EP1995521A1 - Wirbelblech - Google Patents

Wirbelblech Download PDF

Info

Publication number
EP1995521A1
EP1995521A1 EP07010376A EP07010376A EP1995521A1 EP 1995521 A1 EP1995521 A1 EP 1995521A1 EP 07010376 A EP07010376 A EP 07010376A EP 07010376 A EP07010376 A EP 07010376A EP 1995521 A1 EP1995521 A1 EP 1995521A1
Authority
EP
European Patent Office
Prior art keywords
swirler
swirler vane
vane
hole
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.)
Withdrawn
Application number
EP07010376A
Other languages
English (en)
French (fr)
Inventor
Paul Headland
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 EP07010376A priority Critical patent/EP1995521A1/de
Priority to PCT/EP2008/055777 priority patent/WO2008141959A1/en
Publication of EP1995521A1 publication Critical patent/EP1995521A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R3/10—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
    • 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
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/70—Baffles or like flow-disturbing devices
    • 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
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the invention relates to a swirler vane and a swirler, in particular for a gas turbine engine.
  • 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 NO x 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 NO x 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.
  • Figure 2 shows a prior art swirler of a gas turbine engine, comprising a plurality of swirler vanes disposed about a central axis and arranged on a swirler vane support with a central opening.
  • the swirler vanes can be fixed to a burner head (not shown) with their sides showing away from the swirler vane support.
  • Swirler passages are defined and delimited by opposing side faces of swirler vanes, by the surface of the swirler vane support which shows to the burner head and by a surface of the burner head to which the swirler vanes are fixed. Compressor air flows into these passages and starts mixing with fuel which is added through fuel injection openings (not shown). Further downstream, the fuel/air mixture enters the combustion zone with a swirling motion about the central axis of the swirler and is ignited by the heat of the combustion gases.
  • An object of the invention is to provide an improved swirler vane, in particular for a swirler in a gas turbine engine, which is advantageous in providing a homogeneous fuel/air mixture.
  • An inventive swirler vane comprises a through hole connecting at least two surfaces of the swirler vane.
  • the respective openings of the through hole are positioned on the respective side faces of the swirler vane.
  • the pressure gradients between swirler passages allow the fuel to pass from the high pressure to the low pressure sides of the swirler vanes and therefore provide a more even fuel distribution and an increased level of premix by cross flow between swirler passages which reduces the fraction of nitrous oxide in the exhaust gases of a gas turbine engine.
  • the through hole is tube-shaped
  • the invention may be implemented with other shapes.
  • the preferred location of the openings is at a height of between 10% and 90% of a swirler vane height.
  • the homogeneity of the fuel/air mixture over the cross sectional area of a swirler passage can be advantageously increased when respective openings are arranged at different swirler vane heights.
  • a further improvement is achieved by more than only one through hole per swirler vane.
  • the fuel injection system may either be a liquid fuel injection system or a gaseous fuel injection system.
  • the main outlet opening can be provided with turbulence elements, in particular if it is driven with gaseous fuel. Those elements may be present on the circumference of the openings and may e.g. comprise triangular cuts on the circumference.
  • the turbulence enhancing features provide additional mixing and direction of a gaseous fuel/air mixture leaving the through hole.
  • Openings arranged on the side faces of swirler vanes do not necessarily need to be arranged at the same radius about the central axis of the swirler vane support.
  • the invention may be implemented with openings having different distances to a central opening of the swirler vane support.
  • 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).
  • FIG. 2 A perspective view of a prior art swirler 2 is shown in Figure 2 .
  • the swirler comprises a ring-shaped swirler vane support 13 with a central opening 14.
  • Six swirler vanes 15 with pie slice shape are disposed about the central axis 12 and arranged on the swirler vane support 13.
  • the swirler vanes 15 can be fixed to the burner head (see Figure 1 ) with their sides showing away from the swirler vane support 13.
  • Swirler passages 16 are defined and delimited by opposing side faces 17 of swirler vanes 15, by the surface of the swirler vane support 13 which shows to the burner head and by a surface of the burner head to which the swirler vanes 15 are fixed.
  • Compressor air 6 flows into these swirler passages 16 and starts mixing with fuel which is added through fuel injection openings (not shown).
  • Figure 3 schematically shows a side view of an isolated inventive swirler vane 15 arranged on a swirler vane support 13.
  • the surface 20 of the swirler vane 15 shown is a side face 17 with openings 18 of through holes 19.
  • On the left is the edge of the outer surface 21 of the swirler vane 15. Compressor air 6 inflow is from this side and compressor air 6 flows along the surface 20 of the swirler vane 15 as indicated by the arrow.
  • the opening 18 on the right of Figure 3 comprises additional turbulence elements 22 for causing a turbulence of a fuel/air mixture guided through the through hole 19.
  • These elements 22 comprise triangular cuts 23 on the circumference of the opening 18.
  • Figure 4 shows a cut through the swirler vane 15 of Figure 3 , with swirler passages 16 delimited by the swirler vane support 13 and by side faces 17 of the swirler vane 15.
  • the through hole 19 can be straight and horizontal, as shown here, or inclined, as shown in Figure 5 , or curved (not shown) when using, for example, different production methods.
  • the preferred location of the openings 18 is at a height of between 10% and 90% of the swirler vane height.
  • Figures 6 and 7 show alternative embodiments of the inventive swirler vane 15 with through holes 19 not being tangential to a circle about the central axis 12 of the swirler 2, but with openings 18 of a through hole 19, the openings arranged at different radii 24, 25 about the central axis 12.
  • FIG 8 a perspective view of a swirler 2 with inventive swirler vanes 15 is shown. Twelve swirler vanes 15 are disposed about a central axis 12 and arranged on a swirler vane support 13. The top face of the swirler vanes 15 according to the orientation of the swirler vanes 15 as shown in Figure 8 would be connected to the burner head.
  • Figure 8 shows an embodiment of the inventive swirler vanes 15 with openings 18 arranged on the side faces 17 as well as on curved outer surfaces 21 of the swirler vanes 15.
  • compressor air 6 is introduced through a plenum (not shown) and flows through the swirler passages 16 with a pressure gradient from the accelerating flow towards the central opening 14 of the swirler vane support 13.
  • the pressure gradient generates a rotating flow, with a cork screw like appearance, as the flow moves from the outside towards the central opening 14 of the swirler 2.
  • a pressure gradient in the through holes 19 between swirler passages 16 allows the fuel to pass from the high pressure side to the low pressure side of a swirler vane 15 to more evenly distribute the fuel.
  • Some fraction of the compressor air enters the swirler passages 16 via through holes 19 with openings 18 arranged on curved outer surfaces 21 of the swirler vanes 15 and with openings 20 arranged on side faces 17 of the swirler vanes 15, thus creating additional turbulence in the swirler passages 16 which in turn further improves the mixing of fuel and air.
  • the fuel/air mixture 7 then leaves the swirler passages 16 and streams through a central opening 14 of the swirler vane support 13 into the pre-chamber 3 (see Figure 1 ). From the pre-chamber 3 the fuel/air mixture 7 streams into the combustion zone 9 of the main chamber 4 where it is burned.
  • the swirler 2 of the present embodiment has twelve swirler vanes 15, the invention may be implemented with a swirler 2 having a different number of swirler vanes 15, which may either be higher or lower than in the described embodiment.
  • the side faces 17 of the swirler vanes 15 may be curved, as shown in Figure 8 , or straight, as shown in Figure 2 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP07010376A 2007-05-24 2007-05-24 Wirbelblech Withdrawn EP1995521A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07010376A EP1995521A1 (de) 2007-05-24 2007-05-24 Wirbelblech
PCT/EP2008/055777 WO2008141959A1 (en) 2007-05-24 2008-05-09 Swirler vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07010376A EP1995521A1 (de) 2007-05-24 2007-05-24 Wirbelblech

Publications (1)

Publication Number Publication Date
EP1995521A1 true EP1995521A1 (de) 2008-11-26

Family

ID=38596884

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07010376A Withdrawn EP1995521A1 (de) 2007-05-24 2007-05-24 Wirbelblech

Country Status (2)

Country Link
EP (1) EP1995521A1 (de)
WO (1) WO2008141959A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009168439A (ja) * 2008-01-18 2009-07-30 General Electric Co <Ge> ガスタービン燃焼器用のスウォズル設計
CN103134080A (zh) * 2011-11-23 2013-06-05 通用电气公司 具有对轮叶表面进行压缩机排气喷射的旋流器组件
RU2498160C2 (ru) * 2009-04-29 2013-11-10 Сименс Акциенгезелльшафт Горелка для газотурбинного двигателя
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1160902A (fr) * 1956-02-10 1958-08-13 Dispositif dit turbulateur pour brûleur à mazout ou à gaz, particulièrement pourflammes ouvertes à insufflation d'air par pales hélicoïdales
US5511375A (en) * 1994-09-12 1996-04-30 General Electric Company Dual fuel mixer for gas turbine combustor
EP0828115A1 (de) * 1996-09-05 1998-03-11 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Brennstoffeinspritzsystem für eine Brennkammer
US5816049A (en) * 1997-01-02 1998-10-06 General Electric Company Dual fuel mixer for gas turbine combustor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1160902A (fr) * 1956-02-10 1958-08-13 Dispositif dit turbulateur pour brûleur à mazout ou à gaz, particulièrement pourflammes ouvertes à insufflation d'air par pales hélicoïdales
US5511375A (en) * 1994-09-12 1996-04-30 General Electric Company Dual fuel mixer for gas turbine combustor
EP0828115A1 (de) * 1996-09-05 1998-03-11 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Brennstoffeinspritzsystem für eine Brennkammer
US5816049A (en) * 1997-01-02 1998-10-06 General Electric Company Dual fuel mixer for gas turbine combustor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009168439A (ja) * 2008-01-18 2009-07-30 General Electric Co <Ge> ガスタービン燃焼器用のスウォズル設計
RU2498160C2 (ru) * 2009-04-29 2013-11-10 Сименс Акциенгезелльшафт Горелка для газотурбинного двигателя
US8739545B2 (en) 2009-04-29 2014-06-03 Siemens Aktiengesellschaft Burner for a gas turbine engine
CN103134080A (zh) * 2011-11-23 2013-06-05 通用电气公司 具有对轮叶表面进行压缩机排气喷射的旋流器组件
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

Also Published As

Publication number Publication date
WO2008141959A1 (en) 2008-11-27

Similar Documents

Publication Publication Date Title
US8316644B2 (en) Burner having swirler with corrugated downstream wall sections
EP3182013B1 (de) Brenner für eine sequentielle brennkammer
EP2522911B1 (de) Brenner mit lobe drallerzeuger
EP1892469B1 (de) Drallerzeugerkanal und Brenner für eine Gasturbine
EP1488086B1 (de) Trockenverbrennungssystem mit niedrigem ausstoss und mitteln zur beseitung von verbrennungslärm
RU2304741C2 (ru) Устройство топливной форсунки (варианты) и способ его создания
US8579214B2 (en) Swirler vane
US8528313B2 (en) Burner for a second chamber of a gas turbine plant
EP2427696B1 (de) Drallkörper, brennkammer und gasturbine mit verbesserter vermischung
US8387393B2 (en) Flashback resistant fuel injection system
US20080041060A1 (en) Fuel injector for a gas turbine engine
US6684640B2 (en) Gas turbine engine combustion system
CN1118858A (zh) 预混燃烧器
EP1918638A1 (de) Brenner, insbesondere für eine Gasturbine
CN101813315A (zh) 用于燃气轮机燃烧器的同轴式燃料和空气预混合器
US20100175381A1 (en) Swirler
RU2690598C2 (ru) Завихритель, горелка и система сгорания для газотурбинного двигателя
US20160061452A1 (en) Corrugated cyclone mixer assembly to facilitate reduced nox emissions and improve operability in a combustor system
EP1995521A1 (de) Wirbelblech
EP1921376A1 (de) Brennstoffeinspritzsystem
EP2340398B1 (de) Hauptdrallvorrichtungen mit abwechselnder drallrichtung in magervorgemischten gasturbinenbrennkammern
CN115854386A (zh) 浮动初级轮叶旋流器
CN115711176A (zh) 具有集成喇叭形旋流器的圆顶

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20090527