EP1055052A1 - Verfahren zum erkennen eines wellenbruches in einer strömungskraftmaschine - Google Patents
Verfahren zum erkennen eines wellenbruches in einer strömungskraftmaschineInfo
- Publication number
- EP1055052A1 EP1055052A1 EP99955983A EP99955983A EP1055052A1 EP 1055052 A1 EP1055052 A1 EP 1055052A1 EP 99955983 A EP99955983 A EP 99955983A EP 99955983 A EP99955983 A EP 99955983A EP 1055052 A1 EP1055052 A1 EP 1055052A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- shaft
- frequency
- roller bearing
- roller
- rotational
- 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
Links
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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/02—Shutting-down responsive to overspeed
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
- F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
Definitions
- the invention relates to a method for detecting a shaft break in a turbo engine with the aim of subsequently initiating a suitable speed-limiting measure, in particular a rapid fuel cut-off in an aircraft gas turbine system, with a torque-releasing turbine rotor and a torque-absorbing unit being monitored for breakage , essentially connected at the end in at least two roller bearings.
- Speed-limiting devices for aircraft engines in the event of a shaft break between the energy-consuming part (e.g. the compressor) and the energy-generating part (e.g. the turbine runner) have been designed in a number of known inventions by a mechanical operating principle in such a way that there is an axial relative movement between the guide apparatus and the blades of the turbine runner come to create a collision between the nozzle and the blades. In this collision (also called “tangling”), the rotational energy of the turbine rotor is reduced until the turbine rotor comes to a standstill by means of deformation, friction and destruction of the turbine blades in question.
- the patents US 4,505,104, US 4,503,667 and US 4,498 are for this principle of action. 291 mentioned as examples.
- Another mechanical solution for limiting overspeed conditions in the event of a shaft break between the low-pressure turbine and the fan is used in aircraft engines with lower drive powers, the drive shaft between the fan and the low-pressure turbine being equipped with a reference shaft. If a shaft breaks, the broken drive shaft and the reference shaft change their position relative to each other. A pre-tensioned driver is released and gets caught in a wire loop. As a result of a resulting pulling movement on the wire loop as a result of the low-pressure turbine rotating, a rapid fuel cut-off is implemented via the cable pull.
- a commercial disadvantage for a problem to be solved in this way is therefore the large number of systems used, which have to be re-adapted to the specific conditions of the respective aircraft engine.
- a mechanical system with a reference shaft is at least subject to the partial loss of components when required, in addition to the fact that such a system means additional mass for the engine, which is of course undesirable in an aircraft engine.
- the mass-cost ratio of mechanical solutions for realizing the required function of a safety shutdown in the event of a shaft break between the fan and the low-pressure turbine can be classified as disadvantageous from the point of view of the manufacturing costs and the operating costs. Electromechanical or electronic solutions have a clear advantage here from the point of view of the total costs.
- the known electromechanical and electronic processes have hitherto been classified as technically unsuitable for aircraft engines with lower propulsion powers, since they do not react quickly enough in combustion fluid-flow engines with very small moments of inertia when required.
- the required measurement period is too long in relation to the time that remains to recognize such a condition quickly enough in the event of a shaft break in smaller engines, to form the required actuating signal and to carry out the rapid shutdown.
- the object of the present invention is to show an improved, in particular cost-effective and reliable method for detecting a shaft break in a turbo engine.
- the solution to this problem is characterized in that the rotational frequencies of the two shaft ends in the roller bearings of the shaft to be monitored for breakage are determined continuously and essentially in real time and compared with one another, and in that at a higher rotational frequency than the rotational frequency at the roller bearing of the torque-absorbing unit a breakage of the shaft is concluded on the roller bearing on the turbine rotor side.
- the present invention preferably relates to the problem of a shaft break between the fan as a torque-absorbing unit and the torque-releasing low-pressure turbine rotor of an aircraft engine or an aircraft gas turbine system and the required speed limitation of the low-pressure turbine rotor, but can be used analogously on any flow engine.
- the aim is to use such a method and the associated device, which is based on an electromechanical / electronic design.
- the rotational frequency of the respective shaft end in the respective rolling bearing is therefore to be determined on a shaft of a fluid-flow engine which is essentially mounted at the end in rolling bearings. If the rotational frequencies of the two shaft ends differ significantly from one another, there is obviously a shaft break, so that a suitable speed-limiting measure is then initiated.
- Such a measuring method is characterized by the highest speed and an aviation safety that can be preferred
- the rotation frequency of the roller bearing cage and / or the rollover frequency of the roller bearing outer ring and / or the rollover frequency of the roller bearing inner ring and / or the roller body rotation frequency is fixed in real time for both roller bearings via a filter unit and the rotational frequencies of the shaft ends mounted in the roller bearings can be determined separately
- Figure 2 shows the geometry and the movement conditions on one
- FIG. 4 finally shows the determination of the nominal pressure angle ⁇ 0 and the operating pressure angle ⁇ B for angular contact ball bearings.
- f ⁇ denotes the rotational frequency of the respective shaft end in the roller bearing and z the number of rolling elements.
- FIG. 5 shows a typical vibration spectrum for a rolling bearing with an acceleration sensor as a measuring signal sensor.
- the aircraft engine shown in FIG. 6 consists of a high-pressure system 1 and a low-pressure system 2, which are equipped with shafts 3 and 4 for power transmission.
- the two shafts 3, 4 are not mechanically connected to one another and thus rotate independently of one another.
- the fan 2 consists of the fan 2a, the rotor of the booster stage 2b and the low-pressure turbine runner 2c, which are connected to one another via the shaft 3.
- the high-pressure compressor runner 1a and the high-pressure turbine runner 1b are connected via the shaft 4
- the low-pressure turbine rotor 2c is without load. The consequence of this would be an uncontrolled rapid growth the rotational speed of the low-pressure turbine runner 2c In the worst case, the maximum permissible rotational speed for the low-pressure turbine runner 2c could then be exceeded within a short time.As a result of the centrifugal overload and the insufficient strength, it could possibly be destroyed by sudden exploding of the low-pressure turbine runner 2c come
- the shaft 3 is supported on the side of the torque-absorbing unit in the form of the fan 2a and the booster stage 2b via a roller bearing 6 designed as a deep groove ball bearing.
- a roller bearing 6 designed as a deep groove ball bearing.
- the shaft 3 is supported by a roller bearing 7 with cylindrical roller bodies.
- Two measuring signal sensors 8a and 8b in the form of acceleration sensors are coupled to the roller bearing 6 on the fan side.
- Two such measuring signal sensors 9a and 9b designed as acceleration sensors are also provided on the roller bearing 7 on the turbine rotor side.
- the redundant arrangement of the accelerometers on the roller bearings 6, 7 is provided in particular for reasons of improved functional reliability.
- a second accelerometer is provided which provides a measurement signal.
- a separate measuring channel of identical design is provided for each of the two roller bearings 6 and 7. Since only a single measurement signal is required per roller bearing 6 or 7, the two measurement signal recorders 8a and 8b are connected to an OR gate 10. In an analogous manner, an OR gate 11 is responsible for the measurement signal pickups 9a and 9b.
- OR gates 10 and 1 1 each leave a periodic measurement signal in the time domain, which is assigned to the respective roller bearings 6 and 7.
- t denotes a point in time and "T” the period of the periodic function.
- the measured value functions which have undergone a significant data reduction without loss of information, pass through the filters 14 and 15.
- These filters 14, 15 are designed such that they can only pass a frequency band from 0 Hz to the maximum frequency which can be followed Equation (C) given above (in connection with FIGS. 2-4), which represents the rollover frequency of the inner race of the rolling bearing, is determined.
- the value f n in this equation (C) corresponds to the maximum permissible rotational frequency of the low-pressure turbine rotor 2c.
- the filtering mentioned takes place almost instantaneously under real-time conditions.
- the preprocessed and filtered measurement result is then made available to the arithmetic processors 16 and 17.
- Both arithmetic processors 16 and 17 operate independently of one another and have a data processing speed that meets real-time requirements.
- the arithmetic processors 16 and 17 can be used to determine the following values for the roller bearings 6 and 7, namely by means of calculation methods (not described in more detail) from the amplitude spectra provided
- arithmetic processors 16 and 17 calculate according to equations (A) to (D) given above each separately the rotational frequency fm on the roller bearing 6 and the rotational frequency f n2 on the roller bearing 7, the rotational frequency f n1 corresponds to that of the torque-absorbing unit or fan s 2a and the rotational frequency f n2 to that of the low-pressure turbine runner 2c
- the measurement signal to be a high safety standard redundancy and accuracy of the measurement information on the basis of the normal distribution of the measurement error of statistical measurement processes can regard the arithmetic processors 16 and 17 carry out a comparison of the rotational frequencies determined according to equations (A) to (D) for the roller bearings, a predefined spreading width not being allowed to be exceeded
- the Gaussian method of the smallest squares of errors is preferably used to determine the effective values f "and f n2 and the standard deviations O T and ⁇ 2 of the measurement results, which are then used as a basis for a subsequent evaluation.
- the Rotation frequency information in the form ⁇ f n ⁇ ⁇ ⁇ ⁇ ⁇ and ⁇ f n2 ⁇ ⁇ 2 ⁇
- the inflow to the fuel ring line 19 is equipped with a fuel quick-closing valve 20.
- This fuel quick-closing valve 20, which is not shown with an electromagnetic actuator 22, is always kept closed by means of a spring 21 in the electrically non-energized state
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19857552A DE19857552A1 (de) | 1998-12-14 | 1998-12-14 | Verfahren zum Erkennen eines Wellenbruches in einer Strömungskraftmaschine |
DE19857552 | 1998-12-14 | ||
PCT/EP1999/008717 WO2000036280A1 (de) | 1998-12-14 | 1999-11-12 | Verfahren zum erkennen eines wellenbruches in einer strömungskraftmaschine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1055052A1 true EP1055052A1 (de) | 2000-11-29 |
EP1055052B1 EP1055052B1 (de) | 2004-06-02 |
Family
ID=7890982
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99955983A Expired - Lifetime EP1055052B1 (de) | 1998-12-14 | 1999-11-12 | Verfahren zum erkennen eines wellenbruches in einer strömungskraftmaschine |
Country Status (4)
Country | Link |
---|---|
US (1) | US6494046B1 (de) |
EP (1) | EP1055052B1 (de) |
DE (2) | DE19857552A1 (de) |
WO (1) | WO2000036280A1 (de) |
Families Citing this family (46)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE0101984D0 (sv) * | 2001-05-31 | 2001-05-31 | Skf Ab | A device, computer program product and method for indicating a function deviation of one or more details of manufacturing equipment using frequency component analyses |
DE10207455B4 (de) | 2002-02-22 | 2006-04-20 | Framatome Anp Gmbh | Verfahren und Einrichtung zur Detektion einer impulsartigen mechanischen Einwirkung auf ein Anlagenteil |
DE10310900A1 (de) * | 2003-03-13 | 2004-09-23 | Rolls-Royce Deutschland Ltd & Co Kg | Elekronisches Sicherheitssystem zur Vermeidung eines Überdrehzahlzustandes bei einem Wellenbruch |
DE102004026366A1 (de) * | 2004-05-29 | 2005-12-15 | Mtu Aero Engines Gmbh | Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine |
DE102004033924A1 (de) * | 2004-07-14 | 2006-02-09 | Mtu Aero Engines Gmbh | Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine |
DE102004047892A1 (de) * | 2004-10-01 | 2006-04-06 | Mtu Aero Engines Gmbh | Gasturbine und Verfahren zum Abschalten einer Gasturbine bei Identifikation eines Wellenbruchs |
WO2007068550A1 (de) | 2005-12-16 | 2007-06-21 | Siemens Aktiengesellschaft | Überwachungseinrichtung bzw. überwachungsverfahren für eine antriebseinrichtung |
DE102006004941B4 (de) * | 2006-02-03 | 2008-01-10 | Areva Np Gmbh | Verfahren und Einrichtung zur Detektion des Ortes einer impulsartigen mechanischen Einwirkung auf ein Anlagenteil |
DE102006004947B4 (de) | 2006-02-03 | 2007-12-27 | Areva Np Gmbh | Verfahren und Einrichtung zur Detektion einer impulsartigen mechanischen Einwirkung auf ein Anlagenteil |
US8818683B2 (en) * | 2006-04-21 | 2014-08-26 | General Electric Company | Method and apparatus for operating a gas turbine engine |
FR2916482B1 (fr) | 2007-05-25 | 2009-09-04 | Snecma Sa | Systeme de freinage en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz |
FR2916483B1 (fr) | 2007-05-25 | 2013-03-01 | Snecma | Systeme de dissipation d'energie en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz |
FR2923540B1 (fr) | 2007-11-13 | 2010-01-29 | Snecma | Dispositif de detection de rupture d'un arbre de turbomachine |
DE102008007519A1 (de) | 2008-02-05 | 2009-08-13 | Nordex Energy Gmbh | Vorrichtung zur Überwachung der Drehzahl bei einer Windenergieanlage |
EP2131178B1 (de) * | 2008-06-02 | 2011-04-06 | Siemens Aktiengesellschaft | Diagnoseverfahren für zumindest ein Kugellager, insbesondere für ein Schrägkugellager, korrespondierendes Diagnosesystem sowie Verwendung eines derartigen Diagnosesystems |
FR2939924B1 (fr) * | 2008-12-15 | 2012-10-12 | Snecma | Identification de defaillances dans un moteur d'aeronef |
US8752394B2 (en) * | 2010-03-15 | 2014-06-17 | Rolls-Royce Corporation | Determining fan parameters through pressure monitoring |
GB2488805A (en) * | 2011-03-09 | 2012-09-12 | Rolls Royce Plc | Shaft break detection |
GB201120511D0 (en) * | 2011-11-29 | 2012-01-11 | Rolls Royce Plc | Shaft break detection |
GB201121639D0 (en) * | 2011-12-16 | 2012-01-25 | Rolls Royce Plc | Shaft break detection |
FR2987085B1 (fr) * | 2012-02-20 | 2014-03-21 | Snecma | Procede de securisation du fonctionnement d'une turbomachine |
SG11201405922SA (en) | 2012-04-05 | 2014-10-30 | United Technologies Corp | Geared turbofan gas turbine engine with reliability check on gear connection |
US20140178175A1 (en) * | 2012-12-21 | 2014-06-26 | United Technologies Corporation | Air turbine starter monitor system |
US20160123180A1 (en) * | 2013-06-24 | 2016-05-05 | United Technologies Corporation | Over speed monitoring using a fan drive gear system |
US10048144B2 (en) * | 2013-07-12 | 2018-08-14 | Pratt & Whitney Canada Corp. | Method and system for applying a compressive preload |
DE112015001843A5 (de) * | 2014-04-16 | 2017-01-19 | Schaeffler Technologies AG & Co. KG | Verfahren zur Verminderung von Rupfschwingungen einer Reibungskupplung in einem Antriebsstrang eines Kraftfahrzeugs |
US9708927B2 (en) | 2014-07-09 | 2017-07-18 | Siemens Energy, Inc. | Optical based system and method for monitoring turbine engine blade deflection |
ES2780689T3 (es) * | 2014-10-01 | 2020-08-26 | Ge Renewable Tech | Máquina rotativa e instalación para convertir energía que comprende tal máquina |
EP3040520B1 (de) * | 2015-01-05 | 2019-07-03 | Rolls-Royce PLC | Turbinenmotor-wellenbrucherkennung |
US9663278B1 (en) | 2015-12-16 | 2017-05-30 | II Harold C. Daws | Container with improved locking system |
US10228305B2 (en) | 2016-01-18 | 2019-03-12 | Pratt & Whitney Canada Corp. | Shaft shear detection through shaft oscillation |
US10228304B2 (en) | 2016-01-18 | 2019-03-12 | Pratt & Whitney Canada Corp. | Shaft shear detection through shaft oscillation |
US10180078B2 (en) | 2016-06-17 | 2019-01-15 | Pratt & Whitney Canada Corp. | Shaft shear detection in gas turbine engines |
GB201611674D0 (en) * | 2016-07-05 | 2016-08-17 | Rolls Royce Plc | A turbine arrangement |
US10989063B2 (en) * | 2016-08-16 | 2021-04-27 | Honeywell International Inc. | Turbofan gas turbine engine shaft break detection system and method |
US10316689B2 (en) | 2016-08-22 | 2019-06-11 | Rolls-Royce Corporation | Gas turbine engine health monitoring system with shaft-twist sensors |
EP3330494B1 (de) * | 2016-12-02 | 2019-11-27 | Rolls-Royce Deutschland Ltd & Co KG | Anordnung, turbomaschine und verfahren zur erkennung eines wellenbruchs |
EP3330493B1 (de) * | 2016-12-02 | 2019-05-01 | Rolls-Royce Deutschland Ltd & Co KG | Steuerungssystem und -verfahren für einen gasturbinenmotor |
US10436060B2 (en) * | 2016-12-09 | 2019-10-08 | Pratt & Whitney Canada Corp. | Shaft event detection in gas turbine engines |
US11136134B2 (en) * | 2018-12-21 | 2021-10-05 | Pratt & Whitney Canada Corp. | System and method for operating a gas turbine engine coupled to an aircraft propeller |
CN109578795B (zh) * | 2019-01-30 | 2023-10-20 | 潍柴动力扬州柴油机有限责任公司 | 一种十字万向轴防飞脱装置 |
US11333035B2 (en) * | 2019-07-24 | 2022-05-17 | Pratt & Whitney Canada Corp. | Shaft shear detection in a gas turbine engine |
GB2593689A (en) * | 2020-03-30 | 2021-10-06 | Rolls Royce Plc | Gas turbine engine |
FR3111668B1 (fr) * | 2020-06-17 | 2023-04-07 | Airbus Helicopters | Procédé pour arrêter un moteur en survitesse, système et giravion associés |
IT202000028520A1 (it) | 2020-11-26 | 2022-05-26 | Ge Avio Srl | Sistema e metodo per la mitigazione di velocita' eccessiva di rotore |
CN114017267B (zh) * | 2021-11-16 | 2024-06-11 | 西安热工研究院有限公司 | 一种风力发电机组变桨轴承故障诊断方法及系统 |
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US3963372A (en) * | 1975-01-17 | 1976-06-15 | General Motors Corporation | Helicopter power plant control |
JPS5444106A (en) * | 1977-09-14 | 1979-04-07 | Hitachi Ltd | Speed controlling method for steam turbine |
JPS54111871A (en) * | 1978-02-22 | 1979-09-01 | Hitachi Ltd | Frequency detecting method |
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AT370851B (de) * | 1980-07-07 | 1983-05-10 | Simmering Graz Pauker Ag | Turbinen-regel- und schutzsystem |
US4712372A (en) * | 1985-09-18 | 1987-12-15 | Avco Corporation | Overspeed system redundancy monitor |
JPH04287803A (ja) * | 1991-03-19 | 1992-10-13 | Hitachi Ltd | タービン過速度防止装置 |
NL9401949A (nl) * | 1994-11-22 | 1996-07-01 | Skf Ind Trading & Dev | Werkwijze voor het analyseren van regelmatig geëxciteerde mechanische trillingen. |
DE19524992C1 (de) * | 1995-07-08 | 1996-08-08 | Mtu Muenchen Gmbh | Regelung eines Wellentriebwerks mit einem Mikrosteuergerät |
US5804726A (en) * | 1995-10-16 | 1998-09-08 | Mtd Products Inc. | Acoustic signature analysis for a noisy enviroment |
DE19727296A1 (de) * | 1997-06-27 | 1999-01-07 | Mtu Muenchen Gmbh | Einrichtung zur Notabschaltung einer Gasturbine |
-
1998
- 1998-12-14 DE DE19857552A patent/DE19857552A1/de not_active Withdrawn
-
1999
- 1999-11-12 DE DE59909646T patent/DE59909646D1/de not_active Expired - Lifetime
- 1999-11-12 WO PCT/EP1999/008717 patent/WO2000036280A1/de active IP Right Grant
- 1999-11-12 US US09/622,026 patent/US6494046B1/en not_active Expired - Lifetime
- 1999-11-12 EP EP99955983A patent/EP1055052B1/de not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO0036280A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP1055052B1 (de) | 2004-06-02 |
WO2000036280A1 (de) | 2000-06-22 |
US6494046B1 (en) | 2002-12-17 |
DE59909646D1 (de) | 2004-07-08 |
DE19857552A1 (de) | 2000-06-15 |
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