EP0924388B1 - System zur Konstanthatung des Schaufelspitzenspiels bei einer Gasturbine - Google Patents
System zur Konstanthatung des Schaufelspitzenspiels bei einer Gasturbine Download PDFInfo
- Publication number
- EP0924388B1 EP0924388B1 EP98121690A EP98121690A EP0924388B1 EP 0924388 B1 EP0924388 B1 EP 0924388B1 EP 98121690 A EP98121690 A EP 98121690A EP 98121690 A EP98121690 A EP 98121690A EP 0924388 B1 EP0924388 B1 EP 0924388B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- turbine
- stator
- gas turbine
- orifice
- 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
Links
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 4
- 238000005496 tempering Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 210000001331 nose Anatomy 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Definitions
- the present invention relates to a passive gap holding system according to the preamble of the main claim.
- the invention relates in particular to a passive gap holding system in the turbine part, in particular in the high-pressure turbine, a gas turbine, in its turbine housing arranged next to guide vanes on a rotor, preferably a Blades having shroud are provided, whose or whose Tips from jacket ring segments suspended in the turbine housing below Formation of one of a temperature control duct system in terms of its width controlled gap are surrounded, this tempering channel system from the compressor part of the gas turbine past its combustion chamber Air flow can be fed in via a large number of metering holes ring chamber delimited by a stator ring.
- the environment is referred to DE 3040 594 C2
- a gap system with the additional characteristics of The preamble of claim 1 forms at least the internal state of the art.
- hot reslam case is a hot re-acceleration briefly explained below of the gas turbine engine.
- the turbine housing and the rotor part i.e. the the Turbine rotor disc (s) carrying blades completely at high Level warmed up.
- a further embodiment is previously known from US 3,814,313 A.
- an aperture ring is provided, which is designed as a closed ring and increases in diameter with appropriate heating. This opens a valve seat on one side of the orifice ring, so that an air flow is possible through the slot that forms.
- the other end of the aperture ring is guided radially. It is therefore a massive ring.
- the relatively small thermal diameter increase leads to only a very small gap in the valve arrangement created by the ring, so that only very small air masses can be carried out.
- the present invention has for its object to develop a passive gap system according to the preamble of claim 1 so that the turbine housing is heated rather than cooled, especially when idling.
- the solution to this problem is characterized by one with the metering holes interacting aperture ring which, depending on the Temperature of the air flow brought to these the metering holes closes more or less, with a gap between the Stator ring and the casing ring segments at least with a low turbine load a fraction of what flows over the guide vanes and blades Hot gas in the annular chamber and preferably in the direction of flow the gas turbine viewed the rear area of the same can.
- Advantageous training and further education are included in the subclaims.
- This gap holding system is advantageously a passive system, i.e. the aperture ring takes its required, the Metering holes either releasing or closing position automatically depending on the current boundary conditions, namely of the temperature of the compressor part of the gas turbine at its combustion chamber airflow conveyed past. So that the aperture ring this Function, it could be set up using bimetal technology, for example his; A device according to the invention works particularly simply and reliably Gap system, however, when the aperture ring from a Material with a higher coefficient of thermal expansion than that of the stator ring consists. Alone by the different Thermal expansion of the stator ring on the one hand and the aperture ring on the other the metering holes are either closed or Approved.
- reference number 1 is the turbine housing referred to, within which a plurality of blades 2 - only one of these is shown in fragments - load-bearing Rotor is arranged.
- the turbine housing referred to, within which a plurality of blades 2 - only one of these is shown in fragments - load-bearing Rotor is arranged.
- the turbine part of the gas turbine shown is located upstream of the blade 2 shown or upstream the rotor disk represented by this rotor blade 2 has a ring of Guide vanes 4, of which only one is also shown in fragments is.
- This guide vane (s) 4 is / are, as usual, with their not shown End section over several intermediate parts, also not shown connected to the turbine housing 1.
- jacket ring segments 5 are also here as usual in the circumferential area of the rotor blades 2.
- These jacket ring segments 5 form as usual with respect to the turbine axis, not shown - its axial direction is equal to the flow direction 3 - a closed ring and carry a so-called running-in layer on their inner side facing the moving blades 2 5a.
- the individual are via one or more lugs 5b Sheath ring segments 5 in corresponding recesses 1a of the turbine housing 1 hung.
- the blades 2 are provided with a circumferential shroud 6, but this is irrelevant to the essence of the present invention.
- a gap designated by the letter s is located between the tips 6a of the shroud 6, which serve to seal against gap losses, and the running-in layer 5a. In the case of shrouds 2 without shrouds, this gap s is located between the tips of the blades 2 and the running-in layer 5a, which is why the designation “ tips 6a” is or can be used equally for blades 2 with or without shroud 6.
- the gap s is functionally required, of course, after the blades 2 compared to the jacket ring segments 5 around the not shown Rotate the longitudinal axis of the gas turbine, but this gap s should be avoided leakage losses should be as small as possible.
- this gap s should be avoided leakage losses should be as small as possible.
- the turbine rotor or the blades 2 during operation of the gas turbine due to the action of heat can expand or expand differently than this Rotor blades 2 surrounding turbine housing 1. After the shroud segments 5 but are suspended in the turbine housing 1 changes then the size of the gap s.
- this air flow 8 is promoted by the compressor part of the gas turbine and can branched off from this introduced into the turbine housing 1 at a suitable point become; the embodiment shown here is this airflow 8 around a wall of the engine combustion chamber or gas turbine combustion chamber - only the end section of this is represented by the outer wall 9 - bypassed partial air flow.
- a component of the temperature control duct system 7 mentioned is an annular chamber 7a, which is delimited by a so-called stator ring 10 and in the area of the guide blades 4 between this stator ring 10 and the turbine housing 1 lies.
- annular chamber 7a can the side of the combustion chamber outer wall 9 introduced air flow 8 via the end face in the stator ring 10 the provided metering holes 7b.
- the air flow 8 can leave this annular chamber 7a again and arrives then - as already explained - on the back of these jacket ring segments 5 or in a cavity 7c located there and from there on not shown, for example, in a similar annular chamber 7a ', the between the next guide vane 4 'in the axial direction 3 and the turbine housing 1 is provided.
- an orifice ring is provided in the annular chamber 7a, which cooperates with the metering holes 7b and is designated as a whole by 11 and which more or less closes these metering holes 7b as a function of the temperature of the air flow 8 brought to the metering holes 7b.
- This aperture ring 11 has a so-called. Full ring section 11 a, which with respect forms a circumferential ring of the turbine longitudinal axis, not shown, whose central axis is the turbine longitudinal axis. From this full ring section 11a there are a plurality of so-called diaphragm sections arranged in a ring 11b, which - as can be seen - against the direction of flow 3 or in the axial direction 3 up to the metering holes 7b or almost to the inside of the front wall having these metering bores 7b 10a of the stator ring 10 extend. The is supported via several arms 11c Aperture ring 11 on the stator ring 10, which in a suitable manner with the rest is connected to the turbine housing 1. Regarding this support of the Distinguish the aperture ring 11 and the design of the stator ring 10 the two exemplary embodiments according to FIGS. 1, 2, on what will be discussed in more detail later.
- the diaphragm ring 11 consists of a material whose coefficient of thermal expansion is greater than that of the stator ring 10 carrying the diaphragm ring 11.
- this air flow 8 is due to the compression in the compressor part the gas turbine is relatively hot, i.e. in this normal, normal operating state the gas turbine is operated at high load or full load, i.e. it is in cruise operation or even in "take-off operation".
- the temperature of the air flow 8 is significantly lower. This causes due to the different thermal expansion behavior the stator ring 10 on the one hand and the aperture ring 11 on the other hand that the panel sections 11b against the direction of the arrow 12 again in the in the Figures 1, 2 shown, the metering holes 7b again substantially move covering position.
- an air stream 8 is brought in at a significantly elevated temperature.
- the one then passed through the metering holes 7b Airflow 8 further heats the aperture ring 11, causing it Metering holes 7b continue to be released until the already mentioned so-called normal, but not shown operating state reached is, in which practically only the air flow in the temperature control duct system 7 8 is initiated.
- the stator ring 10 is directly connected to the Turbine housing 1 screwed in a parting line 1b.
- the stator ring 10 formed such that the annular chamber 7a of this and the Turbine housing 1 is limited.
- the aperture ring 11 is in this embodiment via his arms 11c on the inside on the front wall 10a of the Stator ring 10 attached.
- Ring carrier 15 attached, which in turn the Stator ring 10 carries.
- the stator ring 10 lies on the inside on the suitably designed Ring carrier 15 and is not the stator ring 10 in several bores penetrating pins 16 designated by Welding points 17 attached to the stator ring 10 and thus against falling out are secured, fixed to the ring carrier 15. These pins 16 do not protrude into this specified bore holes into the ring carrier 15.
- annular chamber 7a substantially completely bounded by the stator ring 10, which, as can be seen on the outside, has a U-shaped or trough-shaped cross section.
- the aperture ring 11 is different designed and hung as in the embodiment of FIG. 1.
- the aperture ring 11 also has the so-called full ring section 11a and the aperture sections cooperating with the metering bores 7b 11b, wherein between two adjacent such aperture sections 11b one of said pins 16 can pass through the annular chamber 7a, however, here the arms 11c face the diaphragm sections 11b from the full ring section 11a and engage with their free ends into suitable recesses 10c in the ring carrier 15 Wall of the stator ring 10 a.
- This construction enables a particularly effective movement of the diaphragm sections 11b of the diaphragm ring 11 relative to the metering holes 7b in the event of thermal expansion, as can also be seen from FIG. 3, which is briefly explained below and shows the stator ring 10 and the diaphragm ring 11 in enlarged positions in enlarged positions ,
- the various positions of the diaphragm ring 11 or more precisely its diaphragm sections 11b and its arms 11c are designated with the Roman numerals I to IV, these designations being located in each case on the lower edge of the diaphragm sections 11b and on the upper edge of the arms 11c.
- the number I stands for the installation state of the aperture ring 11, the number II for the position when idling ( " idle"), the number III for cruise operation ( “ cruise”) and the number IV for full load operation ("max. off ").
- the arms 11c allow the aperture ring 11 to be free radial movement according to its thermal expansion, however, it due to its radial support or support over the free ends of the Arms 11c is twisted. Due to the radially different temperature expansion and occurs due to the torsion of the aperture ring 11 just mentioned increased radial movement at the ends of the aperture sections 11b in or against the direction of arrow 12 relative to the metering holes 7b, similarly a seesaw. This allows relatively large movements in the direction of the arrow 12 even when small temperature differences occur on the Metering holes 7b can be reached. These relatively large relative movements allow relatively large holes for the metering holes 7b use what with regard to the manufacturing and component tolerances to be observed is advantageous.
- the air flow 8 assumes such high temperatures that the aperture ring 11 is heated further and expands more than the stator ring 10 or as a result of its higher coefficient of thermal expansion the ring carrier 15.
- the orifice ring 11 twists in its full ring section 11a and thereby opens the metering bores 7b, after which the air stream 8 conveyed past the combustion chamber by the compression part of the gas turbine reaches the annular chamber 7a and thus the temperature control duct system 7, so that the turbine housing 1 is cooled as desired.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Zunächst einmal besteht der Blendenring 11 aus einem Material, dessen Wärmeausdehnungskoeffizient größer ist als derjenige des den Blendenring 11 tragenden Statorringes 10.
Im Leerlaufbetrieb der Gasturbine seien gemäß der Darstellung nach Fig.2 die Zumeßbohrungen 7b von den jeweils zugeordneten Blendenabschnitten 11b verschlossen. Ist das Gasturbinen-Triebwerk vollständig kalt, d.h. beispielsweise im Aufbauzustand desselben, befindet sich zwischen den freien Enden der Arme 11 c und deren radialer Anlagefläche 15a am Ringträger 15 ein aus Fig. 3 ersichtlicher Spalt. Dieser Spalt wird zunächst abgebaut, wenn sich das Turbinengehäuse 1 und somit der Statorring 10 sowie der Blendenring 11 erwärmt, wobei letzterer - wie bereits erwähnt - einen höheren Wärmeausdehnungskoeffizienten besitzt als der Statorring 10, aber auch als der Ringträger 15 sowie als das Turbinengehäuse 1. Wird dann die Gasturbine mit Hochlast betrieben (beispielsweise Reiseflugbetrieb oder "take-off") so nimmt der Luftstrom 8 derart hohe Temperaturen an, daß der Blendenring 11 weiter erwärmt wird und sich hierbei durch seinen höheren Wärmeausdehnungskoeffizienten stärker ausdehnt als der Statorring 10 bzw. als der Ringträger 15. Hierdurch tordiert der Blendenring 11 in seinem Vollringabschnitt 11a und öffnet dabei die Zumeßbohrungen 7b, wonach der vom Verdichterteil der Gasturbine an deren Brennkammer vorbei geförderte Luftsrom 8 in die Ringkammer 7a und somit in das Temperierkanalsystem 7 gelangt, so daß dann das Turbinengehäuse 1 wie gewünscht gekühlt wird. Selbstverständlich tritt auch hier die bereits erläuterte Veränderung bezügliches des Spaltes 13, über welchen ein Bruchteil von Heißgas in das Temperierkanalsystem 7 gelangen kann, auf, nämlich daß dieser Spalt 13 im Hochlastbetrieb der Gasturbine wesentlich enger ist als im Leerlaufbetrieb. Der wesentliche Unterschied des Ausführungsbeispieles nach Fig. 2 gegenüber demjenigen nach Fig. 1 liegt jedoch darin, daß aufgrund des beschriebenen Torsionseffektes bereits relativ geringe Temperaturunterschiede von beispielsweise 200°C ausreichend sind, um die Zumeßbohrungen 7b entweder freizulegen oder mittels der Blendenabschnitte 11b abzusperren.
- 1
- Turbinengehäuse
- 1 a
- Aussparung zur Aufnahme von 5a
- 1b
- Trennfuge
- 2
- Laufschaufel
- 3
- Strömungsrichtung = Axialrichtung
- 4,4'
- Leitschaufel
- 4a
- Endabschnitt
- 5
- Mantelringsegment
- 5a
- Einlaufschicht
- 5b
- Nase von 5
- 6
- Deckband von 2
- 6a
- Spitze(n) von 6 bzw. 2
- 7
- Temperierkanalsystem
- 7a
- Ringkammer (im Bereich von 4)
- 7a'
- Ringkammer (im Bereich von 4')
- 7b
- Zumessbohrung
- 7c
- Hohlraum, rückseitig von 5
- 8
- Luftstrom durch 7
- 9
- Endabschnitt der Brennkammeraußenwand
- 10
- Statorring
- 10a
- Stirnwand von 10
- 10b
- Ausnehmung in 10, in die 4a hineinragt
- 10c
- Aussparung in 10, in die 11c eingreift
- 11
- Blendenring
- 11 a
- Vollringabschnitt
- 11 b
- Blendenabschnitt
- 11 c
- Arme
- 12
- Pfeilrichtung (11b legt 7b frei)
- 13
- Spalt
- 14
- Pfeil: Luftströmung durch 13
- 15
- Ringträger
- 15a
- radiale Anlagefläche an 15 bezüglich der freien Enden von 11c
- 16
- Stift
- 17
- Schweißpunkt
- s
- Spalt zwischen 6a und 5a
Claims (4)
- Passives Spalthaltungssystem im Turbinenteil einer Gasturbine, in deren Turbinengehäuse (1) neben Leitschaufeln (4) auf einem Rotor angeordnete, vorzugsweise ein Deckband (6) aufweisende Laufschaufeln (2) vorgesehen sind,
deren oder dessen Spitzen (6a) von im Turbinengehäuse (1) aufgehängten Mantelringsegmenten (5) unter Bildung eines von einem Temperierkanalsystem (7) hinsichtlich seiner Breite gesteuerten Spaltes (s) umgeben sind,
wobei diesem Temperierkanalsystem (7) ein vom Verdichterteil der Gasturbine an deren Brennkammer vorbei geförderter Luftstrom (8) zuführbar ist, der über eine Vielzahl von Zumessbohrungen (7b) in eine von einem Statorring (10) begrenzte Ringkammer (7a) gelangt,
wobei ein mit den Zumessbohrungen (7b) zusammenwirkender Blendenring (11), der in Abhängigkeit von der Temperatur des zu diesen herangeführten Luftstromes (8) diese Zumessbohrungen (7b) mehr oder weniger verschließt, vorgesehen ist,
wobei über einen Spalt (13) zwischen dem Statorring (10) und den Mantelringsegmenten (5) zumindest bei niedriger Turbinenlast ein Bruchteil des über die Leitschaufeln (4) und Laufschaufeln (2) strömenden Heißgases in die Ringkammer (7a) und dabei bevorzugt in den in Strömungsrichtung (3) der Gasturbine betrachtet hinteren Bereich derselben gelangen kann, wobei der Blendenring (11) aus einem Material mit einem gegenüber demjenigen des Statorringes (10) höheren Wärmeausdehnungskoeffizienten besteht,
dadurch gekennzeichnet, daß der Blendenring (11) innerhalb der Ringkammer (7a) angeordnet ist und mit den stimseitig im Statorring (10) vorgesehenen Zumessbohrungen (7b) zusammenwirkende Blendenabschnitte (11b) aufweist, die im wesentlichen in Axialrichtung (3) der Gasturbine von einem Vollringabschnitt (11a) des Blendenringes (11) abstehen, der sich über Arme (11c) am Statorring (10) abstützt. - Spalthaltungssystem nach Anspruch 1,
dadurch gekennzeichnet, daß die vom Vollringabschnitt (11 a) des Blendenringes (11) entgegengerichtet zu den Blendenabschnitten (11b) abstehenden Arme (11c) mit ihren freien Enden in Aussparungen (10c) im Statorring (10) eingreifen. - Spalthaltungssystem nach einem der Ansprüche 1 oder 2,
dadurch gekennzeichnet, daß sich die Leitschaufeln (4) mit ihren freien Endabschnitten (4a) zumindest im Hochlastbetrieb in Axialrichtung (3) am Statorring (10) abstützen. - Spalthaltungssystem nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß der Statorring (10) über mehrere Stifte (16) an einem mit dem Turbinengehäuse (1) verbundenem Ringträger (15) fixiert ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19756734A DE19756734A1 (de) | 1997-12-19 | 1997-12-19 | Passives Spalthaltungssystem einer Gasturbine |
DE19756734 | 1997-12-19 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0924388A2 EP0924388A2 (de) | 1999-06-23 |
EP0924388A3 EP0924388A3 (de) | 2000-08-16 |
EP0924388B1 true EP0924388B1 (de) | 2003-09-24 |
Family
ID=7852654
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98121690A Expired - Lifetime EP0924388B1 (de) | 1997-12-19 | 1998-11-13 | System zur Konstanthatung des Schaufelspitzenspiels bei einer Gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US6126390A (de) |
EP (1) | EP0924388B1 (de) |
DE (2) | DE19756734A1 (de) |
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DE10048156A1 (de) * | 2000-09-28 | 2002-04-11 | Rolls Royce Deutschland | Turbinendeckbandsegmentbefestigung |
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DE50204128D1 (de) * | 2001-12-13 | 2005-10-06 | Alstom Technology Ltd Baden | Heissgaspfad-baugruppe einer gasturbine |
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US8939709B2 (en) | 2011-07-18 | 2015-01-27 | General Electric Company | Clearance control for a turbine |
FR2983518B1 (fr) | 2011-12-06 | 2014-02-07 | Snecma | Dispositif deverrouillable d'arret axial d'une couronne d'etancheite contactee par une roue mobile de module de turbomachine d'aeronef |
US9238971B2 (en) | 2012-10-18 | 2016-01-19 | General Electric Company | Gas turbine casing thermal control device |
US9422824B2 (en) | 2012-10-18 | 2016-08-23 | General Electric Company | Gas turbine thermal control and related method |
DE102013210876B4 (de) | 2013-06-11 | 2015-02-26 | MTU Aero Engines AG | Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine |
EP2853685A1 (de) * | 2013-09-25 | 2015-04-01 | Siemens Aktiengesellschaft | Einsatzelement und Gasturbine |
ITFI20130237A1 (it) * | 2013-10-14 | 2015-04-15 | Nuovo Pignone Srl | "sealing clearance control in turbomachines" |
DE102013017713B4 (de) * | 2013-10-24 | 2022-10-27 | Man Energy Solutions Se | Turbomaschine |
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-
1997
- 1997-12-19 DE DE19756734A patent/DE19756734A1/de not_active Withdrawn
-
1998
- 1998-11-13 DE DE59809709T patent/DE59809709D1/de not_active Expired - Lifetime
- 1998-11-13 EP EP98121690A patent/EP0924388B1/de not_active Expired - Lifetime
- 1998-11-23 US US09/197,668 patent/US6126390A/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US6126390A (en) | 2000-10-03 |
EP0924388A2 (de) | 1999-06-23 |
EP0924388A3 (de) | 2000-08-16 |
DE59809709D1 (de) | 2003-10-30 |
DE19756734A1 (de) | 1999-06-24 |
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