SG158865A1 - Method and apparatus to facilitate reducing nox emissions in turbine engines - Google Patents

Method and apparatus to facilitate reducing nox emissions in turbine engines

Info

Publication number
SG158865A1
SG158865A1 SG201000113-9A SG2010001139A SG158865A1 SG 158865 A1 SG158865 A1 SG 158865A1 SG 2010001139 A SG2010001139 A SG 2010001139A SG 158865 A1 SG158865 A1 SG 158865A1
Authority
SG
Singapore
Prior art keywords
panel
turbine engines
nox emissions
reducing nox
facilitate reducing
Prior art date
Application number
SG201000113-9A
Other languages
English (en)
Inventor
Arthur Wesley Johnson
Richard W Stickles
Willard J Dodds
David L Burrus
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SG158865A1 publication Critical patent/SG158865A1/en

Links

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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
SG201000113-9A 2006-07-14 2007-07-16 Method and apparatus to facilitate reducing nox emissions in turbine engines SG158865A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/486,757 US7895841B2 (en) 2006-07-14 2006-07-14 Method and apparatus to facilitate reducing NOx emissions in turbine engines

Publications (1)

Publication Number Publication Date
SG158865A1 true SG158865A1 (en) 2010-02-26

Family

ID=38650015

Family Applications (2)

Application Number Title Priority Date Filing Date
SG201000113-9A SG158865A1 (en) 2006-07-14 2007-07-16 Method and apparatus to facilitate reducing nox emissions in turbine engines
SG200705242-6A SG139666A1 (en) 2006-07-14 2007-07-16 Method and apparatus to facilitate reducing nox emissions in turbine engines

Family Applications After (1)

Application Number Title Priority Date Filing Date
SG200705242-6A SG139666A1 (en) 2006-07-14 2007-07-16 Method and apparatus to facilitate reducing nox emissions in turbine engines

Country Status (7)

Country Link
US (2) US7895841B2 (ja)
EP (1) EP1878971A3 (ja)
JP (1) JP5374031B2 (ja)
CN (2) CN101105293B (ja)
CA (1) CA2593466C (ja)
MY (1) MY151124A (ja)
SG (2) SG158865A1 (ja)

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US9335049B2 (en) * 2012-06-07 2016-05-10 United Technologies Corporation Combustor liner with reduced cooling dilution openings
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US9303871B2 (en) 2013-06-26 2016-04-05 Siemens Aktiengesellschaft Combustor assembly including a transition inlet cone in a gas turbine engine
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US10670267B2 (en) * 2015-08-14 2020-06-02 Raytheon Technologies Corporation Combustor hole arrangement for gas turbine engine
US10378444B2 (en) * 2015-08-19 2019-08-13 General Electric Company Engine component for a gas turbine engine
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US10337738B2 (en) 2016-06-22 2019-07-02 General Electric Company Combustor assembly for a turbine engine
US11022313B2 (en) * 2016-06-22 2021-06-01 General Electric Company Combustor assembly for a turbine engine
DE102016219424A1 (de) * 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine sowie Fluggasturbine
US10830433B2 (en) * 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10655853B2 (en) * 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
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US10816202B2 (en) 2017-11-28 2020-10-27 General Electric Company Combustor liner for a gas turbine engine and an associated method thereof
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
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Also Published As

Publication number Publication date
SG139666A1 (en) 2008-02-29
CN101105293A (zh) 2008-01-16
JP2008020180A (ja) 2008-01-31
MY151124A (en) 2014-04-30
US20080010991A1 (en) 2008-01-17
EP1878971A3 (en) 2014-02-26
US20080010992A1 (en) 2008-01-17
CN101105292A (zh) 2008-01-16
US7900457B2 (en) 2011-03-08
JP5374031B2 (ja) 2013-12-25
CA2593466A1 (en) 2008-01-14
US7895841B2 (en) 2011-03-01
CN101105293B (zh) 2011-06-08
EP1878971A2 (en) 2008-01-16
CA2593466C (en) 2014-11-04

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