EP1999410B1 - Bruleur pour le fonctionnement d'un generateur de chaleur - Google Patents

Bruleur pour le fonctionnement d'un generateur de chaleur Download PDF

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Publication number
EP1999410B1
EP1999410B1 EP07726625.2A EP07726625A EP1999410B1 EP 1999410 B1 EP1999410 B1 EP 1999410B1 EP 07726625 A EP07726625 A EP 07726625A EP 1999410 B1 EP1999410 B1 EP 1999410B1
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EP
European Patent Office
Prior art keywords
burner
nozzle
fuel
combustion chamber
front plate
Prior art date
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Active
Application number
EP07726625.2A
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German (de)
English (en)
Other versions
EP1999410A1 (fr
Inventor
Stefano Bernero
Peter Flohr
Gijsbertus Oomens
Martin Zajadatz
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 Technology AG
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Publication of EP1999410A1 publication Critical patent/EP1999410A1/fr
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Classifications

    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/008—Flow control 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
    • F23R3/34—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
    • 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

Definitions

  • the present invention relates to a burner for operating a heat generator, wherein such a burner comprises a swirl generator for a combustion air stream, and means for injecting at least one fuel into the combustion air stream. Downstream of the swirl generator, a mixing section is arranged, and in the region radially outside the outlet opening of the mixing section of the burner at least one nozzle for supplying liquid pilot fuel is present. Furthermore, the present invention relates to a method for operating such burners.
  • Premix burners such as in the EP 0 321 809 B1 proposed are burners in which a fuel, gaseous or liquid, is first mixed with the combustion air and is burned in the flame after this mixing process.
  • a fuel, gaseous or liquid is first mixed with the combustion air and is burned in the flame after this mixing process.
  • a plurality of conical wall elements is provided, wherein these wall elements to each other in such a way are arranged offset that between them entry slots for the combustion air are formed in the interior of the burner. In this area, so a swirl is generated, and the swirl flow formed therein is then converted into a mixing section.
  • both liquid and gaseous fuels can be burned, the former being preferably supplied on the axis of the burner via a fuel lance, and the latter in the region of the inlet slots, typically via a plurality of outlet holes arranged one behind the other.
  • Such burners are characterized by excellent stability of the flame and by excellent pollutant values (low NOx values) and efficient heat generation.
  • a mixing section is also arranged downstream of the swirl generator from said conical wall elements, and at the entrance of this mixing section specific transition channels are provided which ensure an ideal transfer of the flow formed in the swirl generator into the mixing section.
  • pilot operation has already been proposed several times, ie a mode of operation in which special additional fuel nozzles are placed at suitable locations of the burner or in the combustion chamber, which can be controlled under such low load conditions or transient conditions.
  • gaseous pilot fuel is ignited in an exit ring of the burner after mixing with combustion air by means of an igniter and injected into the combustion chamber.
  • the supply via fuel lines is described with arranged at the end outlet openings, the outlet openings do not open directly into the combustion chamber but much more in a in the Exit edge arranged circumferential cavity in the outlet ring directly adjacent to the burner opening, which is purged with combustion air and which above above the outlet openings resp.
  • the fuel is introduced in a jet into the combustion chamber, which is arranged in a plane which includes the axis of the burner.
  • the jet forms an angle in the range of 15 to 60 ° with the axis of the burner.
  • the outlet openings are flowed around at their surface facing the combustion chamber by the combustion air supplied in the ring, but the cooling still needs to be optimized because the air ring leads to an uneven distribution of the air and thus to an uneven cooling.
  • the cold fuel in this case causes a high temperature gradient, which leads to high voltages.
  • a perforated plate having at least two holes inserted in the line cross sections of the feed line can be used for generating such turbulence.
  • the invention is therefore an object of the invention to provide an improved burner available, which can be driven with liquid fuel in pilot operation.
  • a stable operation is to be made possible at low pollutant values, and overheating of components is to be avoided.
  • a possible modular structure which, for example, a replacement of the elements of the pilot burner, allowed to be given.
  • this involves the improvement of a burner for operating a heat generator, wherein the burner comprises a swirl generator for a combustion air flow, and means for injecting at least one fuel into the combustion air flow, wherein downstream of the swirl generator, a mixing section is arranged, and wherein radially At least one nozzle for supplying liquid pilot fuel is arranged outside the outlet opening of the mixing section of the burner.
  • the at least one nozzle is arranged in a burner front plate, wherein in an arranged substantially parallel to a combustion chamber rear wall front surface of the burner front plate at least one outlet opening is provided through which the liquid pilot fuel exits into the combustion chamber.
  • This burner front plate with its arranged parallel to the rear wall of the combustion chamber front surface, which is arranged outside the outlet opening of the burner, allows to integrate the supply of pilot fuel in the burner, but still at a sufficient distance from the outlet opening of the burner to arrange.
  • shielding air purging air
  • the atomization of the liquid pilot fuel is supported and prevents coking, and prevents local backflow.
  • a better atomization of the fuel can be ensured by the arrangement in the front surface.
  • the injection angle can be kept smaller here in comparison to the prior art, as one penetrates far enough from the Brennefaustrittskante.
  • a modular design is advantageously possible, that is, due to the fact that the elements of the pilot burner not in the exit ring of the burner - as in EP-A-1 389 713 - are arranged, these elements are more accessible and can be easily replaced, which saves costs.
  • a burner of the type mentioned above typically has a central region adjoining the burner opening, which region is designed to taper conically backward with respect to a burner axis and form a bevelled edge.
  • the burner front plate can now be integrally formed with such a region, that is, have a central, adjacent to the burner opening area which is formed with respect to a burner axis radially outwardly tapering back and forming a bevelled edge.
  • the at least one outlet opening with respect to the said burner axis is arranged according to a preferred embodiment of the invention radially outside this flank.
  • an outlet ring is arranged between the burner front plate and the burner opening, which is formed with respect to a burner axis radially outwardly tapering back and forming a bevelled edge. Also in this case, the outlet opening is arranged with respect to the said burner axis radially outside this flank,
  • a further preferred embodiment of the invention is characterized in that the burner front plate a plurality of circumferential arranged outlet openings, wherein the burner front plate has at least one, usually behind a rear wall of the combustion chamber provided inlet through which combustion air from the outside entering the burner front plate and can flow through the pressure drop to the combustion chamber through the outlet openings. This ensures optimum cooling of the edge area and the burner front panel.
  • one nozzle per burner is arranged only behind an outlet opening.
  • the nozzle is formed as a pressure jet nozzle (plain jet) or as a pressure swirl nozzle (pressure swirl nozzle). It is preferred, at least in terms of pollutant values, a Druckdrallzerstäuberdüse.
  • a Druckzerstäuberdüse is a nozzle in which the fuel under high pressure initially over z.
  • B. tangentially extending slots is guided in a vortex chamber and then leaves this vortex chamber via a nozzle bore. This creates a spray cone in which the fuel is torn into exceptionally fine particles (see for example Lueger, Encyclopedia of Technology, Stuttgart, 1965, Volume 7, page 600 ).
  • An aspect of the invention is therefore not, as in the EP-A-1 389 713 is described, to use a conventional hole jet (plain jet injection), but rather a very specific nozzle formation, namely a Druckdrallzerstäuberdüse.
  • a Druckdrallzerstäuberdüse in connection with the Piloteindüsung is possible at all, is quite unexpected.
  • the problem with the injection of liquid fuel in the edge region of the burner, that is in the immediate vicinity of the combustion chamber, is the fact that overheating in the region of the nozzle must be avoided. This can be largely due to the arrangement of the pilot burner in the region of the front surface of a burner front plate be achieved.
  • Another embodiment of the invention is characterized in that it is a pressure swirl atomizer nozzle which produces a hollow cone spray rather than a full cone of fuel.
  • nozzles can be used as in the EP 0 924 461 81 or in the EP 0 794 383 B1 be described, but there are also other constructions possible.
  • the nozzle is arranged in a cavity in the burner front plate, which has an outlet opening to the combustion chamber, through which the spray cone generated by the nozzle enters the combustion chamber, wherein the nozzle opening is set back from the outlet opening with respect to the combustion chamber.
  • this cavity is at least in the region of the nozzle and downstream of the nozzle substantially cylindrical cavity, and more preferably, the inner diameter of this cavity is equal to or less than the inner diameter of the outlet opening.
  • the nozzle opening is offset by up to 50 mm from the combustion chamber facing the front edge of the outlet opening to the rear.
  • An ideal combustion behavior of the pilot flame can be realized if such a cavity has at least one inlet opening, through which combustion air enter from outside into the cavity and flow through the pressure drop to the combustion chamber through the outlet openings can.
  • This screen air (purging air) promotes atomization, and it is advantageous to avoid coking of the injector and local backflow.
  • the injection of the liquid pilot fuel is thus individually and is positioned at each nozzle with its own purge air.
  • the outlet opening is at least the same size as the cylindrical cavity in order to avoid flow losses.
  • the nozzle is oriented so that the main axis of the spray cone generated by the nozzle is arranged in a plane formed by said main axis and the central axis of the burner, between the main axis of the spray cone (with a spray cone angle ⁇ in the range of 0 to 90 °) and the axis of the burner an angle ⁇ in the range of +/- 45 °, preferably in the range of 0 °, is included.
  • the present invention relates to a method of operating a burner as described above.
  • the method is particularly characterized in that liquid fuel through the nozzle at least is used at low load or under transient conditions to generate pilot flames. Due to the specific design of the nozzle, it is possible to control the pilot flame for stabilization even with nominal load or high load.
  • FIG. 1 shows schematically in a central section a burner of the type, as for example in the EP 0 704 657 B1 or in the EP 0 780 629 B1 is described.
  • a burner 23 has a swirl generator 2, which is formed by the staggered arrangement of at least two conical partial bodies 1. Tangential inlet slits 8 are formed between the two partial bodies 1 as a result of this offset arrangement. The combustion air 9 enters through these tangential inlet slits 8 into the burner cavity 10, a high swirl being generated.
  • a fuel nozzle 7 for liquid fuels is arranged.
  • the fuel emerging from this fuel nozzle 7 forms a fuel cone 11 and is captured by and enveloped by the combustion air 9 flowing in tangentially, and a conical column of a mixture of fuel and combustion air is formed.
  • Gaseous fuel can be supplied in the region of the tangential inlet slots 8 via additional fuel nozzles 12.
  • a mixing section 3 Downstream of this swirl generator 2 is a mixing section 3.
  • transition channels 6 are arranged, which support the flow in this area and ensure optimal entry into the mixing section 3.
  • the mixing section 3 consists essentially of a cylindrical tube.
  • a burner front plate 32 On the combustion chamber 16 facing the end of this tube is now a burner front plate 32, which limits the burner to the combustion chamber 16 and possibly arranged inside a discharge ring 4.
  • this burner front plate 32 and the outlet ring 4 for example, means are provided to supply gaseous fuel for the pilot operation, as for example in the EP 0 931 980 B1 or in the EP 0 994 300 B1 is described. Furthermore, a supply for liquid pilot fuel is now also provided in the region of the burner front plate 32, respectively integrated therein.
  • a fuel line 17 is provided, which has at its end facing the combustion chamber via a Druckdrallzerstäuberdüse 20 or via a conventional steel nozzle.
  • the at least one nozzle 20 is arranged in the burner front plate 32.
  • This pressure swirl atomizing nozzle or pressure jet nozzle 20 may be arranged parallel to the axis 29 of the burner (see lower spray cone 21 with a spray cone angle ⁇ in Fig. 1 ). But it is also possible that Main axis of the hollow fuel spray 21 from pilot fuel produced by the Druckdrallzerstäuberdüse 20 in a plane comprising the axis 29 of the burner to tilt by an angle ⁇ . Furthermore, it is possible to tilt by a tilt angle ⁇ (in Fig. 1 not shown) to introduce the fuel in a manner adapted to the rotational movement of the combustion air from the burner.
  • the spray cone angle ⁇ is preferably in the range of 0-90 °.
  • FIG. 2 a detail section of the edge region of the burner in the region of the burner front plate of such a burner is shown. It can be seen that the fuel line 17 enters the burner front plate 32 and is guided concentrically into a tube 31. At the top of the fuel line 17 is a Druckdrallzerstäuberdüse 20 (or analog each a Druckstrahldüse) arranged. The Druckdrallzerstäuberdüse is set back by a distance d, which may be up to 50 mm, from the front edge 26, which faces the combustion chamber 16. This offset contributes to the pressure swirl atomizer nozzle 20 not being exposed to excessive heating by the combustion chamber.
  • the tube 31 encloses a cavity 27.
  • an outlet opening 15 is provided which has such a diameter, so that the hollow cone spray 21 formed by the pressure swirl atomizer nozzle 20 does not touch the outlet opening 15 during operation.
  • the tube 31 has an inner diameter which is at most as large, preferably equal in size, as the inner diameter of the outlet opening 15, in order to avoid flow problems arising over a step. Furthermore, the tube 31 has a combustion chamber 16 facing away from the inlet opening 22 for combustion air 18. This combustion air 18 is sucked through the pressure drop to the combustion chamber 16 through the pipe 31 and the cavity 27 and flows in the direction of the combustion chamber 16.
  • To adjust the flow means 14th (For example, insert) are provided.
  • the combustion air 18 therefore also represents an umbrella air. It promotes the atomization of the liquid fuel, so that due to the uniform distribution of the fuel coking and local backflow can be avoided. It not only ensures that sufficient cooling of the pressure swirl atomizer nozzle 20 is ensured, but also leads to an ideal transfer of the hollow cone spray through the outlet opening 15 in the combustion chamber 16. Furthermore, the atomization of the fuel of the hollow cone at the liquid / gas interface is supported ,
  • FIG. 3 It is shown how an ideal size of the droplets for combustion can be generated from such a pressure swirl atomizing nozzle. It turns out that even for low mass flow of fuel (plotted on the x-axis), on the one hand, a small particle size results (for example, D10 means at 10 g / s that 10% of the droplets are smaller than approximately 22 ⁇ m, and D90, 90% of the droplets are smaller than about 133 ⁇ m). In addition, an optimum volume-to-surface ratio (D32) is achieved over a wide range for the combustion process. Also, the pressure drop under the typical conditions for the supply of fuel for pilot burners moves in the appropriate range.

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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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (14)

  1. Brûleur (23) pour le fonctionnement d'un générateur de chaleur, dans lequel le brûleur comprend un générateur de tourbillon (2) pour un courant d'air de combustion (9) ainsi que des moyens (7,12) d'injection d'au moins un combustible dans le courant d'air de combustion (9), dans lequel en aval du générateur de tourbillon (2) une section de mélange (3) est disposée et dans lequel dans la zone radialement à l'extérieur de l'ouverture de sortie de la section de mélange (3) du brûleur au moins une buse (20) pour l'alimentation de combustible pilote liquide,
    caractérisé en ce que
    au moins une bise (20) est disposée dans une plaque avant de brûleur (32), dans lequel dans une surface avant (34) de la plaque avant de brûleur (32) à disposée essentiellement parallèlement à une paroi arrière de chambre de combustion (28) au moins une ouverture de sortie (15) est prévue, à travers laquelle le combustible pilote liquide ressort dans la chambre de combustion (16).
  2. Brûleur (23) selon la revendication 1, caractérisé en ce que la plaque avant de brûleur (32) présente une zone centrale (4), contiguë à l'ouverture de brûleur, qui est conçue en redescendant coniquement radialement vers l'extérieur par rapport à un axe de brûleur (29) et en formant un flanc chanfreiné (33), et en ce que au moins une ouverture de sortie (15) est disposée radialement à l'extérieur de ce flanc (33) par rapport audit axe de brûleur (29),
    ou en ce que entre la plaque avant de brûleur (32) et l'ouverture de brûleur un anneau de sortie (4) est disposé, qui est conçu en redescendant coniquement radialement vers l'extérieur par rapport à un axe de brûleur (29) et en formant un flanc chanfreiné (33), et en ce que au moins une ouverture de sortie (15) est disposée radialement à l'extérieur de ce flanc (33) par rapport audit axe de brûleur (29).
  3. Brûleur (23) selon la revendication 1 ou 2, caractérisé en ce que la plaque avant de brûleur (32) présente une pluralité d'ouvertures de sortie (15) disposées sur son pourtour, dans lequel la plaque avant de brûleur (32) présente au moins une ouverture d'entrée (22), à travers laquelle de l'air de combustion (18) peut entrer à partir de l'extérieur dans la plaque avant de brûleur (32) et par l'intermédiaire de la chute de pression par rapport à la chambre de combustion (16) peut s'écouler à travers les ouvertures de sortie (15).
  4. Brûleur (23) selon la revendication 3, caractérisé en ce que seulement une buse (20) est disposée derrière une ouverture de sortie (15) par brûleur (23).
  5. Brûleur (23) selon une des revendications précédentes, caractérisé en ce que la buse (20) consiste en une buse à jet de pression ou un gicleur de pression.
  6. Brûleur (23) selon la revendication 5, caractérisé en ce que il s'agit d'un gicleur de pression (20), qui produit une pulvérisation conique creuse (21).
  7. Brûleur (23) selon une des revendications précédentes, caractérisé en ce que la buse (20) est disposée dans un espace creux (27) dans la plaque avant de brûleur (32), qui présente une ouverture de sortie (15) par rpaport à la chambre de combustion (16), à travers laquelle le cône de pulvérisation (21) produit par la buse (20) entre dans la chambre de combustion (16), dans lequel l'ouverture de buse est décalée en retrait de l'ouverture de sortie (15) par rapport à la chambre de combustion (16).
  8. Brûleur (23) selon la revendication 7, caractérisé en ce que l'espace creux (27) présente au moins une ouverture d'entrée (22), à travers laquelle de l'air de combustion (18) peut rentrer de l'extérieur dans l'espace creux (27) et par l'intermédiaire de la chute de pression par rapport à la chambre de combustion (16) peut s'écouler à travers l'ouverture(s) de sortie (15).
  9. Brûleur (23) selon la revendication 8, caractérisé en ce que la buse (20) est disposé sur l'extrémité d'une conduite de combustible (17) de conception essentiellement cylindrique, qui dépasse dans l'espace creux (20) essentiellement cylindrique et concentriquement à celui-ci, de sorte que l'air de combustion (18) diffuse le cône de pulvérisation (21) essentiellement autour du pourtour.
  10. Brûleur (23) selon une des revendications 8 ou 9, caractérisé en ce que en amont de la buse (20) des moyens (14) sont prévus, au moyen desquels la section de passage de l'air de combustion (18) peut être réglée dans l'espace creux (27).
  11. Brûleur (23) selon une des revendications précédentes, caractérisé en ce que la buse (20) est disposée de telle sorte que l'axe principal du cône de pulvérisation (21) produit par la buse (20) est disposé dans un plan formé par ledit axe principal et l'axe central (29) du brûleur (23), dans lequel de préférence entre l'axe principal du cône de pulvérisation (21) produit par la buse (20) et l'axe du brûleur un angle γ dans la plage de +/- 45°, de préférence dans la plage de 0° est défini.
  12. Brûleur (23) selon la revendication 11, caractérisé en ce que le cône de pulvérisation (21) formé à partir d'un plan à travers ledit axe principal et l'axe central (29) du brûleur (23) est incliné d'un angle δ, notamment pour entraîner l'alimentation du combustible pilote liquide dans la direction du courant d'air de combatif tournant provenant du brûleur (23).
  13. Procédé de fonctionnement d'un brûleur (23) selon une des revendications 1-12, caractérisé en ce que le combustible liquide passant par la buse (20) est utilisé en présence d'une charge minime ou de conditions transitoires pour générer des flammes pilotes.
  14. Procédé selon la revendication 13, caractérisé en ce que la flamme pilote est commandée à des fins de stabilisation également en présence d'une charge supérieure à la charge nominale respective.
EP07726625.2A 2006-03-27 2007-03-05 Bruleur pour le fonctionnement d'un generateur de chaleur Active EP1999410B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4772006 2006-03-27
PCT/EP2007/052031 WO2007110298A1 (fr) 2006-03-27 2007-03-05 Brûleur pour le fonctionnement d'un générateur de chaleur

Publications (2)

Publication Number Publication Date
EP1999410A1 EP1999410A1 (fr) 2008-12-10
EP1999410B1 true EP1999410B1 (fr) 2015-12-02

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EP07726625.2A Active EP1999410B1 (fr) 2006-03-27 2007-03-05 Bruleur pour le fonctionnement d'un generateur de chaleur

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US (1) US7972133B2 (fr)
EP (1) EP1999410B1 (fr)
JP (1) JP2009531642A (fr)
WO (1) WO2007110298A1 (fr)

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DE59907942D1 (de) * 1999-07-22 2004-01-15 Alstom Switzerland Ltd Vormischbrenner
ITMI20012781A1 (it) * 2001-12-21 2003-06-21 Nuovo Pignone Spa Assieme migliorato di camera di pre miscelamento e di camera di combustione, a basse emissioni inquinanti per turbine a gas con combustibile
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
EP1802915B1 (fr) * 2004-10-18 2016-11-30 General Electric Technology GmbH Bruleur pour turbine a gaz
US7901204B2 (en) * 2006-01-24 2011-03-08 Exxonmobil Chemical Patents Inc. Dual fuel gas-liquid burner
US7909601B2 (en) * 2006-01-24 2011-03-22 Exxonmobil Chemical Patents Inc. Dual fuel gas-liquid burner
US8075305B2 (en) * 2006-01-24 2011-12-13 Exxonmobil Chemical Patents Inc. Dual fuel gas-liquid burner
WO2007110298A1 (fr) 2006-03-27 2007-10-04 Alstom Technology Ltd Brûleur pour le fonctionnement d'un générateur de chaleur

Also Published As

Publication number Publication date
WO2007110298A1 (fr) 2007-10-04
EP1999410A1 (fr) 2008-12-10
JP2009531642A (ja) 2009-09-03
US20090081599A1 (en) 2009-03-26
US7972133B2 (en) 2011-07-05

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