JPS57157935A - Gas turbine combustor - Google Patents

Gas turbine combustor

Info

Publication number
JPS57157935A
JPS57157935A JP57028242A JP2824282A JPS57157935A JP S57157935 A JPS57157935 A JP S57157935A JP 57028242 A JP57028242 A JP 57028242A JP 2824282 A JP2824282 A JP 2824282A JP S57157935 A JPS57157935 A JP S57157935A
Authority
JP
Japan
Prior art keywords
fuel
divergent
nozzles
throat
cavities
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.)
Pending
Application number
JP57028242A
Other languages
Japanese (ja)
Inventor
Mikurosu Bia Jiyanosu
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.)
CBS Corp
Original Assignee
Westinghouse Electric 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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of JPS57157935A publication Critical patent/JPS57157935A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
    • 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
    • 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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

A combustor (10) is capable of reducing the noxious emissions such as fuel bound and thermal nitrogen oxide products during combustion of high nitrogen bearing and high aromatic content fuels. It includes a plurality of substantially concentric pipes (11 to 16) defining annular passages (12a to 16a) with annular venturi shaped divergent nozzles (20 to 24) to facilitate fast mixing of axially supplied air between adjacent annular passages. The longitudinal spacing between at least two adjacent nozzles defines first and second divergent cavities (30, 40). A fuel rich toroidal vortex (T) is formed in proximity to a central fuel jet in the first cavity (30) and advantageously converts fuel bound nitrogen to N2. A fuel lean toroidal vortex (T') formed in the second cavity (40) mixes hot combustion products with additional gaseous reactant to complete the combustion while avoiding locally high temperatures, and thus thermal NOx formation. A ring of jet nozzles (42) radially injects relatively small amounts of high pressure gaseous reactant or steam to form a throat to separate and stabilize the vortices. Alternatively, the pipes extending between the two cavities can include a convergent and divergent portion forming the throat. <IMAGE>
JP57028242A 1981-02-27 1982-02-25 Gas turbine combustor Pending JPS57157935A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US23866881A 1981-02-27 1981-02-27

Publications (1)

Publication Number Publication Date
JPS57157935A true JPS57157935A (en) 1982-09-29

Family

ID=22898839

Family Applications (2)

Application Number Title Priority Date Filing Date
JP57028242A Pending JPS57157935A (en) 1981-02-27 1982-02-25 Gas turbine combustor
JP1984078122U Granted JPS6016866U (en) 1981-02-27 1984-05-29 Two-stage rich lean combustor

Family Applications After (1)

Application Number Title Priority Date Filing Date
JP1984078122U Granted JPS6016866U (en) 1981-02-27 1984-05-29 Two-stage rich lean combustor

Country Status (13)

Country Link
JP (2) JPS57157935A (en)
AR (1) AR227092A1 (en)
AU (1) AU546612B2 (en)
BE (1) BE892290A (en)
BR (1) BR8201026A (en)
CA (1) CA1179156A (en)
CH (1) CH661974A5 (en)
GB (1) GB2094464B (en)
IN (1) IN155686B (en)
IT (1) IT1149777B (en)
MX (1) MX155871A (en)
NL (1) NL8200333A (en)
ZA (1) ZA82831B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11257665A (en) * 1997-12-31 1999-09-21 United Technol Corp <Utc> Low nox combustor for gas turbine engine
JP2001208349A (en) * 1999-12-10 2001-08-03 General Electric Co <Ge> Method and apparatus for reducing discharge of harmful waste from combustor
WO2019088107A1 (en) * 2017-10-31 2019-05-09 国立研究開発法人産業技術総合研究所 Combustor and combustion method

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
US5361586A (en) * 1993-04-15 1994-11-08 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor
US5454712A (en) * 1993-09-15 1995-10-03 The Boc Group, Inc. Air-oxy-fuel burner method and apparatus
DE19627760C2 (en) * 1996-07-10 2001-05-03 Mtu Aero Engines Gmbh Burner with atomizer nozzle
US7175423B1 (en) * 2000-10-26 2007-02-13 Bloom Engineering Company, Inc. Air staged low-NOx burner
DE10140422C1 (en) * 2001-08-17 2002-11-28 Eisenmann Kg Maschbau Thermal post-combustion device for cleaning waste gases comprises a burner having a second flame tube surrounding the end of a first flame tube with a greater radius to form an annular gap
US9879635B2 (en) * 2007-11-12 2018-01-30 GETAS GESELLSCHAFT FüR THERMODYNAMISCHE ANTRIEBSSYSTEME MBH Axial piston engine and method for operating an axial piston engine
US8783585B2 (en) * 2009-05-20 2014-07-22 General Electric Company Methods and systems for mixing reactor feed

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11257665A (en) * 1997-12-31 1999-09-21 United Technol Corp <Utc> Low nox combustor for gas turbine engine
JP2001208349A (en) * 1999-12-10 2001-08-03 General Electric Co <Ge> Method and apparatus for reducing discharge of harmful waste from combustor
WO2019088107A1 (en) * 2017-10-31 2019-05-09 国立研究開発法人産業技術総合研究所 Combustor and combustion method
JPWO2019088107A1 (en) * 2017-10-31 2020-11-12 国立研究開発法人産業技術総合研究所 Combustor and combustion method

Also Published As

Publication number Publication date
JPS6126774Y2 (en) 1986-08-11
CA1179156A (en) 1984-12-11
JPS6016866U (en) 1985-02-05
BE892290A (en) 1982-08-25
GB2094464B (en) 1984-08-30
CH661974A5 (en) 1987-08-31
AU546612B2 (en) 1985-09-12
NL8200333A (en) 1982-09-16
BR8201026A (en) 1983-01-04
ZA82831B (en) 1983-03-30
IT8219859A0 (en) 1982-02-25
IN155686B (en) 1985-02-23
IT1149777B (en) 1986-12-10
MX155871A (en) 1988-05-16
AU7998082A (en) 1982-09-02
GB2094464A (en) 1982-09-15
AR227092A1 (en) 1982-09-15

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