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EP0841517A3 - Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle - Google Patents

Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle Download PDF

Info

Publication number
EP0841517A3
EP0841517A3 EP97114341A EP97114341A EP0841517A3 EP 0841517 A3 EP0841517 A3 EP 0841517A3 EP 97114341 A EP97114341 A EP 97114341A EP 97114341 A EP97114341 A EP 97114341A EP 0841517 A3 EP0841517 A3 EP 0841517A3
Authority
EP
European Patent Office
Prior art keywords
coolant
combustion chamber
gas turbine
fuel
turbine combustion
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
EP97114341A
Other languages
German (de)
French (fr)
Other versions
EP0841517B1 (en
EP0841517A2 (en
Inventor
William Kwan
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce 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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0841517A2 publication Critical patent/EP0841517A2/en
Publication of EP0841517A3 publication Critical patent/EP0841517A3/en
Application granted granted Critical
Publication of EP0841517B1 publication Critical patent/EP0841517B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse (1), die ein ein Kraftstoff-Führungsrohr (4) mit Abstand umgebendes Kühlflüssigkeits-Rohr (10) aufweist, welches nahe der Düsen-Austrittsöffnung (7) in einen Ringraum (9) für die Kühlflüssigkeit mündet oder diesen das Kraftstoff-Führungsrohr direkt umgebenden Ringraum bildet, wobei innerhalb des Kühlflüssigkeits-Rohres bezüglich der Kraftstoff-Strömungsrichtung stromauf des Ringraumes ein das Kraftstoff-Führungsrohr umgebendes Trennwand-Element (11) vorgesehen ist, welches den Innenraum des Kühlflüssigkeits-Rohres in zwei Raumsegmente (12A,12B) unterteilt, wobei das erste Raumsegment mit einem Zuführkanal (13) und das zweite Raumsegment mit einem Abführkanal (14) für die Kühlflüssigkeit verbunden ist.

Figure 00000001
Fuel injection device for a gas turbine combustion chamber with a liquid-cooled injection nozzle (1), which has a coolant pipe (10) surrounding a fuel guide pipe (4) at a distance, which coolant pipe (10) for an annular space (9) near the nozzle outlet opening (7) the coolant flows out or forms this annular space directly surrounding the fuel guide tube, a partition wall element (11) surrounding the fuel guide tube being provided within the coolant tube with respect to the fuel flow direction upstream of the annular space, which divides the interior of the coolant tube divided into two room segments (12A, 12B), the first room segment being connected to a supply channel (13) and the second room segment being connected to a discharge channel (14) for the cooling liquid.
Figure 00000001
EP97114341A 1996-11-07 1997-08-20 Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle Expired - Lifetime EP0841517B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19645961 1996-11-07
DE19645961A DE19645961A1 (en) 1996-11-07 1996-11-07 Fuel injector for a gas turbine combustor with a liquid cooled injector

Publications (3)

Publication Number Publication Date
EP0841517A2 EP0841517A2 (en) 1998-05-13
EP0841517A3 true EP0841517A3 (en) 1998-12-23
EP0841517B1 EP0841517B1 (en) 2001-12-19

Family

ID=7810954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97114341A Expired - Lifetime EP0841517B1 (en) 1996-11-07 1997-08-20 Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle

Country Status (4)

Country Link
US (1) US6003781A (en)
EP (1) EP0841517B1 (en)
CA (1) CA2220213C (en)
DE (2) DE19645961A1 (en)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2248736C (en) 1996-03-13 2007-03-27 Parker-Hannifin Corporation Internally heatshielded nozzle
EP1046010B1 (en) * 1998-10-09 2006-07-12 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6357237B1 (en) 1998-10-09 2002-03-19 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6149075A (en) * 1999-09-07 2000-11-21 General Electric Company Methods and apparatus for shielding heat from a fuel nozzle stem of fuel nozzle
US6256995B1 (en) * 1999-11-29 2001-07-10 Pratt & Whitney Canada Corp. Simple low cost fuel nozzle support
US6460340B1 (en) * 1999-12-17 2002-10-08 General Electric Company Fuel nozzle for gas turbine engine and method of assembling
FR2817017B1 (en) 2000-11-21 2003-03-07 Snecma Moteurs COMPLETE COOLING OF THE TAKE-OFF INJECTORS OF A TWO-HEAD COMBUSTION CHAMBER
US7117675B2 (en) * 2002-12-03 2006-10-10 General Electric Company Cooling of liquid fuel components to eliminate coking
US6918255B2 (en) * 2002-12-03 2005-07-19 General Electric Company Cooling of liquid fuel components to eliminate coking
US6892552B2 (en) 2003-01-06 2005-05-17 Physics Support Services, Llc System and method for cooling air inhaled by air conditioning housing unit
GB2423353A (en) * 2005-02-19 2006-08-23 Siemens Ind Turbomachinery Ltd A Fuel Injector Cooling Arrangement
US7506510B2 (en) * 2006-01-17 2009-03-24 Delavan Inc System and method for cooling a staged airblast fuel injector
US8166763B2 (en) * 2006-09-14 2012-05-01 Solar Turbines Inc. Gas turbine fuel injector with a removable pilot assembly
US8286433B2 (en) * 2007-10-26 2012-10-16 Solar Turbines Inc. Gas turbine fuel injector with removable pilot liquid tube
US8393155B2 (en) * 2007-11-28 2013-03-12 Solar Turbines Incorporated Gas turbine fuel injector with insulating air shroud
US9221704B2 (en) * 2009-06-08 2015-12-29 Air Products And Chemicals, Inc. Through-port oxy-fuel burner
EP2520858A1 (en) * 2011-05-03 2012-11-07 Siemens Aktiengesellschaft Fuel cooled pilot fuel lance for a gas turbine
US9188063B2 (en) 2011-11-03 2015-11-17 Delavan Inc. Injectors for multipoint injection
US20140054394A1 (en) * 2012-08-27 2014-02-27 Continental Automotive Systems Us, Inc. Reductant delivery unit for automotive selective catalytic reduction systems - active cooling
WO2014058381A1 (en) * 2012-10-11 2014-04-17 Ecomb Ab (Publ) Supply device for a combustion chamber
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US9989257B2 (en) 2015-06-24 2018-06-05 Delavan Inc Cooling in staged fuel systems
US10584927B2 (en) 2015-12-30 2020-03-10 General Electric Company Tube thermal coupling assembly
US10876477B2 (en) 2016-09-16 2020-12-29 Delavan Inc Nozzles with internal manifolding
FR3088969B1 (en) * 2018-11-27 2021-02-19 Ifp Energies Now Fuel injector with cooling means
US11970977B2 (en) 2022-08-26 2024-04-30 Hamilton Sundstrand Corporation Variable restriction of a secondary circuit of a fuel injector
US20240271571A1 (en) * 2023-02-14 2024-08-15 Collins Engine Nozzles, Inc. Proportional control of cooling circuit of fuel nozzle
US20240271790A1 (en) * 2023-02-14 2024-08-15 Collins Engine Nozzles, Inc. Variable cooling of secondary circuit of fuel nozzles

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2166395A5 (en) * 1971-02-09 1973-08-17 Lehougre Jean
WO1994008179A1 (en) * 1992-09-28 1994-04-14 Parker-Hannifin Corporation Multiple passage cooling circuit for gas turbine fuel injector nozzle
US5467925A (en) * 1994-09-06 1995-11-21 Riano; Marcos D. Sulfur gun assembly with rapid service capability
EP0689007A1 (en) * 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooling the take-off injector in a combustion chamber with two burner heads

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE936901C (en) * 1951-07-03 1955-12-22 Dowty Equipment Ltd Fuel ring line for the burners of gas turbines
US3121457A (en) * 1956-12-11 1964-02-18 Lummus Co Burner assembly for synthesis gas generators
US3065916A (en) * 1960-05-03 1962-11-27 Air Prod & Chem Fluid transfer device
US3043577A (en) * 1960-10-20 1962-07-10 Walter V Berry Lance with conduits for mixing gases located interiorly
US3198436A (en) * 1962-02-15 1965-08-03 Air Prod & Chem Apparatus for supplying a plurality of fluids to a combustion zone
US3170016A (en) * 1962-11-23 1965-02-16 Nat Steel Corp Fluid transfer device
US3638932A (en) * 1969-03-26 1972-02-01 Chemetron Corp Combined burner-lance for fume suppression in molten metals
US4735044A (en) * 1980-11-25 1988-04-05 General Electric Company Dual fuel path stem for a gas turbine engine
FR2721693B1 (en) * 1994-06-22 1996-07-19 Snecma Method and device for supplying fuel and cooling the take-off injector of a combustion chamber with two heads.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2166395A5 (en) * 1971-02-09 1973-08-17 Lehougre Jean
WO1994008179A1 (en) * 1992-09-28 1994-04-14 Parker-Hannifin Corporation Multiple passage cooling circuit for gas turbine fuel injector nozzle
EP0689007A1 (en) * 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooling the take-off injector in a combustion chamber with two burner heads
US5467925A (en) * 1994-09-06 1995-11-21 Riano; Marcos D. Sulfur gun assembly with rapid service capability

Also Published As

Publication number Publication date
DE59705876D1 (en) 2002-01-31
EP0841517B1 (en) 2001-12-19
CA2220213A1 (en) 1998-05-07
US6003781A (en) 1999-12-21
DE19645961A1 (en) 1998-05-14
CA2220213C (en) 2006-04-04
EP0841517A2 (en) 1998-05-13

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