EP1921376A1 - Sistème d'injection de carburant - Google Patents

Sistème d'injection de carburant Download PDF

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Publication number
EP1921376A1
EP1921376A1 EP06023273A EP06023273A EP1921376A1 EP 1921376 A1 EP1921376 A1 EP 1921376A1 EP 06023273 A EP06023273 A EP 06023273A EP 06023273 A EP06023273 A EP 06023273A EP 1921376 A1 EP1921376 A1 EP 1921376A1
Authority
EP
European Patent Office
Prior art keywords
fuel
swirler
outlet opening
injection system
passage
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Withdrawn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
EP06023273A
Other languages
German (de)
English (en)
Inventor
Nigel Wilbraham
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
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP06023273A priority Critical patent/EP1921376A1/fr
Publication of EP1921376A1 publication Critical patent/EP1921376A1/fr
Withdrawn legal-status Critical Current

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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 
    • 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NOx).
  • NOx nitrogen oxides
  • the first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction.
  • the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NOx is not excessively formed.
  • the second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NOx will be.
  • premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone.
  • the swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
  • US 5,865,024 describes a dual fuel mixer with axial swirlers including hollow vanes with internal cavities which are in flow communication with a gas manifold and also having a plurality of gas fuel passages connected to internal cavities to inject gaseous fuel into an air stream.
  • the project summary of the "Cleaner Fossil Fuels Programme” originates from an inter-company project between Alstom Power Technology Centre, and Alstom Power UK Ltd. in association with Cranfield University, School of Engineering and Queens University Harbor and describes a design with radial swirler including hollow vanes. Each vane has internal cavities and shows fuel injection openings aligned very close to the trailing edge and all arranged at the same distance from an exit of a fuel/air mixing passage.
  • the publication of the project summary can be obtained from the Department of Trade and Industry (dti) in the UK.
  • An object of the invention is to provide a new fuel injection system, especially for LCV fuel, allowing for a better control of the pre-mixing of gaseous fuel and compressor air when operating especially LCV fuels to provide a homogeneous fuel/air mixture and thereby reduce formation of NOx.
  • Another objective is to provide a swirler vane for an improved fuel injection system, especially for LCV fuels.
  • a third objective is to provide a burner with an improved fuel injection system, especially for LCV fuels.
  • a fourth objective is to provide a gas turbine with an improved fuel injection system, especially for LCV fuels.
  • This inventive fuel injection system is, that a small amount of the high volumetric flows of fuel, especially required for an LCV burner, hits and mixes with the compressor air earlier than the main part, thus improving the mixing of fuel and compressor air and consequently reducing the formation of pollutants and, at the same time, keeping the risk of blockage low without additional expenses in production.
  • the injection angle of the fuel jets in the inventive fuel injection system controlling the fuel penetration across the swirler passage, still is acute angled relative to the flow of compressor air so as to minimise the obstruction to the air flow through the burner at all machine load conditions.
  • slight adjustments in the fuel momentum perpendicular to the air cross-flow within the fuel/air mixing passage can have a marked impact on the final fuel mixing in the pre-chamber of the burner.
  • Such changes may be done in a controlled way through the angular displacement of one or more fuel outlet openings. Changes to the fuel penetration and mixing can be achieved through changes to the positioning of one or more of the multiple fuel injection openings in the fuel/air mixing passages.
  • Fuel/air mixing passages such as swirler passages are delimited by side faces of neighbouring swirler vanes, by the surface of a swirler vane support which is facing a burner head and by a surface of the burner head to which the swirler vanes are fixed.
  • a swirler passage extends from a compressor air inlet opening to an exit of the swirler passage positioned downstream from the compressor air inlet opening relative to the streaming direction of the compressed air.
  • an inventive swirler passage comprises a fuel injection system with at least one fluid passage where the corresponding fuel outlet opening is arranged in a side wall of the swirler passage close to the trailing edge of the side wall for injecting fuel into the swirler passage and at least one fluid passage, where the fuel outlet opening is arranged in a side wall of the swirler passage upstream, relative to the flow of compressor air, of the fuel outlet opening close to the trailing edge.
  • These fuel outlet openings are sized to allow the large volumetric fuel flows associated especially with low calorific value (LCV) fuels.
  • LCD calorific value
  • Figure 1 illustrates a longitudinal section through a combustor.
  • the combustor comprises relative to a flow direction: a burner with swirler 2 and a burner-head 1 attached to the swirler 2, a transition piece referred to as combustion pre-chamber 3 and a main combustion chamber 4.
  • the main chamber 4 has a diameter being larger than the diameter of the pre-chamber 3.
  • the combustion chamber 4 is connected to the pre-chamber 3 via a dome portion 10 comprising a dome plate 11.
  • the transition piece 3 may be implemented as a one part continuation of the burner head 1 towards the main chamber 4, as a one part continuation of the main chamber 4 towards the burner head 1, or as a separate part between the burner head 1 and the main chamber 4.
  • the burner head 1 and the main chamber 4 assembly show rotational symmetry about a longitudinally central axis 12.
  • a fuel conduit 5 is provided for leading fuel to the burner which is to be mixed with in-streaming air in the swirler 2.
  • the fuel/air mixture 7 is then guided towards the primary combustion zone 9 where it is burnt to form hot, pressurised exhaust gases streaming in a direction 8 indicated by arrows to a turbine of the gas turbine engine (not shown).
  • a prior art fuel injection system 13 namely a swirler 2 of a gas turbine engine for LCV fuels, includes a plurality of swirler vanes 19 and a swirler vane support 21.
  • the swirler vanes 19 are disposed about a central axis 12 and arranged on a swirler vane support 21 with a central opening 29.
  • Swirler passages 18 are defined between side faces 20 of adjacent swirler vanes 19 and the inflowing compressor air 6 passes through these to enter the pre-chamber 3.
  • the swirler passages 18 extend between compressor air inlet openings 26 and exits 17 at trailing edges of swirler vanes 19 relative to the flow of the compressor air 6.
  • FIG. 2 an entry of a swirler passage 18, in the following referred to as compressor air inlet opening 26, is indicated in dashed lines and an exit 17 of another swirler passage 18 is indicated in dotted lined.
  • compressor air 6 starts mixing with fuel which is added through first fuel outlet openings 14 aligned at the trailing edge of a side face 20 of a swirler vane 19.
  • Fuel and air enter the pre-chamber 3 with a swirling motion about the central axis 12 of the swirler 2.
  • FIG 3 illustrates the internal structure of prior art swirler vanes 19 of the swirler 2 as illustrated in Figure 2 .
  • Each first fuel outlet opening 14 connects through a first fluid passage 22 to a conduit 24, which is connected to a fuel supply (not shown).
  • the first fluid passages 22 of a swirler vane 19 are parallel to each other and have a narrower width than the conduit 24 to which they connect and extend inwardly from this conduit 24 at an inclined angle relative to a radial direction of the swirler 2.
  • the longitudinal axes 27 of these first fluid passages 22 are oriented such that the fuel enters the central opening 29 of the swirler 2 roughly tangentially to the edge of the central opening 29.
  • first and second fuel outlet openings 14,15 of the inventive swirler 2 do not align.
  • second fuel outlet openings 15 do not align with first fuel outlet openings 14 along an axis parallel to the central axis 12 of the swirler 2, as well as the corresponding first and second fluid passages 22,23 are not parallel to each other while still connecting to the same conduit 24. Therefore, first fuel outlet openings 14 are arranged closer to the exits 17 of the swirler passages 18 than the second fuel outlet openings 15.
  • Figure 5 depicts a swirler vane 19 according to the prior art including at least two fluid passages 22 where all fluid passages 22 have first longitudinal axes 27 aligned in parallel.
  • an inventive swirler vane 19 is shown. It comprises at least first and second fluid passages 22,23, wherein a second longitudinal axis 28 of the second fluid passage 23 forms an angle ⁇ relative to the first longitudinal axis 27 of the first fluid passage 22.
  • Figure 4 only shows one second fuel outlet opening 15 per swirler vane and the corresponding second fluid passage 23, clearly more than one second fluid passage 23 may be rotated about the conduit centre line 25. If more than one fluid passage 23 is rotated, not all fluid passages 23 need to be rotated by the same angle.
  • first and second fluid passages 22,23 are of reduced cross-section compared to an LCV design.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP06023273A 2006-11-08 2006-11-08 Sistème d'injection de carburant Withdrawn EP1921376A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06023273A EP1921376A1 (fr) 2006-11-08 2006-11-08 Sistème d'injection de carburant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06023273A EP1921376A1 (fr) 2006-11-08 2006-11-08 Sistème d'injection de carburant

Publications (1)

Publication Number Publication Date
EP1921376A1 true EP1921376A1 (fr) 2008-05-14

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ID=37832889

Family Applications (1)

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EP06023273A Withdrawn EP1921376A1 (fr) 2006-11-08 2006-11-08 Sistème d'injection de carburant

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EP (1) EP1921376A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246617A1 (fr) * 2009-04-29 2010-11-03 Siemens Aktiengesellschaft Brûleur pour moteur de turbine à gaz
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
CN104791846A (zh) * 2015-03-17 2015-07-22 上海交通大学 一种燃气轮机低污染燃烧室的低旋流预混喷嘴
CN106568083A (zh) * 2016-11-07 2017-04-19 北京航天石化技术装备工程有限公司 一种裂解炉用侧壁低氮氧化物燃气燃烧器
CN107466354A (zh) * 2015-04-01 2017-12-12 西门子股份公司 用于燃气涡轮发动机的旋流器、燃烧器和燃烧装置
EP3564585A1 (fr) * 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Agencement tourbillonnaire d'un brûleur

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2293001A (en) * 1994-09-12 1996-03-13 Gen Electric Dual fuel mixer for gas turbine combustor
EP0747635A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19532264A1 (de) * 1995-09-01 1997-03-06 Mtu Muenchen Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
EP0936406A2 (fr) * 1998-02-10 1999-08-18 General Electric Company Brûleur à prémélange combustible/air uniforme pour une combustion à faibles émissions
DE10043933A1 (de) * 2000-09-06 2002-03-14 Alstom Power Nv Verfahren zum Betrieb einer Gasturbine und Gasturbine
US20020174656A1 (en) * 1999-10-29 2002-11-28 Olaf Hein Turbine engine burner
EP1406047A1 (fr) * 2001-07-10 2004-04-07 Mitsubishi Heavy Industries, Ltd. Buse de premelange, bruleur et turbine a gaz

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2293001A (en) * 1994-09-12 1996-03-13 Gen Electric Dual fuel mixer for gas turbine combustor
EP0747635A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19532264A1 (de) * 1995-09-01 1997-03-06 Mtu Muenchen Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
EP0936406A2 (fr) * 1998-02-10 1999-08-18 General Electric Company Brûleur à prémélange combustible/air uniforme pour une combustion à faibles émissions
US20020174656A1 (en) * 1999-10-29 2002-11-28 Olaf Hein Turbine engine burner
DE10043933A1 (de) * 2000-09-06 2002-03-14 Alstom Power Nv Verfahren zum Betrieb einer Gasturbine und Gasturbine
EP1406047A1 (fr) * 2001-07-10 2004-04-07 Mitsubishi Heavy Industries, Ltd. Buse de premelange, bruleur et turbine a gaz

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246617A1 (fr) * 2009-04-29 2010-11-03 Siemens Aktiengesellschaft Brûleur pour moteur de turbine à gaz
US8739545B2 (en) 2009-04-29 2014-06-03 Siemens Aktiengesellschaft Burner for a gas turbine engine
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
CN104791846A (zh) * 2015-03-17 2015-07-22 上海交通大学 一种燃气轮机低污染燃烧室的低旋流预混喷嘴
CN107466354A (zh) * 2015-04-01 2017-12-12 西门子股份公司 用于燃气涡轮发动机的旋流器、燃烧器和燃烧装置
CN106568083A (zh) * 2016-11-07 2017-04-19 北京航天石化技术装备工程有限公司 一种裂解炉用侧壁低氮氧化物燃气燃烧器
CN106568083B (zh) * 2016-11-07 2018-11-30 北京航天石化技术装备工程有限公司 一种裂解炉用侧壁低氮氧化物燃气燃烧器
EP3564585A1 (fr) * 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Agencement tourbillonnaire d'un brûleur

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