US20100316966A1 - Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement - Google Patents

Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement Download PDF

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Publication number
US20100316966A1
US20100316966A1 US12/814,707 US81470710A US2010316966A1 US 20100316966 A1 US20100316966 A1 US 20100316966A1 US 81470710 A US81470710 A US 81470710A US 2010316966 A1 US2010316966 A1 US 2010316966A1
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US
United States
Prior art keywords
flow
supply channel
burner
burner arrangement
fuel
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.)
Abandoned
Application number
US12/814,707
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English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Ulrich Wörz
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.)
Siemens AG
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Siemens AG
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Filing date
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOETTCHER, ANDREAS, KRIEGER, TOBIAS, WOERZ, ULRICH
Publication of US20100316966A1 publication Critical patent/US20100316966A1/en
Abandoned 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the invention relates to a burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement with the features cited in the preambles of the respective independent claims.
  • burners were developed over the last few years which have particularly minimal nitrogen oxide (NOx) emissions.
  • NOx nitrogen oxide
  • Such burners are described for instance in EP 0 276 696 B1.
  • inert substances in particular water or water vapor
  • WO 89/08803 A1 also discloses that with the use of heavy oils as fuel, for example, admixtures should also be mixed with the injected substances in order to prevent damage to components of a subsequent gas turbine.
  • EP 0 276 696 B1 discloses a hybrid burner for premixing operation with gas and/or oil, like is used in particular for gas turbine systems.
  • the burner consists of a central pilot burner system, which can be operated with gas and/or oil as a so-called diffusion burner or a separate premix burner. Provision is also made for the possibility of feeding inert substances.
  • the pilot burner system is surrounded by a main burner system, which has an air supply annular channel system with a helical blading located therein having a plurality of blades for the premixing operation with gas.
  • Inlet nozzles for oil are also present in the region of the helical blading in the main burner system, thereby enabling the main air flow to be premixed with oil.
  • An annular gas compartment supplies the main burner in respect of the flow direction of the inflowing air on the input side upstream of the so-called helical blades, which convey a mixed helix to the air flow with the combustion gas or through the helical blades.
  • An oil supply is also available as the gas supply, which is generally arranged in the vicinity of the burner outlet. It includes an annular oil compartment, and an oil supply channel leading to the annular compartment, which is arranged in the hub wall located between the annular gas compartment and the pilot burner.
  • gas has a lower density than oil, it requires a larger cross-section, as a result of which the dimensioning of the gas supply is considerably larger than the oil supply.
  • the part of the burner hub with the gas supply therefore has a larger external surface facing the air channel than the oil supply.
  • the air supply takes place with precompressed air, which has passed through a compressor, as a result of which this supplied air has a temperature, as a result of the compression, which already reaches above 400° C.
  • the region of the burner hub with the gas supply is consequently rapidly heated to a temperature in the region of above 400° C. and remains at this operating temperature.
  • the oil supply channel leading to the annular oil compartment is by contrast distanced far from the hot air supply channel so that the oil in the oil supply channel barely experiences any heating and thus only has a temperature of approximately 50° C.
  • the burner hub experiences a strong heating in the region of the annular gas compartment and, on the other hand, the adjacent oil supply channel is considerably cooler, the wall between the annular gas compartment and the oil supply channel is subjected to a large temperature gradient both during continual operation and also when flushing out the burner hub. If the hub, i.e. the oil channel, is flushed with water, the gas channels remain hot and the oil channel cools down significantly. The channels are very close to one another as a result of the limited space in the hub and high temperature/thermal gradients result. As a result of the temperature gradient, thermal stresses result, which significantly shorten the service life of such burner hubs.
  • the object of the present invention is thus to reduce the described thermally specific stresses in the burner hub during operation and when flushing the hub of the burner arrangement.
  • An inventive burner arrangement for a combustion system for combusting liquid fuels includes a burner hub, at least one air supply channel and at least one fuel supply channel for each type of fuel.
  • the at least one fuel supply channel is embodied at least partially in the burner hub, so that the material of the burner hub forms a wall of the fuel supply channel.
  • a flow divider is provided in at least one fuel supply channel, said flow divider being distanced from the wall of the fuel supply channel so that an interspace associated with the flow path of the fuel flowing through the fuel supply channel is formed between the wall of the fuel supply channel and the flow divider.
  • the interspace forms a region associated with the flow path, in which an adjustable continual fuel flow flows.
  • This fuel flow prevents deposits from forming in the interspace and thus prevents a blockage of the nozzles through which the fuel escapes.
  • the flow in this region decouples the hot structure from the cold structure and thus represents a heat shield.
  • the flow divider consists of a flow-through means, in particular a pipe with a flow-through opening, and a disk with a corresponding flow-through opening.
  • a central bore in the center of the flow divider is preferably provided as a flow-through opening. The majority of the fuel flows through this central bore.
  • the disk When viewed in the flow direction, the disk is also provided at the first end on the flow-through means.
  • the disk has a larger diameter than the diameter of the flow-through means.
  • the disk can be clamped here in the wall of the fuel supply channel.
  • Positioning means e.g. a positioning projection, can however also be provided on the wall of the fuel supply channel.
  • the flow divider in the disk preferably has at least one bore.
  • the disk also has several bores, which are essentially distributed equally over the periphery. These bores route a small part of the preferably cold fuel flow into the interspace, with the hot carrier structure thus being thermally decoupled from the inflowing cold fuel. The heat transfer in this region is thus reduced.
  • said object is achieved by a method for operating such a burner arrangement, with, during operation, fuel being routed through the fuel supply channel, with the majority of the fuel flowing through the flow-through opening of the flow divider and a small part of the fuel flowing through the interspace of the flow divider, thereby largely preventing deposits in the interspace.
  • a small part of the flow is thus routed through the interspace and thus prevents the formation of deposits in the interspace, in other words, above all on the wall of the carrier structure of the combustion chamber hub. A blockage of the nozzles is thus prevented.
  • a function as a heat protection shield is provided, since the hot carrier structure is thermally decoupled from the inflowing cold fuel, in particular from cold oil.
  • the main flow for supplying the nozzles flows through the flow-through opening of the flow divider, with this flow-through opening preferably being provided as a large, central bore in the center of the flow divider. High temperatures and stress gradients therefore no longer form. A significant increase in the service life is the desired result.
  • FIG. 1 shows a burner arrangement known from EP 0 580 683 B1
  • FIG. 2 shows a partial cross-sectional view through a known burner arrangement
  • FIG. 3 shows a basic diagram of an inventive helical blade with two integrated gas stages which can be controlled independently of one another
  • FIG. 4 shows a basic diagram of a burner chamber hub with two integrated gas stages, which can be controlled independently of one another and an oil channel,
  • FIG. 5 shows a burner chamber hub 18 with an inventive flow divider 40
  • FIG. 6 shows an inventive flow divider 40 .
  • FIG. 1 shows a burner arrangement 20 as claimed in the prior art, which, if necessary in conjunction with several similar arrangements, can be used in the combustion chamber of a gas turbine system for instance.
  • the pilot burner system consists of an inner part, the pilot burner system and an outer part, the main burner system, which is disposed concentrically thereto. Both systems are suited to operation with gaseous and/or liquid fuels in any combination.
  • the pilot burner system consists of a central oil supply 1 (medium G) and an inner gas supply channel 2 (medium F) arranged concentrically around the latter. This is in turn surrounded by an inner air supply channel 3 (medium E) which is arranged concentrically around the axis of the burner.
  • a suitable ignition system can be arranged in or on this channel, for which many embodiment possibilities are known and the representation thereof was therefore omitted here.
  • the central oil supply 1 has an oil nozzle 5 at its end and the inner air supply channel 3 has a helical blading 6 in its end region.
  • a pilot burner system 1 , 2 , 3 , 5 , 6 can be operated in a manner known per se, i.e. predominantly as a diffusion burner. Its task is to keep the main burner stable during combustion, since this is mostly operated with a lean mixture which tends towards instabilities.
  • the main burner system has an outer air supply annular channel system 4 which is arranged concentrically with respect to the pilot burner system and runs obliquely thereto.
  • This air supply annular channel system 4 is also provided with a helical blading 7 .
  • the helical blading 7 consists of hollow blades with outlet nozzles 11 in the flow cross-section of the air supply annular channel system 4 (medium A). These are fed from a supply line 8 and an annular channel 9 through openings 10 for the medium B.
  • the burner also has a supply line 12 for a medium C, preferably oil, which opens into an annular channel 13 , which has outlet nozzles 14 for the medium C in the region or below the helical blading 7 .
  • a spray jet 15 of the medium C is also shown.
  • the burner also has a further coal gas supply channel 16 for medium D. This opens into the outer air supply annular channel system 4 , just above the helical blading 7 with the outlet nozzles 11 , and on its internal side, so that in principle both together form a diffusion burner.
  • FIG. 2 shows an enlarged partial cross-sectional view through a known burner hub 18 as claimed in the prior art.
  • the burner arrangement is circular, so that the annular channel 9 and 13 can also be represented as circular.
  • the region of the main burner in FIG. 1 can also be realized similarly.
  • the helical blades 9 only have a supply channel with the outlet nozzles 11 , which are preferably provided to inject a gaseous medium B.
  • An outlet nozzle 14 for injecting preferably liquid medium V is provided therebelow in the flow direction.
  • a plurality of outlet nozzles 14 is arranged along the circular annular channel 13 , so that the injection of the medium C can take place equally in the similarly circular combustion chamber.
  • this representation nevertheless only has one gas supply line and one oil supply line.
  • FIG. 3 shows a basic diagram of a helical blade 7 with two integrated gas stages B and D which can be controlled independently of one another.
  • the helical blade 7 has two supply channels 11 and 21 which are independent of one another.
  • the one supply channel with the outlet nozzles 11 can be used to inject the medium D for instance and the second supply channel 21 can be used to inject the medium B by way of the outlet nozzles 24 .
  • Both mediums to be injected through the supply channels of the helical blade 7 are preferably gaseous, e.g. the one natural gas and the other coal gas.
  • An inert substance such as water vapor for instance can similarly be injected by way of these outlet nozzles 11 and/or 21 as required.
  • FIG. 4 shows a fuel hub 18 with the supply channel 16 , the annular channels 9 and 13 and openings 10 , which lead the fuel into the blade 7 .
  • FIG. 5 shows an inventive fuel hub 18 with a flow divider 40 .
  • the flow divider 40 ( FIG. 6 ) consists of a pipe 45 with a flow-through opening 55 (subsequently referred to as pipe opening 55 ).
  • a disk 42 is attached to the first end of the pipe 45 when viewed in the flow direction.
  • the disk 42 likewise has a pipe opening 55 , which corresponds to the pipe opening 55 .
  • the diameter of the disk 42 is larger than the diameter of the pipe 45 .
  • the disk 42 can essentially be attached e.g. clamped to the wall 21 in a faun-fit manner.
  • the embodiment of a positioning projection 35 is also possible, on which the disk 42 rests.
  • Bores 50 are attached in the disk 42 . These bores 50 are preferably evenly distributed over the periphery.
  • a fluid flow is divided. An adjustable small part of the flow is routed through these smaller bores 50 into the interspace 38 . This fluid flow thus prevents the formation of deposits in the interspace 38 and a blockage of the nozzles 14 .
  • the minimal flow also functions as a heat protection pipe.
  • the reduced flow in this region decouples the hot structure from the code and thus represents a heat shield.
  • the hot carrier structure is thus thermally decoupled from the inflowing fuel, preferably cold oil.
  • the main flow for supplying the nozzles 14 also flows through the pipe opening 55 .
  • This is preferably realized as a central bore in the center of the flow divider 40 .
  • the thermal transfer a in the interspace is essentially less than the thermal transfer ⁇ previous without the flow divider at the same point; therefore ⁇ previous .
  • the main flow for supplying the nozzle 14 nevertheless also flows through the central bore, in other words through the pipe opening 55 .
  • the thermal transfer ⁇ essentially remains unchanged here, i.e. ⁇ previous .
  • the flow divider 40 therefore functions as a heat protection shield and the hot carrier structure is thus decoupled from the inflowing cold oil. High temperature and tensile gradients therefore no longer form. The service life of the combustion chamber hub 19 is thus significantly increased.
  • the inventive flow divider 40 thus divides the fluid flow namely into a minimal flow, which flows through the interspace 38 and a quantitative main flow, which flows through the pipe opening 55 .
  • the flow divider 40 thus prevents deposits and a blockage of nozzles when using liquid fuels.
  • the reduced flow also decouples the hot structure from the cold and thus represents a heat shield.
  • high thermal gradients and thermal stresses resulting therefrom are prevented by way of a minimal cross-section.
  • the component 18 can thus fulfill the high demands in terms of service life.
  • the flow divider 40 is simple to manufacture and easy to adapt in existing fuel chamber hubs 18 .

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  • 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)
US12/814,707 2009-06-16 2010-06-14 Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement Abandoned US20100316966A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP09162827.1 2009-06-16
EP09162827A EP2264370B1 (de) 2009-06-16 2009-06-16 Brenneranordnung für eine Verfeuerungsanlage zum Verfeuern fluidischer Brennstoffe und Verfahren zum Betrieb einer solchen Brenneranordnung

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US20100316966A1 true US20100316966A1 (en) 2010-12-16

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US12/814,707 Abandoned US20100316966A1 (en) 2009-06-16 2010-06-14 Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement

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US (1) US20100316966A1 (ru)
EP (1) EP2264370B1 (ru)
CN (1) CN101922714B (ru)
RU (1) RU2531714C2 (ru)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160252254A1 (en) * 2013-10-31 2016-09-01 Siemens Aktiengesellschaft Gas turbine burner hub with pilot burner
US10414005B2 (en) 2014-04-09 2019-09-17 General Electric Company Method and apparatus for servicing combustion liners
RU2813936C1 (ru) * 2023-03-31 2024-02-19 Общество с ограниченной ответственностью "КОТЭС Инжиниринг" Коаксиальная ступенчатая горелка факельного сжигания топливовоздушной смеси

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2952814A1 (de) * 2014-06-04 2015-12-09 Siemens Aktiengesellschaft Brenneranordnung mit Resonator
JP7200077B2 (ja) * 2019-10-01 2023-01-06 三菱重工業株式会社 ガスタービン燃焼器及びその運転方法
KR102382634B1 (ko) * 2020-12-22 2022-04-01 두산중공업 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
DE102022207492A1 (de) * 2022-07-21 2024-02-01 Rolls-Royce Deutschland Ltd & Co Kg Düsenvorrichtung zur Zugabe zumindest eines gasförmigen Kraftstoffes und eines flüssigen Kraftstoffes, Set, Zuleitungssystem und Gasturbinenanordnung

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US1262351A (en) * 1915-11-01 1918-04-09 F L Wildes Cutting and welding torch.
US1593186A (en) * 1922-06-22 1926-07-20 Mckean John Graves Atomizer for liquid fuel and the like
US1552558A (en) * 1923-10-20 1925-09-08 James F Guthrie Oil burner
US1596577A (en) * 1926-01-02 1926-08-17 John S Burns Oil burner
US1940343A (en) * 1928-10-29 1933-12-19 Nat Welders Mfg And Supply Com Interchangeable torch
US2224171A (en) * 1939-08-07 1940-12-10 William Van Triest Automatic fuel control for scarfing torches and the like
US2517641A (en) * 1946-02-19 1950-08-08 Dod Cedric Oxygen jet metal-cutting nozzle
US2838105A (en) * 1953-09-18 1958-06-10 Texas Co Burner for the production of carbon monoxide and hydrogen
US3002341A (en) * 1957-12-31 1961-10-03 Boeing Co Jet engine noise suppression nozzles
US2979126A (en) * 1959-03-25 1961-04-11 Gen Motors Corp Flame pulsation suppressor for inshot gas burners
US3283802A (en) * 1964-06-11 1966-11-08 Fuel Firing Ltd Multi-stage burner unit
US3477644A (en) * 1968-03-06 1969-11-11 Little Inc A Liquid fuel burner
US3848807A (en) * 1973-12-10 1974-11-19 P Partida Confining nozzle for spray gun
US4095748A (en) * 1975-07-04 1978-06-20 Kanebo, Ltd. Apparatus for mixing a cement slurry with a glass fiber
US4284242A (en) * 1976-10-08 1981-08-18 Coal Industry (Patents) Limited Spray head
US4155701A (en) * 1977-09-26 1979-05-22 The Trane Company Variable capacity burner assembly
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US4340180A (en) * 1980-12-03 1982-07-20 Maxon Corporation Nozzle mixing line burner
US5186620A (en) * 1991-04-01 1993-02-16 Beckett Gas, Inc. Gas burner nozzle
US5417069A (en) * 1993-06-03 1995-05-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Separator for an annular gas turbine combustion chamber
US5873524A (en) * 1995-07-28 1999-02-23 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Process and device for spraying a liquid product
US6089171A (en) * 1996-07-08 2000-07-18 Combustion Engineering, Inc. Minimum recirculation flame control (MRFC) pulverized solid fuel nozzle tip
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US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US6736635B1 (en) * 1999-11-02 2004-05-18 Ebara Corporation Combustor for exhaust gas treatment
US20090325111A1 (en) * 2001-05-30 2009-12-31 Prysmian Cavi E Sistemi Energia S.R.L. Method and burner for manufacturing a glass optical fibre preform by vapour deposition
US6439136B1 (en) * 2001-07-03 2002-08-27 Alstom (Switzerland) Ltd Pulverized solid fuel nozzle tip with ceramic component
US20070131796A1 (en) * 2005-12-08 2007-06-14 General Electric Company Drilled and integrated secondary fuel nozzle and manufacturing method
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US20090301092A1 (en) * 2006-12-13 2009-12-10 Nigel Wilbraham Burners for a gas turbine engine
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US20160252254A1 (en) * 2013-10-31 2016-09-01 Siemens Aktiengesellschaft Gas turbine burner hub with pilot burner
US10414005B2 (en) 2014-04-09 2019-09-17 General Electric Company Method and apparatus for servicing combustion liners
RU2813936C1 (ru) * 2023-03-31 2024-02-19 Общество с ограниченной ответственностью "КОТЭС Инжиниринг" Коаксиальная ступенчатая горелка факельного сжигания топливовоздушной смеси

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EP2264370A1 (de) 2010-12-22
RU2010124411A (ru) 2011-12-20
CN101922714B (zh) 2014-12-17
EP2264370B1 (de) 2012-10-10
RU2531714C2 (ru) 2014-10-27
CN101922714A (zh) 2010-12-22

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