EP0899508B1 - Brenner für einen Wärmeerzeuger - Google Patents

Brenner für einen Wärmeerzeuger Download PDF

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Publication number
EP0899508B1
EP0899508B1 EP98810651A EP98810651A EP0899508B1 EP 0899508 B1 EP0899508 B1 EP 0899508B1 EP 98810651 A EP98810651 A EP 98810651A EP 98810651 A EP98810651 A EP 98810651A EP 0899508 B1 EP0899508 B1 EP 0899508B1
Authority
EP
European Patent Office
Prior art keywords
swirl generator
burner according
tube
flow
section
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
EP98810651A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0899508A1 (de
Inventor
Klaus Dr. Döbbeling
Christian Dr. Steinbach
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 Switzerland 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
Publication of EP0899508A1 publication Critical patent/EP0899508A1/de
Application granted granted Critical
Publication of EP0899508B1 publication Critical patent/EP0899508B1/de
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
    • 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
    • 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
    • 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
    • F23R3/36—Supply of different fuels
    • 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 a heat generator according to Preamble of claim 1.
  • EP-A-704 657 are in a premix burner the double-cone design for operating an internal combustion engine, a combustion chamber a gas turbine group or firing system with one arranged in the cone tip High pressure atomizing nozzle for atomizing liquid fuel through the nozzle holes aligned with the zones of high air speed in the burner and the angle between the fuel drop spray and the longitudinal axis of the burner is at least as large as the cone half angle between the partial cone bodies and the longitudinal axis of the burner.
  • the High pressure atomizing nozzle consists of a nozzle body in which at least one feed channel for those to be atomized and which can be supplied under a pressure of greater than 100 bar liquid fuel is arranged and this feed channel stands with or without in between arranged turbulence chamber via at least two nozzle bores with the interior of the burner. This arrangement makes fine atomization with a high fuel pulse, which is a prerequisite for rapid evaporation of the Fuel as well as for a good premix.
  • 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 precautions by which a perfect premix the fuel used is guaranteed, while maintaining a reliable and optimal flame positioning.
  • the main advantages of the invention are that enrichment the central zone is prevented, and the fuel drops increasing radius within the premixing section a stronger radial acceleration are exposed in such a way that they enter into the Can mix in combustion air well.
  • the number of injection points is adapted to the burner design, at least one injection per bowl or scoop should be provided.
  • the mixing tube 220 can be made from one consist of only one piece, i.e. then that the transition piece 200 and Tube 20 are fused into a single coherent structure, keeping the characteristics of each part. Become a transition piece 200 and tube 20 created from two parts, these are by one Socket ring 10 connected, this head side as an anchoring surface for serves the swirl generator 100. Such a bushing ring 10 also has the Advantage that different mixing tubes can be used. outflow side of the tube 20 is the actual combustion chamber 30, which is here is only symbolized by the flame tube.
  • the mixing tube 220 fulfills that Condition that a defined mixing section is provided downstream of the swirl generator 100 in which a perfect premixing of different fuelskind is achieved.
  • This mixing section ie the mixing tube 220, enables the further a loss-free flow control, so that it is also in operative connection cannot initially form a backflow zone with the transition geometry, with which over the length of the mixing tube 220 to the quality of the mixture for all types of fuel Influence can be exercised.
  • This mixing tube 220 has another other property, which is that in the mixing tube 220 itself Axial velocity profile has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. Indeed it is correct that with such a configuration this axial speed falls to the wall.
  • transition channels 201 accordingly bridge the respective cross-sectional difference, without negatively influencing the flow formed. If the chosen arrangement in guiding the pipe flow 40 along the Mixing tube 220 triggers an intolerable pressure loss, can counteract this Remedy can be created by not at the end of the mixing tube in the figure shown diffuser is provided. At the end of the mixing tube 220 closes a combustion chamber 30, wherein between the two flow cross sections a cross-sectional jump is present. Only here does a central backflow zone form 50, which has the properties of a flame holder. forms there is a flow within this cross-sectional jump during operation Edge zone, in which by the prevailing negative pressure Vertebral detachments occur, this leads to increased ring stabilization the backflow zone 50.
  • the combustion chamber 30 has a number of openings at the end 31 through which an amount of air jumps directly into the cross section flows, and there lower others help that the ring stabilization of the Backflow zone 50 is strengthened.
  • the Generation of a stable backflow zone 50 also a sufficiently high one Twist number in a pipe required. If this is initially undesirable, you can stable return flow zones through the supply of small, strongly swirled air flows generated at the end of the pipe, for example by tangential openings become. It is assumed here that the amount of air required for this in is about 5-20% of the total air volume.
  • Fig. 2-5 The configuration of the tear-off edge at the end of the mixing tube 220 is shown in FIG. 7 described in more detail.
  • the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 2 100.
  • This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner.
  • the number of conical Partial body can of course be larger than two, like the examples 4 and 5 show.
  • the number of conical partial bodies depends on each depends on which operating mode is used. It is with certain operating constellations not excluded, a single spiral Provide swirl generator.
  • the offset of the respective central axis or longitudinal symmetry axes 201b, 202b of the conical partial bodies 101, 102 to one another creates a mirror image of the neighboring wall, one tangential channel each, i.e. an air inlet slot 119, 120 (FIG.
  • the cone shape of the partial body shown 101, 102 in the flow direction has a certain fixed angle.
  • the partial bodies 101, 102 in Flow direction have an increasing or decreasing cone inclination, similar to a trumpet or Tulip. The latter two forms are not recorded in the drawing, since they can be easily understood by the expert are.
  • the two conical partial bodies 101, 102 each have a cylindrical one Initial part 101a, 102a, which also, analogous to the conical partial bodies 101, 102, run offset to one another so that the tangential air inlet slots 119, 120 are present over the entire length of the swirl generator 100.
  • a main nozzle 103 In the area of the cylindrical initial part is a main nozzle 103, preferably for one liquid fuel 112 housed.
  • the introduction of the fuel into the cone cavity 114 takes place here a decentralized injection, which is carried out by a number of nozzle pipes 104 becomes.
  • the angle of the fuel jet formed from these nozzle tubes 104 105 compared to the burner axis corresponds approximately the tapered course of the partial bodies 101, 102. If the swirl generator is characterized by a blade configuration acting on a plane, the angle corresponds of the fuel jet 105 the angle of attack of the blades with respect to the Combustion chamber axis. In this connection, reference is made to FIG. 8.
  • the preferably to be provided injection position of the fuel jet 105 with respect the inflow level of the combustion air 115 is closer to Fig. 3-5 explained.
  • the injection capacity and injection type of the individual nozzle pipes 104 depends on the given parameters of the respective burner. ever depending on the size of the burner, turbulence-assisted Provide pressure atomization nozzle for the individual nozzle tubes 104, the Injection pressure to achieve good atomization qualities be around 100 bar should.
  • the length of the nozzle tubes 104 is the required injection radius to adjust, but should not exceed 1/4 of the partial body. blade length (Fig. 8), otherwise there is an inherent risk that during operation with gaseous fuels, the nozzle tubes 104 act as a flame holder. For long partial body or blades (Fig. 8) a decentralized injection must be provided, in which the nozzle tubes 104 directly from the partial body, respectively. Look fine (Fig. 8) emerges in the wake flow.
  • the fuel can be targeted Zones of high air velocity are sprayed.
  • a company can also be operated maintained with minimized pollutant emissions without the addition of water gets along. It is then essential that the fine atomization is connected with a high fuel pulse, good prerequisites for rapid evaporation of fuel as well as maximized premix.
  • the swirl generator 100 can be made purely conical, that is to say without cylindrical starting parts 101a, 102a.
  • the conical sub-bodies 101, 102 further each have a fuel line 108, 109, which are arranged along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing there, such as this is symbolized by the arrows 116.
  • These fuel lines 108, 109 are preferably placed at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture.
  • the fuel 112 brought in through the main nozzle 103 is normally a liquid fuel, and it is readily possible to form a mixture with another medium. If the combustion air 115 is additionally preheated or, for example, enriched with a recirculated flue gas or exhaust gas, this sustainably supports the evaporation of the liquid fuel 112 within the premixing section formed by the length of the burner before this mixture flows into the downstream combustion stage. The same considerations also apply if liquid fuels should be supplied via lines 108, 109.
  • the design of the swirl generator 100 is furthermore excellently suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operational bandwidth can be recorded without changing the overall length of the swirl generator 100.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which an overlap thereof can even be provided. It is also possible to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement. It is thus possible to vary the shape, the size and the configuration of the tangential air inlet slots 119, 120 as desired, with which the swirl generator 100 can be used universally without changing its overall length.
  • FIG. 3 now shows the geometric configuration of the guide plates 121a, 121 b. They have a flow introduction function, and this, accordingly their length, the respective end of the tapered partial body 101, 102 in the direction of flow extend towards the combustion air 115.
  • the channeling the combustion air 115 into the cone cavity 114 can be opened or closing the guide plates 121 a, 121 b by one in the area of the entry thereof Channel in the cone cavity 114 pivot point 123 are optimized, this is particularly necessary if the original gap size of the tangential Air inlet slots 119, 120 should be changed dynamically.
  • these dynamic arrangements can also be provided statically, by making required baffles an integral part with the tapered Form partial bodies 101, 102.
  • the swirl generator 100 can also be used without Baffles are operated, or other aids can be provided for this become.
  • the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed.
  • the associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.
  • FIG. 5 differs from FIG. 4 in that the partial body 140, 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
  • 3-5 is within the flow cross-section positioned one-tip positions of the fuel jet 105, which of the Flow of the combustion air corresponds to the opposite sides. Usually it will a nozzle tube is provided for each combustion air inflow, one of these Assignment is not essential. Preferably the number of fuel jets adapted to the burner design.
  • the individual fuel jets 105 are positioned in such a way that, in compliance with the procedure shown in FIG underlying angle of the fuel jet, along the leeward side of the partial body 101 and 102, 130-133, 140-143, as can be seen from FIGS. 3-5, respectively. of the guide vanes in a configuration of the swirl generator according to FIG. 8 act. There the drop spray is exposed to lower aerodynamic forces, so that it is better mixed radially into the combustion air 115.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 4 or 5, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on, whereby the conical quarter area of said partial body is extended until the wall of the tube 20 resp. of the mixing tube 220 cuts.
  • the same considerations also apply when the swirl generator comes from another Principle, as that described under Fig. 2, is constructed.
  • the down surface of the individual transition channels 201 running in the direction of flow has a spiral shape in the direction of flow, which one describes crescent-shaped course, corresponding to the fact that present the flow cross section of the transition piece 200 in the flow direction flared.
  • the swirl angle of the transition channels 201 in the flow direction is selected so that the pipe flow then up to the cross-sectional jump there is still a sufficiently large distance at the combustion chamber inlet, to achieve a perfect premix with the injected fuel. Furthermore, the measures mentioned above also increase the axial speed on the mixing tube wall downstream of the swirl generator. The Transition geometry and the measures in the area of the mixing tube a significant increase in the axial speed profile towards the center of the mixing tube, so that the danger of early ignition is decisively counteracted becomes.
  • 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 20 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 ⁇ .
  • FIG. 8 shows a swirl generator 150 which uses swirl blading 151 is constructed.
  • a swirl generator Concentric to the central main nozzle powered by fuel 112 103 a swirl generator is scheduled, which consists of a swirl blading 151 exists, i.e. cause the blades arranged in a ring here a swirl, analogous to that of Fig. 2.
  • the combustion air supplied 115 can take place here using an annular channel, not shown in more detail, which extends upstream of the swirl blading 151.
  • the central main fuel nozzle 103 Downstream of the swirl blading 151, the central main fuel nozzle 103 has a number of nozzle pipes 104, whose fuel jet 105 is the angle of attack of the swirl blades 151 relative to the burner axis 60 respectively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)
EP98810651A 1997-08-25 1998-07-08 Brenner für einen Wärmeerzeuger Expired - Lifetime EP0899508B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19736902A DE19736902A1 (de) 1997-08-25 1997-08-25 Brenner für einen Wärmeerzeuger
DE19736902 1997-08-25

Publications (2)

Publication Number Publication Date
EP0899508A1 EP0899508A1 (de) 1999-03-03
EP0899508B1 true EP0899508B1 (de) 2004-01-28

Family

ID=7840057

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810651A Expired - Lifetime EP0899508B1 (de) 1997-08-25 1998-07-08 Brenner für einen Wärmeerzeuger

Country Status (5)

Country Link
US (1) US6102692A (ja)
EP (1) EP0899508B1 (ja)
JP (1) JP4442940B2 (ja)
CN (1) CN1318797C (ja)
DE (2) DE19736902A1 (ja)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
DE102009053379A1 (de) * 2009-11-14 2011-05-19 Volkswagen Ag Brenner

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DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE50110801D1 (de) 2000-12-23 2006-10-05 Alstom Technology Ltd Brenner zur Erzeugung eines Heissgases
EP1262714A1 (de) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brenner mit Abgasrückführung
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
DE502005005999D1 (de) * 2004-01-20 2009-01-02 Alstom Technology Ltd Vormischbrenneranordnung sowie Verfahren zum Betreiben einer Brennkammer
WO2005078348A1 (de) * 2004-02-12 2005-08-25 Alstom Technology Ltd Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer
CN100559080C (zh) * 2004-10-18 2009-11-11 阿尔斯通技术有限公司 燃气轮机用的燃烧器
WO2006058843A1 (de) * 2004-11-30 2006-06-08 Alstom Technology Ltd Verfahren und vorrichtung zur verbrennung von wasserstoff in einem vormischbrenner
DE502006007811D1 (de) * 2005-06-17 2010-10-21 Alstom Technology Ltd Brenner zur vormischartigen Verbrennung
FR2889292B1 (fr) * 2005-07-26 2015-01-30 Optimise Procede et installation de combustion sans soutien de gaz combustible pauvre a l'aide d'un bruleur et bruleur associe
CA2515923A1 (en) * 2005-08-05 2007-02-05 Mark A. Dupuis Nozzle
WO2007135691A1 (en) * 2006-05-22 2007-11-29 Spray Engineering Devices Limited Improved jet nozzle for multijet multispray condenser
CN101235969B (zh) * 2007-01-31 2014-11-26 通用电气公司 具有同轴燃料-空气通道的逆流喷射机构
DE102009060844A1 (de) 2009-12-29 2011-06-30 Friedrichs, Arno, 95326 Verfahren zur Herstellung eines Kanäle aufweisenden Kraftstoffeinspritzelementes sowie Kraftstoffeinspritzelement
KR101190128B1 (ko) * 2010-09-15 2012-10-12 강원석 세척용 분사노즐
US8365534B2 (en) 2011-03-15 2013-02-05 General Electric Company Gas turbine combustor having a fuel nozzle for flame anchoring
RU2011115528A (ru) 2011-04-21 2012-10-27 Дженерал Электрик Компани (US) Топливная форсунка, камера сгорания и способ работы камеры сгорания
EP2650612A1 (en) * 2012-04-10 2013-10-16 Siemens Aktiengesellschaft Burner
EP2693117A1 (en) 2012-07-30 2014-02-05 Alstom Technology Ltd Reheat burner and method of mixing fuel/carrier air flow within a reheat burner
CN104456553B (zh) * 2014-11-24 2016-08-10 浙江大学 适用于研究液体燃料燃烧特性的锥形火焰燃烧器及其方法
CN107620958B (zh) * 2017-09-23 2019-02-15 武汉富世达能源科技股份有限公司 一种聚能预热燃烧器
CN108019741A (zh) * 2017-12-10 2018-05-11 罗碧婉 旋涡式锅炉炉膛
CN108036306A (zh) * 2017-12-10 2018-05-15 罗碧婉 旋涡式锅炉烟气燃烧室
FR3099547B1 (fr) * 2019-07-29 2021-10-08 Safran Aircraft Engines Nez d'injecteur de carburant pour turbomachine comprenant une chambre de mise en rotation intérieurement délimitée par un pion
CN111503659B (zh) * 2020-04-28 2021-11-09 中国航发湖南动力机械研究所 火焰筒、微型涡喷发动机及火焰筒的制备工艺
CN115163667B (zh) * 2022-07-27 2024-06-14 合肥工业大学 一种涡旋型出气的平面静压气浮轴承

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DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
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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
DE19610930A1 (de) * 1996-03-20 1997-09-25 Abb Research Ltd Brenner für einen Wärmeerzeuger

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009053379A1 (de) * 2009-11-14 2011-05-19 Volkswagen Ag Brenner
DE102009053379B4 (de) * 2009-11-14 2021-02-04 Volkswagen Ag Abgasanlage einer Brennkraftmaschine mit einem Brenner

Also Published As

Publication number Publication date
DE19736902A1 (de) 1999-03-04
JP4442940B2 (ja) 2010-03-31
CN1318797C (zh) 2007-05-30
US6102692A (en) 2000-08-15
EP0899508A1 (de) 1999-03-03
CN1209521A (zh) 1999-03-03
DE59810650D1 (de) 2004-03-04
JPH11118108A (ja) 1999-04-30

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