EP0937864A2 - Configuration des aubes de guidage pour une turbomachine axiale - Google Patents

Configuration des aubes de guidage pour une turbomachine axiale Download PDF

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Publication number
EP0937864A2
EP0937864A2 EP99103156A EP99103156A EP0937864A2 EP 0937864 A2 EP0937864 A2 EP 0937864A2 EP 99103156 A EP99103156 A EP 99103156A EP 99103156 A EP99103156 A EP 99103156A EP 0937864 A2 EP0937864 A2 EP 0937864A2
Authority
EP
European Patent Office
Prior art keywords
housing
guide vane
vane ring
shroud
reinforcement
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.)
Granted
Application number
EP99103156A
Other languages
German (de)
English (en)
Other versions
EP0937864A3 (fr
EP0937864B1 (fr
Inventor
Hermann Klingels
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Aero Engines GmbH, MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Aero Engines GmbH
Publication of EP0937864A2 publication Critical patent/EP0937864A2/fr
Publication of EP0937864A3 publication Critical patent/EP0937864A3/fr
Application granted granted Critical
Publication of EP0937864B1 publication Critical patent/EP0937864B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to a fluid flow machine with a rotor and stator in fluidic terms single or multi-stage design, according to the preamble of the claim 1.
  • Such a turbomachine is known for example from DE-PS 27 45 130, this document specifically relates to axial turbines with labyrinth seals.
  • the flow channel of the working medium alternately leads through guide vanes and rotating vane rings, the static components protruding radially from the outside and the rotating ones radially from the inside.
  • Figure 1 of this document clearly shows, there are both radially inside seals between the rotor and the vane rings ( Inner Airseal ”) as well as seals arranged radially on the outside between the rotor blades and the stator ( Outer Airseal ").
  • the sealing fins are the Inner Airseal "is attached to the rotor (item 4), so that their dimensions or dimensional deviations depend on the conditions on the rotor (temperature, speed).
  • the associated sealing lining (item 7), on the other hand, is on the inner cover band (item 20)
  • the guide vane segments are mounted on the housing (pos. 13, 14), so that the dimensions or dimensional deviations of the sealing layer are ultimately determined by the conditions on the outside of the housing on the other hand, the housing often does not change conformingly at the same time, so that there are gap-changing relative movements between the sealing elements (item 7.8) Outer Airseal "(item 11, 12).
  • each segment of a guide vane ring is a mechanical unit on - in the longitudinal section hook-shaped housing elements (item 14 At the upstream end of the outer shroud, each guide vane segment has an edge bead with a groove which engages around the hook-shaped housing element (item 14, 22) in a claw-like manner (see FIG. 3).
  • each guide vane segment there is an angled section in longitudinal section with a radially outwardly facing contact surface, which during operation is caused by a flow-induced tilting moment around the upstream one Claw bearing "is pressed against the corresponding hook-shaped housing element (see FIG. 1).
  • the hook-shaped housing elements also as Hook rings “identifiable -flows of high density heat flow to the colder housing, the "Hook rings” especially in the area of Claw bearings "can be increasingly plastically deformed by crawling. The only remedy here is permanent cooling of the Hook rings ".
  • DE-PS 35 40 943 describes such a gap control system especially for one Dual-flow engine.
  • the secondary air duct extends at least up to to the end of the turbine area and has openings (item 11) in its inner wall on, through the secondary air from the outside targeted to areas of the turbine housing can be blown.
  • This simplified ACC system may have the problem that the low excess pressure of the secondary air flow is not sufficient to in locally narrow housing zones due to correspondingly small flow cross sections To generate cooling air flows with sufficient mass flow.
  • an ACC compressor air from the booster or low pressure compressor branched off as coolant, routed in separate channels and via valves specifically blown out.
  • guide vane rings In the case of smaller gas turbine engines, it is known to design guide vane rings as self-supporting, integral components with closed shrouds and to center them in the housing. This is for manufacturing and strength reasons (thermal stresses) monolithic "solution limited to blade rings with relatively small dimensions.
  • DE-OS 33 36 420 describes a mechanism for protection against overtightening of a gas turbine rotor in the event of a shaft break.
  • the mechanism works in the Way that the guide vane segments axially at least one vane ring pivoted and brought into contact / engagement with adjacent blades become. The mutual mechanical blade friction and destruction slows down the rotor quickly and effectively.
  • the vane segments belonging to the mechanism each have a pivot bearing on the outer shroud segment and are on their inner circumference by means of a form-fitting, ring-like reinforcement element connected so that the segments together form a rigid, self-supporting Form the guide vane ring.
  • the swivel bearings (positions 36, 56, 58 and 64) provide spoke centering for the intrinsically stable guide vane ring, which contributes to precise positioning / centering reduced thermal voltages.
  • a disadvantage is the heat transfer from Hot gas area to the housing (item 34), which also affects the bearing elements are. The resulting high temperatures and temperature gradients in the components this area can significantly reduce the service life.
  • the US-PS 3,588,267 protects a guide vane ring construction in plastic construction, in which the blades are attached to a closed, inner torus and form a self-supporting wreath with it.
  • the outer blade tips are designed without a cover tape and directly in the recesses of a metallic one Glued housing, the elasticity of the bond small relative shifts balances / absorbs. It is obvious that this design is for higher temperatures is completely unusable and at best in the fan or low pressure compressor area Can be used.
  • the invention thus lies in the thermal decoupling of the housing and guide vanes by means of a special design and storage / centering of at least one guide vane ring and by means of air cooling of the housing.
  • the - at least one - guide vane ring is designed as a self-supporting component with a reinforcement on the inner shroud, which stiffens it against slipping axial deformation. Starting from an approximately flat, radial alignment of the blade axes in the unloaded state, these are offset by the static pressure difference in front of / behind the guide blade ring during deflection Zero "axially deflected towards the middle of the rim and possibly also curved.
  • the guide vane rim is therefore mechanically comparable to a disc spring, the inner edge (hole edge) of which forms the inner cover band and the outer edge of which forms the outer cover band.
  • the inner cover band is both axially displaced as well as twisted / inverted due to the blade-induced moments, which means that the material cross-sections of the shroud visible in radial-axial sections are rotated more or less around imaginary axes perpendicular to the cutting surface depending on the rigidity / reinforcement.
  • the inventive reinforcement of the inner shroud against said inversion also reduces the axial deflection of the blade axes and thus the overall deformation of the guide vane ring under load. This improves the dimensional stability of the static component Inner Airseal ".
  • the at least triple bearing which allows radial movements ( Spoke centering ") of the shroud segments practically does not hinder thermal expansion / contraction and thus also contributes to minimizing tension. In addition, exact centering in the housing is achieved.
  • the combination of the guide vane ring construction and bearing arrangement and cooling air ducting according to the invention has the result that the deformation behavior of the ring is mainly determined by the conditions / temperatures in the hot gas, which are also decisive for the rotor behavior. Since the static components of the Inner "- and Outer Airseal "are carried by the guide vane rings and behave in conformity with them, the best possible adaptation of the deformations of the static and rotary sealing components with regard to time course, size and direction is achieved with changing operating conditions (unsteady operation). Thus, the machine can consistently with approximately constant, minimal gaps or leakage losses and thus high efficiency can be achieved, especially in the guide vane area there is no risk of premature component fatigue. The use of brush seals is promoted or even made possible by the conformal behavior of the seal carrier (slight gap change, low eccentricity etc.).
  • the present invention is generally for turbomachines with a rotor and stator, i.e. suitable for compressors and turbines, which at least in sections in Axial design, i.e. with predominantly axial flow.
  • Axial design i.e. with predominantly axial flow.
  • Thermodynamic and due to their size, low-pressure turbines are likely to be medium to large Gas turbine engines are preferred applications, which is why the figure Example from this area shows.
  • the first two stages are from the low-pressure turbine 1 and from this in turn the relevant elements of the top half are shown, with the turbine / engine axis would run horizontally below the representation.
  • the flow direction of the working gas runs from left to right, i.e. first through the guide vane ring 14, then through the area of the blades 3, then through the guide vane ring 15 and through the area of the moving blades 4, whereby further stages (leading, running) can follow.
  • the outer engine casing forms the housing 13 in which the guide vane rings 14, 15 are radially centered and are axially fixed. Both the blades 3,4 and the vane rings 14, 15 are designed with inner and outer cover bands 5 to 8 and 16 to 19, the inner and outer blade shrouds between each the blades have gaps, including damaged blades can be replaced individually are.
  • the guide vane rings 14, 15 are designed as self-supporting components, their mechanical stability being achieved predominantly in the area of the inner shrouds 16, 17. There are closed in the circumferential direction, ie circumferential ", reinforcements 20, 21 arranged, which also decisively influence the thermal behavior (changes in shape and shape) of the guide vane rings 14, 15.
  • the gas forces during operation cause, among other things, an inverting axial deformation of the guide vane rings, ie an axial deflection increasing from the outer to the inner shroud with some twisting of the shrouds plate spring-like "deformation can be significantly reduced by the reinforcements on the inner cover bands.
  • the reinforcements shown are, for example, the toroidal hollow bodies shown, axially spaced rings, combinations of hollow and solid profiles, etc., the space conditions also playing a role.
  • the reinforcements should play a role.
  • the reinforcements should in any case - in the axial / radial section - have as large a moment of inertia as possible about a radial axis, for example through the center of gravity, which can be achieved by sufficient, axially spaced area portions.
  • the area portions of the shroud are to be taken into account here.
  • the determination of the stresses and deformations in the Stülpen is possible using relevant calculation methods.
  • the reinforcement 20 is positively connected to the shroud 16, the Guide vane ring 14 can consist of several segments, which on the reinforcement be held together.
  • the reinforcement 21, however, is in the shroud 17 integrated, i.e. integrally joined with this.
  • Guide vane segments are the starting parts, which by welding or Solder in the area of the inner shroud / reinforcement.
  • outer shrouds 18, 19 should still be segmented in the installed state be, i.e. have several joints on the circumference to prevent thermal stress minimize.
  • the Inner Airseal is - at least predominantly - designed with brush seals, brushes 22, 23 fastened in the area of the guide vane ring reinforcements running against rings 11, 12 connected to the rotor 2, which form axial stops for the rotor blades 3, 4.
  • the honeycomb carriers 28, 29 are in turn mounted on the guide vane rings 14, 15 and are therefore adapted to the deformation behavior thereof.
  • air cooling is used for the housing and the bearing units the guide vane rings provided, which is not so constructively is complex, like an ACC system.
  • an air guide shell 30 is arranged at a radial distance, so that between this and the housing cooling air can flow in the longitudinal direction of the engine.
  • the admission the cooling air, which is usually branched off from the compressor, is carried out via bores 35 into a first chamber 33.
  • the air guide shell has in the area of the bearing journals 26 and 27 30 deliberately gas-permeable openings 31,32, so that part of the cooling air along the journals 26, 27 in the area of the outer shrouds 18, 19 of the guide vane rings 14.15 can flow, a corresponding pressure drop (Cooling air overpressure) provided.
  • This cools the bearings and Heat flows from the vane rings to the housing are minimized.
  • the wall element 37 has - not shown - restrictors or forms itself with corresponding ones Throttle columns a restrictor for the cooling air, so that this in the subsequent Chamber 34 enters with reduced pressure. It is sufficient if the cooling air only a moderate overpressure in relation to the working gas in the adjacent one Has flow channel.
  • the pressure of the working gas decreases axially, it makes sense to also to reduce the cooling air pressure at least in a few stages, which is here is achieved by the chamber design mentioned with restrictors. High pressures the cooling air would also have a high compressive strength of the air guide shell 30 require, i.e. larger wall thicknesses and more weight.
  • Wall elements 36, 38 There are more between the flow channel of the working gas and the cooling air channel Wall elements 36, 38 arranged, which secondary gas flows, i.e. -losses, to prevent through these passages. For cooling reasons, these are also Wall elements 36, 38 deliberately designed or fastened somewhat gas-permeable.
EP99103156A 1998-02-20 1999-02-18 Configuration des aubes de guidage pour une turbomachine axiale Expired - Lifetime EP0937864B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19807247A DE19807247C2 (de) 1998-02-20 1998-02-20 Strömungsmaschine mit Rotor und Stator
DE19807247 1998-02-20

Publications (3)

Publication Number Publication Date
EP0937864A2 true EP0937864A2 (fr) 1999-08-25
EP0937864A3 EP0937864A3 (fr) 2000-10-25
EP0937864B1 EP0937864B1 (fr) 2003-08-13

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Family Applications (1)

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EP99103156A Expired - Lifetime EP0937864B1 (fr) 1998-02-20 1999-02-18 Configuration des aubes de guidage pour une turbomachine axiale

Country Status (4)

Country Link
US (1) US6139263A (fr)
EP (1) EP0937864B1 (fr)
JP (1) JP4230040B2 (fr)
DE (2) DE19807247C2 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011018072A3 (fr) * 2009-08-14 2011-09-15 Mtu Aero Engines Gmbh Turbomachine
CN103482219A (zh) * 2013-09-16 2014-01-01 沈阳黎明航空发动机(集团)有限责任公司 一种燃气轮机运输过程中对转子进行轴、径向定位方法
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
EP2796667A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Bague d'étanchéité glissante
EP2947281A1 (fr) * 2014-05-14 2015-11-25 MTU Aero Engines GmbH Système de boîtier de turbine à gaz

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IT1318103B1 (it) * 2000-07-03 2003-07-23 Nuovo Pignone Spa Sistema di connessione tra un ugello di bassa pressione ed untransition duct in una turbina a gas
DE10037837C2 (de) * 2000-08-03 2002-08-01 Mtu Aero Engines Gmbh Aufhängung
JP2002129901A (ja) * 2000-10-30 2002-05-09 Ishikawajima Harima Heavy Ind Co Ltd チップシュラウド構造
DE10064272A1 (de) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Turbinenschaufel für eine Gasturbine
DE10122464C1 (de) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring
US7059821B2 (en) * 2003-05-07 2006-06-13 General Electric Company Method and apparatus to facilitate sealing within turbines
DE10359730A1 (de) 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
DE102004016222A1 (de) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine
GB2448116B (en) * 2007-04-05 2009-05-27 Rolls Royce Plc Means for cooling a bearing assembly
US8090456B2 (en) * 2008-11-03 2012-01-03 United Technologies Corporation System and method for design and control of engineering systems utilizing component-level dynamic mathematical model
US8315741B2 (en) * 2009-09-02 2012-11-20 United Technologies Corporation High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control
US8668434B2 (en) * 2009-09-02 2014-03-11 United Technologies Corporation Robust flow parameter model for component-level dynamic turbine system control
DE102009042029A1 (de) * 2009-09-17 2011-03-24 Mtu Aero Engines Gmbh Schaufelkranz für eine Strömungsmaschine
DE102009052314A1 (de) 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Dichtanordnung für eine Gasturbine und eine derartige Gasturbine
US20110255959A1 (en) * 2010-04-15 2011-10-20 General Electric Company Turbine alignment control system and method
US9371733B2 (en) 2010-11-16 2016-06-21 Mtu Aero Engines Gmbh Rotor blade arrangement for a turbo machine
DE102011083814A1 (de) 2011-09-30 2013-04-04 Mtu Aero Engines Gmbh Segmentiertes Bauteil
EP2647795B1 (fr) 2012-04-04 2018-11-07 MTU Aero Engines AG Système d'étanchéité pour turbomachine
EP2647798B1 (fr) 2012-04-04 2015-09-16 MTU Aero Engines AG Procédé de fabrication d'une garniture de rodage
EP2647796A1 (fr) 2012-04-04 2013-10-09 MTU Aero Engines GmbH Système d'étanchéité pour turbomachine
KR101480089B1 (ko) 2012-05-10 2015-01-08 이병화 목재용 앵커 볼트
US10975721B2 (en) * 2016-01-12 2021-04-13 Pratt & Whitney Canada Corp. Cooled containment case using internal plenum
IT201900014736A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
IT201900014724A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
IT201900014739A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
CN115387906B (zh) * 2022-05-12 2024-04-16 中国航发四川燃气涡轮研究院 低进口轮毂比发动机的进气承力框架连接结构及装配方法

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DE2745130C2 (de) 1977-10-07 1980-01-03 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Dichtungseinrichtung für die freien Schaufelenden von Axialturbinen
DE3336420A1 (de) 1982-10-06 1984-04-12 Rolls-Royce Ltd., London Mechanismus zur verhinderung eines ueberdrehens des turbinenrotors eines gasturbinentriebwerks im falle eines wellenbruches
DE3540943C2 (fr) 1985-11-19 1992-01-23 Mtu Muenchen Gmbh

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011018072A3 (fr) * 2009-08-14 2011-09-15 Mtu Aero Engines Gmbh Turbomachine
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
US9605551B2 (en) 2012-10-12 2017-03-28 MTU Aero Engines AG Axial seal in a casing structure for a fluid flow machine
EP2796667A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Bague d'étanchéité glissante
US9835039B2 (en) 2013-04-24 2017-12-05 MTU Aero Engines AG Slide ring seal
CN103482219A (zh) * 2013-09-16 2014-01-01 沈阳黎明航空发动机(集团)有限责任公司 一种燃气轮机运输过程中对转子进行轴、径向定位方法
CN103482219B (zh) * 2013-09-16 2016-06-01 沈阳黎明航空发动机(集团)有限责任公司 一种燃气轮机运输过程中对转子进行轴、径向定位方法
EP2947281A1 (fr) * 2014-05-14 2015-11-25 MTU Aero Engines GmbH Système de boîtier de turbine à gaz
US9816386B2 (en) 2014-05-14 2017-11-14 MTU Aero Engines AG Casing arrangement for a gas turbine

Also Published As

Publication number Publication date
JP4230040B2 (ja) 2009-02-25
JPH11294103A (ja) 1999-10-26
EP0937864A3 (fr) 2000-10-25
DE19807247A1 (de) 1999-09-09
DE59906550D1 (de) 2003-09-18
DE19807247C2 (de) 2000-04-20
US6139263A (en) 2000-10-31
EP0937864B1 (fr) 2003-08-13

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