Inc. Gas turbine engine
US6145296A (en) * 1998-09-25 2000-11-14 Alm Development, Inc. Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines
US6305157B1 (en) 1998-09-25 2001-10-23 Alm Development, Inc. Gas turbine engine
US6557337B1 (en) 1998-09-25 2003-05-06 Alm Development, Inc. Gas turbine engine
US6189311B1 (en) 1999-03-11 2001-02-20 Alm Development, Inc. Gas turbine engine
US6212871B1 (en) 1999-03-11 2001-04-10 Alm Development, Inc. Method of operation of a gas turbine engine and a gas turbine engine
US6272844B1 (en) 1999-03-11 2001-08-14 Alm Development, Inc. Gas turbine engine having a bladed disk
US6363708B1 (en) 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6460324B1 (en) 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
US6442945B1 (en) 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US6438959B1 (en) * 2000-12-28 2002-08-27 General Electric Company Combustion cap with integral air diffuser and related method
EP1482244A1 (en) * 2003-05-31 2004-12-01 Aqua-Chem, Inc. Counterflow fuel injection nozzle in a burner-boiler system
EP1489359A1 (fr) * 2003-06-17 2004-12-22 Snecma Moteurs Chambre de combustion annulaire de turbomachine
FR2856468A1 (fr) * 2003-06-17 2004-12-24 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US20050042076A1 (en) * 2003-06-17 2005-02-24 Snecma Moteurs Turbomachine annular combustion chamber
US7155913B2 (en) 2003-06-17 2007-01-02 Snecma Moteurs Turbomachine annular combustion chamber
RU2342602C2 (ru) * 2003-06-17 2008-12-27 Снекма Мотер Кольцевая камера сгорания газотурбинного двигателя
US20110061390A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Inlet premixer for combustion apparatus
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110061391A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Vortex premixer for combustion apparatus
US20110061395A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Method of fuel staging in combustion apparatus
US8689561B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Vortex premixer for combustion apparatus
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110265483A1 (en) * 2009-10-28 2011-11-03 Man Diesel & Turbo Se Combustor For A Turbine, and Gas Turbine Outfitted With A Combustor of This Kind
US9140452B2 (en) * 2009-10-28 2015-09-22 Man Diesel & Turbo Se Combustor head plate assembly with impingement
US8522553B2 (en) * 2011-09-14 2013-09-03 General Electric Company System and method for conditioning a working fluid in a combustor
CN102997281A (zh) * 2011-09-14 2013-03-27 通用电气公司 用于调节燃烧器中的工作流体的系统和方法
EP2775208A3 (en) * 2013-03-08 2015-10-21 Pratt & Whitney Canada Corp. Combustor heat shield with carbon avoidance feature
US10816200B2 (en) 2013-03-08 2020-10-27 Pratt & Whitney Canada Corp. Combustor heat shield with carbon avoidance feature
US9518739B2 (en) 2013-03-08 2016-12-13 Pratt & Whitney Canada Corp. Combustor heat shield with carbon avoidance feature
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
CN105627363A (zh) * 2014-11-25 2016-06-01 通用电器技术有限公司 燃烧器衬套
CN105627366A (zh) * 2014-11-25 2016-06-01 通用电器技术有限公司 具有环状非流线型主体的燃烧器
EP3026346A1 (en) * 2014-11-25 2016-06-01 Alstom Technology Ltd Combustor liner
US20160146467A1 (en) * 2014-11-25 2016-05-26 General Electric Technology Gmbh Combustor liner
US20160146464A1 (en) * 2014-11-25 2016-05-26 General Electric Technology Gmbh Combustor with annular bluff body
US10830198B2 (en) * 2015-08-27 2020-11-10 Westpoint Power Inc. Deposit mitigation for gaseous fuel injectors

Also Published As

Publication number Publication date
DE2018641C2 (de) 1972-05-10
FR2086180B1 (cs) 1975-09-26
DE2018641B1 (de) 1971-10-14
FR2086180A1 (cs) 1971-12-31
GB1347697A (en) 1974-02-27
JPS4946665B1 (cs) 1974-12-11
SE368258B (cs) 1974-06-24

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