EP0916894B1 - Brûleur pour la mise en oeuvre d'un générateur de chaleur - Google Patents

Brûleur pour la mise en oeuvre d'un générateur de chaleur Download PDF

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Publication number
EP0916894B1
EP0916894B1 EP97810867A EP97810867A EP0916894B1 EP 0916894 B1 EP0916894 B1 EP 0916894B1 EP 97810867 A EP97810867 A EP 97810867A EP 97810867 A EP97810867 A EP 97810867A EP 0916894 B1 EP0916894 B1 EP 0916894B1
Authority
EP
European Patent Office
Prior art keywords
section
flow
burner according
swirl generator
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.)
Expired - Lifetime
Application number
EP97810867A
Other languages
German (de)
English (en)
Other versions
EP0916894A1 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
Thomas Ruck
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.)
General Electric Technology GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP97810867A priority Critical patent/EP0916894B1/fr
Priority to DE59710788T priority patent/DE59710788D1/de
Priority to US09/187,343 priority patent/US6027331A/en
Priority to JP32224098A priority patent/JP4263278B2/ja
Priority to CNB981269826A priority patent/CN1137342C/zh
Publication of EP0916894A1 publication Critical patent/EP0916894A1/fr
Application granted granted Critical
Publication of EP0916894B1 publication Critical patent/EP0916894B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • 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
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • 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

Definitions

  • the invention relates to a burner for the operation of a heat generator according to Preamble of claim 1.
  • the upstream side consists of a swirl generator, the flow formed therein seamlessly in a mixing section is transferred. This is done using one at the beginning of the Mixing section formed for this purpose flow geometry, which Transition channels exist, which are sectoral, according to the number of acting Partial body of the swirl generator, capture the end face of the mixing section and in Flow direction swirl.
  • the mixing section On the outflow side of these transition channels the mixing section has a number of filming holes, which one Ensure an increase in the flow velocity along the pipe wall.
  • a combustion chamber the transition between the Mixing section and the combustion chamber formed by a cross-sectional jump in whose plane a backflow zone or backflow bubble forms.
  • the Twist strength in the swirl generator is selected so that the bursting of the Vortex does not occur within the mixing section, but further downstream, as Executed above, in the area of the cross-sectional jump.
  • EP-A2-747 635 discloses a premix burner with a radial swirl generator for a gas turbine.
  • these swirl generating blades are openings available for fuel injection. This type of premixing leads to a lean one Fuel / air mixture with the advantage of combustion with low emissions.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose the above-mentioned type of precautions which affect the quality of the mixture Fuel / air mixture can improve.
  • the fuel in the swirl generator is injected on both sides along the inlet channels through which the combustion air flows into the interior.
  • the main advantages of the invention can be seen in the fact that the fuel injection provided on both sides of the inlet channels achieves a better penetration depth of the fuel into the combustion stream, which leads to a better premixing between fuel and combustion air.
  • the injection levels of the two rows of fuel injectors at the transition to the interior of the Swirl generator are arranged from the tip to the exit of the swirl generator increases. This is the route until it enters the swirl generator of fuel injectors further downstream, this leads to a better premixing of the injected fuel.
  • the object according to the invention is also particularly suitable for use in the case of other burners in which the swirl generator is also the premixing section of the burner.
  • the swirl generator is also the premixing section of the burner.
  • particular reference is made to the Document EP-0 321 809 B1 pointed out, which is an integrating component This description forms.
  • Fig. 1 shows the overall structure of a burner.
  • the top of the burner is a Swirl generator 100 effective, the design of which is shown in the following FIG. 2 and 3 is shown and described in more detail.
  • It is a conical body that is tangential multiple times in the circumferential direction of one incoming combustion air flow 115 is applied, in the area the inflow of this combustion air 115 different injections 116, 116a of a gaseous and / or liquid fuel are available:
  • FIGS. 2 and 3 Another fuel injection can through a central and head-mounted fuel nozzle 103 can be accomplished.
  • operation with a liquid and / or gaseous fuel are maintained.
  • the one forming here Swirl flow is provided on the basis of a swirl generator 100 downstream Transition geometry seamlessly transferred into a transition piece 200, that no detachment areas can form in this zone.
  • the configuration this transition geometry is described in more detail in FIG. 4. outflow side this transition piece 200 becomes the transition geometry which is thereby formed extended by a mixing tube 20, both parts of the actual Form mixing section 220 of the burner.
  • the mixing section 220 consist of a single piece, i.e. then that transition piece 200 and the mixing tube 20 into a single coherent Bodies merge, keeping the characteristics of each part.
  • transition piece 200 and mixing tube 20 are made from two parts, so these are connected by a bushing ring 10, the same bushing ring 10 serves as an anchoring surface for the swirl generator 100 on the head side.
  • Such sleeve ring 10 also has the advantage that different mixing tubes can be used without affecting the basic configuration of the burner to have to change something.
  • Downstream of the mixing tube 20 is the actual combustion chamber 30 of a combustion chamber, which is here only by a Flame tube is shown.
  • the mixing section 220 largely fulfills the task that a defined distance is provided downstream of the swirl generator 100 in which achieves a perfect premixing of different types of fuel can be.
  • This mixing section that is to say, the mixing tube 20, enables furthermore a loss-free flow guidance, so that there is also an operative connection with the transition geometry initially no backflow zone or Backflow bubble can form, which over the length of the mixing section 220 on the Mixing quality can be exercised for all types of fuel.
  • This Mixing section 220 has yet another property, which consists in that the axial velocity profile has a pronounced maximum in it has the axis so that the flame reignites from the combustion chamber not possible. However, it is correct that with such a configuration this Axial velocity drops towards the wall. To reignite this too, the mixing tube 20 in the flow and circumferential direction with a number of regularly or irregularly distributed bores 21 various cross sections and directions through which an amount of air flows into the interior of the mixing tube 20, and along the wall in the sense induce an increase in flow velocity during filming. This Bores 21 can also be designed so that on the inner wall of the mixing tube 20 at least additionally sets an effusion cooling.
  • transition channels 201 Another way of increasing the speed of the mixture within To achieve the mixing tube 20 is that its flow cross-section on the outflow side of the transition channels 201, which are those already mentioned Form transition geometry, undergoes a narrowing, causing the whole Speed level within the mixing tube 20 is raised.
  • these bores 21 run at an acute angle the burner axis 60.
  • the outlet corresponds to the transition channels 201 the narrowest flow cross section of the mixing tube 20.
  • the transition channels mentioned 201 accordingly bridge the respective cross-sectional difference, without negatively influencing the flow formed. If the chosen precaution when guiding the pipe flow 40 along the mixing pipe 20 triggers an intolerable pressure loss, this can be remedied be created by not at the end of this mixing tube in the figure shown diffuser is provided.
  • combustion chamber 30 combustion chamber 30
  • Backflow zone 50 which has the properties of a flame front disembodied flame holder.
  • FIG. 2 shows a swirl generator constructed from four partial bodies 140, 141, 142, 143 100, these partial bodies having a blade profile shape, with which a targeted flow for the through the respective inlet channels 120 into the interior 114 incoming combustion air flow 115 is accomplished.
  • the Flow cross-section of the inlet channels 120 is determined by the displacement of the respective Central axes 141a, 142a, 143a, 144a of the partial body are achieved, as shown in FIG. 2 emerges particularly well.
  • the fuel 116, 116a in the swirl generator is on both sides injected along the inlet channels 120. The closer type of injection goes from the explanations under Fig. 3.
  • FIG. 3 shows a perspective illustration of a four-slot swirl generator 100.
  • the introduction of fuel 116, 116a for admixing into the combustion air flow 115 is accomplished here by means of fuel lines, which are integrated into the partial bodies 140-143, in contrast to the fuel supply according to EP-0 780 629 A2.
  • the bilateral fuel supply along the inlet channels 120 is held here in such a way that the individual opposite ones Injections are arranged axially offset from one another. In order to it is achieved that the intermediate space between two injections on the one side from the opposite offset injection on the other Page is filled. This is important as this is the fuel injected captured by the combustion air stream 115 forms a bubble spray.
  • Opposing staggered fuel bubbles are able to fill the entire cross section of the inlet channels 120, the depth of penetration of the entered Fuel is larger, which has a positive effect on the fuel / combustion air mixture formation effect.
  • Optimizing mixture formation affects the design of the injection level H of the fuel 116, 116a in the axial direction of the swirl generator 100. This increases from the tip of the swirl generator 100 to the swirl generator outlet.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 2 and 3, built. Accordingly, the transition geometry four transition channels as a natural extension of the upstream part 201 on, whereby the conical quarter area of said partial body is extended until it cuts the wall of the mixing tube.
  • the same reasoning also apply if the swirl generator is based on a principle other than the one below Fig. 3 is constructed.
  • the down in the flow direction running surface of the individual transition channels 201 has a flow direction spiral shape, which has a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 flared in the direction of flow.
  • the swirl angle of the transition channels 201 in the flow direction is selected that the pipe flow then up to the cross-sectional jump on Combustion chamber entry still has a sufficient distance to be perfect Premix with the injected fuel. Furthermore increased the axial speed due to the above-mentioned measures on the mixing tube wall downstream of the swirl generator.
  • the transition geometry and the measures in the area of the mixing tube cause a significant increase the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.
  • Fig. 5 shows the tear-off edge already mentioned, which exits at the burner is formed.
  • the flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends.
  • This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply.
  • the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20.
  • the backflow bladder 50 increases enormously.
  • This radius R runs to the exit plane of the tube 20, the angle ⁇ between the beginning and end of curvature is ⁇ 90 °.
  • the tear-off edge A runs inside the tube 20 and thus forms a tear-off step S opposite the front point of the tear-off edge A, whose depth> 3 mm is.
  • this can be parallel to the exit plane of the tube 20th running edge based on a curved course back to the exit level to be brought.
  • the angle ⁇ ' which is between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20 is the same as large as angle ⁇ .
  • Another Design of the tear-off edge for the same purpose can be done with the combustion chamber achieve toroidal notches. Including the mentioned publication the scope of protection there is, as far as the tear-off edge is concerned, an integrating one Part of this description.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)

Claims (14)

  1. Brûleur pour le fonctionnement d'un générateur de chaleur, dans lequel le brûleur se compose essentiellement d'un générateur de tourbillons (100) pour un courant d'air de combustion, de moyen d'injection d'au moins un combustible dans le courant d'air de combustion, une section de mélange (220) étant prévue en aval du générateur de tourbillons, laquélle présente, à l'intérieur d'une première partie de sa section dans le sens de l'écoulement, une pluralité de canaux de transition (201) pour le passage d'un écoulement formé dans le générateur de tourbillons dans un tube de mélange (20) monté après en aval de ces canaux de transition,
    caractérisé en ce que
    le générateur de tourbillons (100) est équipé, de part et d'autre d'un canal d'entrée (120) produisant des tourbillons, d'injecteurs de combustible (116, 116a), les deux rangées d'injecteurs de combustible (116, 116a) formant un plan d'injection (H) et ce plan d'injection (H) augmentant depuis la pointe jusqu'à la sortie du générateur de tourbillons (100).
  2. Brûleur selon la revendication 1, caractérisé en ce que les injecteurs de carburant (116, 116a) agissant de part et d'autre sont disposés de manière décalée les uns par rapport aux autres dans la direction axiale.
  3. Brûleur selon la revendication 1, caractérisé en ce que le générateur de tourbillons (100) se compose d'au moins deux corps partiels creux (140, 141, 142, 143), de forme conique, emboítés l'un dans l'autre dans le sens de l'écoulement, en ce que les axes médians respectifs (140a, 141a, 142a, 143a) de ces corps partiels s'étendent de manière décalée les uns par rapport aux autres, de telle sorte que les parois voisines des corps creux forment dans leur étendue longitudinale des canaux d'entrée tangentiels (120) pour un courant d'air de combustion (115), et en ce qu'une section de prémélange peut agir dans l'espace interne (114) formé par les corps partiels.
  4. Brûleur selon la revendication 3, caractérisé en ce qu'une buse d'injection de combustible (103) est prévue du côté de la tête du générateur de tourbillons (100).
  5. Brûleur selon la revendication 3, caractérisé en ce que les corps partiels (140, 141, 142, 143) présentent, en section transversale, un profilage en forme de pale.
  6. Brûleur selon la revendication 3, caractérisé en ce que les corps partiels présentent, dans le sens de l'écoulement, un angle conique fixe ou une inclinaison conique croissante, ou une inclinaison conique décroissante.
  7. Brûleur selon la revendication 3, caractérisé en ce que les corps partiels sont emboítés les uns dans les autres en formant une spirale.
  8. Brûleur selon la revendication 1, caractérisé en ce que le nombre des canaux de transition (201) dans la section de mélange (220) correspond au nombre des courants partiels formés par le générateur de tourbillons (100).
  9. Brûleur selon la revendication 1, caractérisé en ce que le tube de mélange (20) monté après les canaux de transition (201) est pourvu dans le sens de l'écoulement et dans le sens périphérique d'ouvertures (21) pour l'injection d'un courant d'air à l'intérieur du tube de mélange (20).
  10. Brûleur selon la revendication 9, caractérisé en ce que les ouvertures (21) s'étendent suivant un angle aigu par rapport à l'axe du brûleur (60) du tube de mélange (20).
  11. Brûleur selon la revendication 1, caractérisé en ce que la section transversale d'écoulement du tube de mélange (20) en aval des canaux de transition (201) est plus petite, égale ou supérieure à la section transversale de l'écoulement (40) formé dans le générateur de tourbillons (100, 100a).
  12. Brûleur selon la revendication 1, caractérisé en ce qu'une chambre de combustion (30) est prévue en aval de la section de mélange (220), en ce qu'entre la section de mélange (220) et la chambre de combustion (30) se produit un saut de section transversale, qui induit la section transversale d'écoulement initiale de la chambre de combustion (30), et en ce qu'un zone de reflux (50) peut agir dans la région de ce saut de section transversale.
  13. Brûleur selon la revendication 12, caractérisé en ce qu'un diffuseur et/ou une section de venturi est prévu (e) en amont de la zone de reflux (50).
  14. Brûleur selon la revendication 1, caractérisé en ce que le tube de mélange (20) présente, du côté de la chambre de combustion (30) un bord de rupture (A).
EP97810867A 1997-11-13 1997-11-13 Brûleur pour la mise en oeuvre d'un générateur de chaleur Expired - Lifetime EP0916894B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810867A EP0916894B1 (fr) 1997-11-13 1997-11-13 Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59710788T DE59710788D1 (de) 1997-11-13 1997-11-13 Brenner für den Betrieb eines Wärmeerzeugers
US09/187,343 US6027331A (en) 1997-11-13 1998-11-06 Burner for operating a heat generator
JP32224098A JP4263278B2 (ja) 1997-11-13 1998-11-12 熱発生器を運転するためのバーナ
CNB981269826A CN1137342C (zh) 1997-11-13 1998-11-13 用于驱动热发生器的喷嘴

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810867A EP0916894B1 (fr) 1997-11-13 1997-11-13 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Publications (2)

Publication Number Publication Date
EP0916894A1 EP0916894A1 (fr) 1999-05-19
EP0916894B1 true EP0916894B1 (fr) 2003-09-24

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ID=8230469

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810867A Expired - Lifetime EP0916894B1 (fr) 1997-11-13 1997-11-13 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Country Status (5)

Country Link
US (1) US6027331A (fr)
EP (1) EP0916894B1 (fr)
JP (1) JP4263278B2 (fr)
CN (1) CN1137342C (fr)
DE (1) DE59710788D1 (fr)

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US6769903B2 (en) * 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
DE10040869A1 (de) * 2000-08-21 2002-03-07 Alstom Power Nv Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE102004015904A1 (de) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Verfahren zur Flüssigbrennstoffzerstäubung in einem Vormischbrenner sowie Vormischbrenner
EP1754003B1 (fr) 2004-06-08 2007-09-19 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide
EP1614963A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Système de combustion à prémélange et procédé
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
WO2006069861A1 (fr) * 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange
US8448881B2 (en) * 2006-10-13 2013-05-28 Rolls-Royce Power Engineering Plc Fuel injector
EP1990578A1 (fr) * 2007-05-08 2008-11-12 ALSTOM Technology Ltd Turbine à gaz avec injection d'eau
US8061142B2 (en) * 2008-04-11 2011-11-22 General Electric Company Mixer for a combustor
US8220269B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Combustor for a gas turbine engine with effusion cooled baffle
US8220271B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Fuel lance for a gas turbine engine including outer helical grooves
CN101936530A (zh) * 2010-09-29 2011-01-05 中国石油化工股份有限公司 一种多点燃烧的长火焰超低氮氧化物排放的气体燃烧器
CN102705867A (zh) * 2012-06-11 2012-10-03 石家庄市新华工业炉有限公司 一种煤粉点火器
EP2685163B1 (fr) * 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
CN109237472B (zh) * 2018-06-26 2024-05-17 天时燃烧设备（苏州）有限责任公司 燃烧管组件和燃烧器

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ATE42821T1 (de) * 1985-03-04 1989-05-15 Siemens Ag Brenneranordnung fuer feuerungsanlagen, insbesondere fuer brennkammern von gasturbinenanlagen sowie verfahren zu ihrem betrieb.
EP0276696B1 (fr) * 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
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DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19547913A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger

Also Published As

Publication number Publication date
EP0916894A1 (fr) 1999-05-19
DE59710788D1 (de) 2003-10-30
CN1137342C (zh) 2004-02-04
CN1225437A (zh) 1999-08-11
JPH11223305A (ja) 1999-08-17
JP4263278B2 (ja) 2009-05-13
US6027331A (en) 2000-02-22

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