EP2103876A2 - Brûleur pour turbine à gaz avec mécanisme de rinçage pour les buses à combustible - Google Patents

Brûleur pour turbine à gaz avec mécanisme de rinçage pour les buses à combustible Download PDF

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Publication number
EP2103876A2
EP2103876A2 EP09002943A EP09002943A EP2103876A2 EP 2103876 A2 EP2103876 A2 EP 2103876A2 EP 09002943 A EP09002943 A EP 09002943A EP 09002943 A EP09002943 A EP 09002943A EP 2103876 A2 EP2103876 A2 EP 2103876A2
Authority
EP
European Patent Office
Prior art keywords
fuel
gas turbine
outlet holes
burner according
burner
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Withdrawn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
EP09002943A
Other languages
German (de)
English (en)
Other versions
EP2103876A3 (fr
Inventor
Thomas Dörr
Leif Rackwitz
Waldemar Lazik
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
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2103876A2 publication Critical patent/EP2103876A2/fr
Publication of EP2103876A3 publication Critical patent/EP2103876A3/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Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/30—Purging

Definitions

  • the invention relates to a gas turbine burner according to the features of the preamble of claim 1 and to a method for purging a fuel nozzle.
  • the risk of fuel coking increases when the fuel line is shut off and some of the fuel lines are no longer continuously fueled. This is e.g. For tiered lean burners, it is possible to switch off main burners step by step or completely when passing between different load conditions. A portion of the fuel may remain in the fuel lines which are no longer continuously flowing and is then heated due to the high metal temperatures of the fuel lines and the radiation effect of the flame.
  • the invention has for its object to provide a gas turbine burner and a method for its flushing, which with a simple structure and simple, reliable application avoid a deposit of fuel and its reaction products in the area of the fuel nozzle.
  • a flush mechanism for the shut-off fuel lines of a burner which allows a complete automatic emptying of the fuel lines.
  • the basic principle is to impose different static pressures P a, i in the outlet cross sections of the fuel lines and to generate pressure differences for the autonomous emptying of the fuel lines.
  • the Fig. 1 shows a schematic embodiment of an example of the prior art.
  • a fuel nozzle 1 is provided, which comprises a burner axis 4 and a combustion chamber 2 is assigned, in which a combustion chamber flow 3 results.
  • Reference numeral 17 exemplifies a pilot fuel injection.
  • a prior art lean burn combustor with controlled fuel inhomogeneity for a main stage of a gas turbine combustor is shown in the prior art.
  • the lean burn burner comprises an inner swirl generator 11 as well as a central swirl generator 12 and an outer swirl generator 13, which are assigned to an inner flow channel 14 and a central flow channel 15 and an outer flow channel 16.
  • the reference numeral 17 shows a pilot fuel injection, a main fuel injection is designated 18. Furthermore, an inner downstream surface of the main fuel injection (film depositor) 19 is provided.
  • Reference numeral 20 denotes an outer surface of the main fuel injection, the trailing edge of which is designated 21.
  • the reference numeral 23 shows fuel discharge holes of the main fuel injection. 24 shows a flame stabilizer.
  • an outer burner ring 27 (dome) is provided.
  • Reference numeral 28 denotes the inner contour of the outer burner ring.
  • a pilot fuel supply 29 and a main fuel supply 30 are provided.
  • the reference numeral 33 shows an exit surface of the pilot fuel injection, while the reference numeral 34 shows an exit contour of the inner leg of the flame stabilizer.
  • the Fig. 3 shows a schematic representation of different measures for impressing the different static pressures of the air supply (air flow) and for generating pressure differences.
  • the surface contour of flow-guiding components is profiled in front of the fuel outlet bores 23, so that different pressures in the area of the fuel outlet bores 23 result, which lead to emptying (empty suction) of the fuel lines.
  • measure D it is possible to change the blade positions and / or the profiles of the air swirler (air swirler 12) in the middle flow channel 15. This results in different pressure conditions, which act on the individual fuel outlet holes differently and thus lead to a negative pressure (suction).
  • Fig. 4 shows a schematic representation of the invention provided basic principle of emptying the main fuel lines by a variation of the applied pressure at the fuel outlet holes 23.
  • Fig. 4 an example is shown in which the use of a lower static pressure for every second, designated in the figure with I.
  • Fuel outlet bore which are provided alternately to fuel outlet holes II.
  • the Fig. 5 shows a schematic representation in which a staggering of the fuel outlet holes 23 along the burner axis 4 is provided. Out Fig. 5 result in the different pressure ratios when assigning the staggered fuel outlet holes 23 to a fuel line. 5
  • the 6 and 7 each show the use of a directional control valve 6 in the fuel line 5.
  • the Fig. 6 shows a switching position of the directional control valve 6, in which fuel through the fuel line 5 in a free area of a subsequent fuel line 7, which is connected to the fuel outlet bore 23, is passed.
  • a purge line 8 is out of action.
  • the Fig. 7 shows a switching position of the directional control valve 6, in which air is passed through the purge line 6 in the fuel line 7 and thus to the fuel outlet bore 23, while the supply of fuel through the fuel line 5 is suppressed.
  • This measure corresponds to measure E.
  • Fig. 2 The location of the corresponding constructive measures for a burner is in Fig. 2 shown schematically.
  • the measures can be transferred to any burner with a corresponding discrete fuel injection, for example, the application in Fig. 2 shown for a known lean burn burner.
  • the aim of all measures described above is to position the different application locations for the fuel so that on the one hand different local static pressures of the air flow for emptying standing fuel can be used but also an optimized fuel-air mixture to ensure lowest emissions is possible. Due to the different static pressures of the air at the surface (wall pressures), it follows that air enters the one recess of the fuel line and thus flushes or expels the fuel from the other recess.
  • a variation of the static pressure can be achieved in the circumferential direction.
  • a targeted coordination of the surface contouring with the number and position of the outlet bores can then cause a depletion of the stationary fuel in a shutdown of the main fuel then applied pressure drop.
  • a similar effect can be brought about by adapting the circumferential variation of the blade position of air swirlers in the flow channel of the main stage, in particular on the outer radius and by varying the blade profiling.
  • Another way to set different static pressure drop for the fuel holes is a suitable choice of application sites on the inner contour of the main stage.
  • the presence of an existing by the aerodynamics of the burner static pressure distribution is exploited to position the interconnected fuel outlet holes in areas high or low static pressures and to generate a necessary for the emptying of the stationary fuel pressure difference (s. Fig. 4 ).
  • a different interconnection of the fuel lines of e.g. proposed more than two fuel lines and / or different positioning of interconnected fuel outlet holes in the axial and circumferential directions.
  • Another method for automatic emptying is the integration of a directional valve with eg two switching positions in the burner (s. Fig. 5 ).
  • the main fuel flows continuously through the directional valve.
  • the shutdown of the fuel causes a movement of the directional control valve in a second switching position in which the continuous flow of the fuel is interrupted. Due to the presence of appropriate channel geometries, which can be located either in the middle air duct or upstream in the burner arm, then there is the possibility for continuous flow of purging air. This ensures complete emptying of the fuel lines.
  • the movement of the directional control valve into the starting position causes the release of the pending fuel while the purge air channel is blocked.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
EP09002943.0A 2008-03-18 2009-03-02 Brûleur pour turbine à gaz avec mécanisme de rinçage pour les buses à combustible Withdrawn EP2103876A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008014744A DE102008014744A1 (de) 2008-03-18 2008-03-18 Gasturbinenbrenner für eine Gasturbine mit Spülmechanismus für eine Brennstoffdüse

Publications (2)

Publication Number Publication Date
EP2103876A2 true EP2103876A2 (fr) 2009-09-23
EP2103876A3 EP2103876A3 (fr) 2013-07-03

Family

ID=40785493

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09002943.0A Withdrawn EP2103876A3 (fr) 2008-03-18 2009-03-02 Brûleur pour turbine à gaz avec mécanisme de rinçage pour les buses à combustible

Country Status (3)

Country Link
US (1) US8443609B2 (fr)
EP (1) EP2103876A3 (fr)
DE (1) DE102008014744A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115095861A (zh) * 2022-06-17 2022-09-23 宁波方太厨具有限公司 燃烧器、燃烧器防堵塞方法和燃气灶具

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JP5023526B2 (ja) * 2006-03-23 2012-09-12 株式会社Ｉｈｉ 燃焼器用バーナ及び燃焼方法
DE102007050276A1 (de) * 2007-10-18 2009-04-23 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner für ein Gasturbinentriebwerk
US8991188B2 (en) 2011-01-05 2015-03-31 General Electric Company Fuel nozzle passive purge cap flow
US8340886B2 (en) 2011-03-07 2012-12-25 General Electric Company System and method for transitioning between fuel supplies for a combustion system
US9046262B2 (en) * 2011-06-27 2015-06-02 General Electric Company Premixer fuel nozzle for gas turbine engine
US20140051028A1 (en) * 2012-08-16 2014-02-20 Daniel Edward Matejczyk Propellant compatible component for combustion device
US10480791B2 (en) 2014-07-31 2019-11-19 General Electric Company Fuel injector to facilitate reduced NOx emissions in a combustor system
GB201506017D0 (en) 2015-04-09 2015-05-27 Rolls Royce Plc Fuel injector system
WO2017116266A1 (fr) * 2015-12-30 2017-07-06 General Electric Company Buses à combustible liquide pour chambres de combustion à double carburant
US10775048B2 (en) 2017-03-15 2020-09-15 General Electric Company Fuel nozzle for a gas turbine engine
US10739006B2 (en) 2017-03-15 2020-08-11 General Electric Company Fuel nozzle for a gas turbine engine
DE102017217328A1 (de) * 2017-09-28 2019-03-28 Rolls-Royce Deutschland Ltd & Co Kg Düse mit axialer Verlängerung für eine Brennkammer eines Triebwerks
GB201820206D0 (en) * 2018-12-12 2019-01-23 Rolls Royce Plc A fuel spray nozzle
US11592177B2 (en) 2021-04-16 2023-02-28 General Electric Company Purging configuration for combustor mixing assembly
CN113513409B (zh) * 2021-08-20 2022-12-20 中国联合重型燃气轮机技术有限公司 用于燃气轮机的吹扫系统及其控制方法
GB202214143D0 (en) * 2022-09-28 2022-11-09 Rolls Royce Plc Gas turbine engine with an improved thermal management system
GB202214148D0 (en) 2022-09-28 2022-11-09 Rolls Royce Plc Gas turbine engine with improved heat management
GB202214153D0 (en) 2022-09-28 2022-11-09 Rolls Royce Plc Modulated heat management for geared gas turbine engines

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US6543235B1 (en) 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors

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US5243816A (en) * 1992-06-19 1993-09-14 Fuel Systems Textron, Inc. Self purging fuel injector
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5735117A (en) * 1995-08-18 1998-04-07 Fuel Systems Textron, Inc. Staged fuel injection system with shuttle valve and fuel injector therefor
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
GB9708662D0 (en) * 1997-04-30 1997-06-18 Rolls Royce Plc Fuel injector
DE59810159D1 (de) * 1998-02-26 2003-12-18 Alstom Switzerland Ltd Verfahren zum sicheren Entfernen von Flüssigbrennstoff aus dem Brennstoffsystem einer Gasturbine sowie Vorrichtung zur Durchführung des Verfahrens
US6125624A (en) * 1998-04-17 2000-10-03 Pratt & Whitney Canada Corp. Anti-coking fuel injector purging device
US6675583B2 (en) * 2000-10-04 2004-01-13 Capstone Turbine Corporation Combustion method
DE10219354A1 (de) * 2002-04-30 2003-11-13 Rolls Royce Deutschland Gasturbinenbrennkammer mit gezielter Kraftstoffeinbringung zur Verbesserung der Homogenität des Kraftstoff-Luft-Gemisches
US6735949B1 (en) * 2002-06-11 2004-05-18 General Electric Company Gas turbine engine combustor can with trapped vortex cavity
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US6898926B2 (en) * 2003-01-31 2005-05-31 General Electric Company Cooled purging fuel injectors
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Publication number Priority date Publication date Assignee Title
US6543235B1 (en) 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115095861A (zh) * 2022-06-17 2022-09-23 宁波方太厨具有限公司 燃烧器、燃烧器防堵塞方法和燃气灶具

Also Published As

Publication number Publication date
US20090255263A1 (en) 2009-10-15
US8443609B2 (en) 2013-05-21
DE102008014744A1 (de) 2009-09-24
EP2103876A3 (fr) 2013-07-03

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