EP1745245B1 - Combustion chamber for a gas turbine - Google Patents
Combustion chamber for a gas turbine Download PDFInfo
- Publication number
- EP1745245B1 EP1745245B1 EP05736060A EP05736060A EP1745245B1 EP 1745245 B1 EP1745245 B1 EP 1745245B1 EP 05736060 A EP05736060 A EP 05736060A EP 05736060 A EP05736060 A EP 05736060A EP 1745245 B1 EP1745245 B1 EP 1745245B1
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- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- brush seal
- bristles
- protective elements
- casing section
- Prior art date
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- 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
- F23R3/002—Wall structures
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the invention relates to a combustion chamber for a gas turbine with a thermal protective lining, and more particularly to a seal for the semi-static area between elements of the thermal protective lining.
- the invention particularly relates to combustors of this type in large gas turbines, such as stationary industrial gas turbines.
- the combustors for gas turbines are typically lined with thermal protection elements that protect the chamber housing from the hot gas of the combustor and are secured thereto along the perimeter of the combustor in the form of juxtaposed segments on supports in the chamber housing.
- the protective lining is cooled by cooling air flowing between the supports and the segments.
- the cooling air is typically conducted in the direction of the combustion chamber axis and then added to the fuel in the region of the combustion chamber inlet.
- Seals are located between the thermal protection elements and the combustion chamber housing at the combustion chamber inlet of the combustion chamber. They prevent cooling air between the protective elements and the housing from entering the combustion chamber and influencing the combustion process (see, eg WO 02/088601-A ).
- the thermal protection elements are exposed to movements of different magnitude and frequency Due to thermal expansion movements of low frequency, also known as so-called "low cycle fatigue movements” occur in the axial and radial directions. They are particularly important in large stationary, industrial gas turbines, since there are the thermal expansions due to the large dimensions of the components in a large proportion to the accuracy with which the gas turbine and combustor are made.
- the thermally induced relative movements represent a challenge in the Seal between the thermal protection elements and in the area around the protective elements. Movements of higher frequency of the thermal protection elements result from vibrations that may occur in general combustion chamber operation. The operation can excite vibrations of different frequencies in the protective elements, which can lead to increased vibration of protective elements and carriers by the natural frequencies of the protective elements. They are also known under so-called "high cycle fatigue movements” and are compared to the thermal movements of smaller size and higher frequency. In particular, they can reduce the reliable operating life of the protective elements.
- the thermal protection elements, their supports and adjacent components are basically static. However, since the spaces between individual protective elements as well as the spaces between the protective elements and adjacent components are exposed to the mentioned, relatively large movements, the protective elements and the seals for the intermediate spaces are to be seen in a semi-static area.
- the magnitude of vibrations can be reduced by attenuating or breaking the amplitudes and frequencies of the vibrations. This is realized for example by deliberately controlling the combustion process or by acoustic damping elements in the combustion chamber which dissipate the energy of the vibrations.
- Out EP 990,851 is a method for acoustic damping of vibrations within combustion chambers by Helmoltz damping known. There is disclosed a combination of Helmholtz resonators with another damping medium, such as a plurality of plates with openings for a cooling flow.
- US 6,357,752 discloses the application of brush seals in the area between the downstream end of a combustor for a gas turbine and the first guide row of the gas turbine. It is a double brush seal with pressure across the first seal and second seal falling in opposite directions.
- the combustion chamber should be designed in particular in the region of protective elements on the housing wall of the combustion chamber at the combustion chamber inlet so that as possible no cooling air for cooling the protective elements enters the combustion chamber, which would disturb the combustion process.
- a combustion chamber for a gas turbine has a Brennkanimergephaseuse and a front housing part.
- a plurality of thermal protection elements over the circumference of the combustion chamber are arranged like a segment, which protect the combustion chamber housing from the radiation of the combustion process.
- a flow of cooling air passes between the thermal protection elements and the combustion chamber housing wall and in the direction from the region of the combustion chamber exit to the region of the combustion chamber inlet, the cooling air finally passing into a space outside the front housing of the combustion chamber.
- a brush seal is arranged between the front housing part of the combustion chamber and the thermal protection elements and extends over the circumference of the front housing part.
- the inventive combustion chamber has a brush seal, which seals the space outside of the front housing part, in which the cooling air flows, from the combustion chamber interior. It provides in particular a uniform over the circumference and over the various operating conditions of the combustion chamber temporally uniform seal. It prevents uncontrolled penetration of cooling air into the combustion chamber and resulting influences on the combustion process.
- the combustion chamber according to the invention thus achieves stable, spatially uniform and reproducible combustion.
- the brush seal ensures even with large, thermally induced relative movements ("low cycle fatigue movement") the components a sealing effect, since it inherently has a large elastic compliance.
- the inventive combustion chamber is particularly advantageous in large, industrial gas turbines, since there the thermal movements are large and especially large compared to the accuracy to which the components of the gas turbine are coordinated.
- the brush seal also provides a reliable seal for high-cycle fatigue movement of components in contact with the seal.
- the vibrations are dissipated or even extinguished, which reduces the vibration. This type of vibration damping is achieved for all vibration frequencies that occur in all operating conditions of the combustion chamber.
- the brush seal is configured in segments which are juxtaposed over the circumference of the combustion chamber, each of the segments of the brush seal being in contact with at least two thermal protection elements.
- the brush seal is mounted in the front housing of the combustion chamber and the bristles extend in the direction of the thermal protection elements. This is advantageous in view of the fact that the vibrations of the front housing are smaller than those of the protective elements. In appropriate situations, it is also feasible to attach the brush seal to the protective elements.
- the brush seal is configured by aligning the bristles at an angle to the radial direction with respect to the combustion chamber longitudinal axis. Specifically, the bristles are angled in the direction of the circumferential tangent. This allows a sealing effect even with varying radial distance between the combustion chamber front housing and thermal protection elements comprising the front housing.
- the Anwinkelung is arbitrary, but is preferably 45 ° ⁇ 5 °.
- brush seals are used, the force-locking and positive locking by pressing in a groove are clamped.
- Such brush seals provide the advantage that they can be installed in a small space and components with a small arbitrary radius of curvature.
- the surface with which the bristles of the brush seal are in contact is provided with a coating for protection against wear.
- This coating for example of Cr 3 C 2 , provides a very smooth surface over which the bristles can slide without digging into the component, whereby the wear of the bristles is greatly reduced. The coating thus causes an increase in the friction damping and ensures a higher sealing effect with longer service life of the bristles.
- the bristles of the brush seal have a bias in the axial direction, which means the direction of the combustion chamber axis.
- a bias provides a good seal in the particular case of a small pressure drop across the seal.
- the pressure drop is small in comparison to Pressure drop in other seals, such as a brush seal on a turbine rotor.
- FIG. 1 shows a combustion chamber 1 for a gas turbine in a section along the longitudinal axis 2 of a burner 3.
- the burner 3 is shown schematically, flows through the fuel in the indicated direction 4.
- the combustion chamber 1 is surrounded by a circularly symmetrical combustion chamber housing 6 which extends in the longitudinal direction from the burner 3 to the combustion chamber outlet 5, to which the first guide row of the gas turbine (not shown) is added.
- the combustion chamber 1 has a front housing 7 with a recess in which the burner 3 is arranged.
- the inner surface of the combustion chamber housing 6, 6 ' is lined with thermal protection elements 8, which are fixed to the housing wall 6, 6', for example by means of carriers (not shown).
- the thermal protection elements are cooled by a cooling air flow 10.
- the cooling air for example, from the compressor for the Gas turbine is removed, is passed through openings 11 in the combustion chamber housing 6, 6 'in the gap 12 between the combustion chamber housing wall 6, 6' and the thermal protection elements 8 and in the axial direction in the counterflow direction of the fuel in a space 13 outside the front housing 7 of the combustion chamber directed. There it is fed through openings 14 in the housing of the burner 3 the fuel stream.
- the front housing 7 of the combustion chamber 1 is fixed by struts 15 on the combustion chamber housing 6, 6 '. It has an opening 16 in which the burner 3 is arranged.
- thermal protection element 8 Between adjacent struts 15 and between each of the front housing 7 and the opposite thermal protection element 8 are areas of possible leakage flow 17 of cooling air into the interior 18 of the combustion chamber. In the area between the front housing 7 and protective elements 8, a seal 19 is arranged. It is preferably fastened in a groove 20 recessed in the front housing 7 and extends up to the surface of the thermal protection element 8.
- the thermal protection elements 8 are fixedly attached at a point, for example in the region of the first turbine guide row, from which the thermal movements in the axial and radial directions originate.
- FIG. 2 shows a detailed view of the region II in FIG. 1, in which a part of the front housing 7 and a part of the opposite thermal protection element 8 and the combustion chamber housing wall 6 are shown. Between the housing wall 6 and the protective element 8, in turn, the cooling air flow 10 is shown, which flows through the gap 12 between the protective element and the housing wall.
- On the front housing 7 is located on the combustion chamber housing side facing a groove 20 having an undercut. In the groove 20, a brush seal 19 is arranged.
- a brush seal is used which has been produced by a press-in process by means of a clamp 21.
- the bristles 22 extend radially in the plane shown (with respect to axis 2) to the protective element.
- FIG 3 shows the upper half of the annular combustion chamber in a section through the front housing 7 according to III-III in Figure 1.
- a plurality of openings 16 for the burners which are arranged along the circumference of the annular combustion chamber.
- the thermal protection elements 8 are attached on the inner wall of the combustion chamber housing 6, both at the outer housing wall 6 and on the inner housing wall 6 'of the ring. They each extend over a segment of the entire circumference. Between the individual protective elements 8 seals are mounted, which prevent hot gas from entering the combustion chamber housing 6.
- the inventive seal 19 extends from the front housing 7 to the protective elements 8, wherein the bristles are aligned at an angle to the radial direction.
- the seal 19 is arranged like a segment. According to the invention, a single sealing segment 19 'is in contact with at least two adjacent thermal protection elements 8.
- the transition from one brush seal element 19 'to the next brush seal element 19' is almost seamless and is preferably approximately at the level of the center of a thermal protection element 8.
- the junctions can be placed anywhere in relation to the protection elements, including at locations between two guarded protective elements.
- Figure 4 shows a further detail according to IV in Figure 3.
- the detail shows the orientation of the bristles of the brush seal 19 with respect to the radial direction of the combustion chamber.
- the bristles are inclined from the radial in the direction of the circumferential tangent at an angle ⁇ in any range, preferably in a range of 40-50 °.
- the brush seal is designed especially for use with small pressure drops.
- the brush seal is designed here in particular with a bias of the bristles in the opposite direction of the leakage current.
- the bias voltage is thereby generated by the clip 24 in the manufacture of the seal is placed over the part of the bristles 25 which is wound around a round rod 26, wherein the ends of the bracket 24 are obliquely at a predetermined angle, and not parallel, to the course of the bristles 25, as shown in Figure 5 by the pressing in the Groove 20 of the front housing part 7, the bristles are straight again as shown in Figure 2 shows the bristles receive a bias.
- the angle is chosen the greater, the greater the desired preload.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
Description
Die Erfindung betrifft eine Brennkammer für eine Gasturbine mit einer thermischen Schutzauskleidung und insbesondere eine Dichtung für den semi-statischen Bereich zwischen Elementen der thermischen Schutzauskleidung. Die Erfindung betrifft insbesondere Brennkammern dieser Art in grossen Gasturbinen, wie zum Beispiel stationären, industriellen Gasturbinen.The invention relates to a combustion chamber for a gas turbine with a thermal protective lining, and more particularly to a seal for the semi-static area between elements of the thermal protective lining. The invention particularly relates to combustors of this type in large gas turbines, such as stationary industrial gas turbines.
Die Brennkammern für Gasturbinen sind typischerweise mit thermischen Schutzelementen ausgekleidet, die das Kammergehäuse vom Heissgas der Brennkammer schützen und hierzu entlang dem Umfang der Brennkammer in der Form von aneinandergereihten Segmenten an Trägem im Kammergehäuse befestigt sind. Die Schutzauskleidung wird durch Kühlluft, die zwischen den Trägem und den Segmenten strömt, gekühlt. Die Kühlluft wird typischerweise in Richtung der Brennkammerachse geleitet und danach im Bereich des Brennkammereintritts dem Brennstoff zugefügt. Zwischen den thermischen Schutzelementen und dem Brennkammergehäuse am Brennkammereintritt der Brennkammer sind Dichtungen angeordnet Sie verhindern, dass Kühlluft zwischen Schutzelementen und Gehäuse in die Brennkammer gelangt und den Verbrennungsprozess beeinflusst (siehe z.B.
Die thermischen Schutzelemente sind Bewegungen von verschiedenem Ausmass und verschiedener Frequenz ausgesetzt
Durch thermische Ausdehnungen bedingte Bewegungen niederer Frequenz, auch unter sogenannter "low cycle fatigue movements" bekannt, treten in axialer sowie radialer Richtung auf. Sie sind insbesondere bei grossen stationären, industriellen Gasturbinen bedeutend, da dort die thermischen Ausdehnungen aufgrund der grossen Dimensionen der Bauteile in einem grossen Verhältnis zur Genauigkeit stehen, mit der die Gasturbine und Brennkammer hergestellt werden. Die thermisch bedingten Relativbewegungen bedeuten eine Herausforderung bei der Dichtung zwischen den thermischen Schutzelementen sowie im Bereich um die Schutzelemente.
Bewegungen höherer Frequenz der thermischen Schutzelemente ergeben sich durch Vibrationen, die beim allgemeinen Brennkammerbetrieb auftreten können. Der Betrieb kann bei den Schutzelementen Vibrationen verschiedener Frequenzen anregen, welche durch die Eigenfrequenzen der Schutzelemente zu vergrösserten Vibrationen von Schutzelementen und Trägem fuhren können. Sie sind auch unter sogenannten "high cycle fatigue movements" bekannt und sind im Vergleich zu den thermisch bedingten Bewegungen von kleinerem Ausmass und von höherer Frequenz. Sie können insbesondere die zuverlässige Betriebsdauer der Schutzelemente reduzieren.The thermal protection elements are exposed to movements of different magnitude and frequency
Due to thermal expansion movements of low frequency, also known as so-called "low cycle fatigue movements" occur in the axial and radial directions. They are particularly important in large stationary, industrial gas turbines, since there are the thermal expansions due to the large dimensions of the components in a large proportion to the accuracy with which the gas turbine and combustor are made. The thermally induced relative movements represent a challenge in the Seal between the thermal protection elements and in the area around the protective elements.
Movements of higher frequency of the thermal protection elements result from vibrations that may occur in general combustion chamber operation. The operation can excite vibrations of different frequencies in the protective elements, which can lead to increased vibration of protective elements and carriers by the natural frequencies of the protective elements. They are also known under so-called "high cycle fatigue movements" and are compared to the thermal movements of smaller size and higher frequency. In particular, they can reduce the reliable operating life of the protective elements.
Die thermischen Schutzelemente, ihre Träger sowie benachbarte Bauteile sind grundsätzlich statisch. Da die Zwischenräume zwischen einzelnen Schutzelementen sowie die Räume zwischen den Schutzelementen und benachbarten Bauteilen jedoch den erwähnten, relativ grossen Bewegungen ausgesetzt sind, sind die Schutzelemente und die Dichtungen für die Zwischenräume in einem semi-statischen Bereich zu sehen.The thermal protection elements, their supports and adjacent components are basically static. However, since the spaces between individual protective elements as well as the spaces between the protective elements and adjacent components are exposed to the mentioned, relatively large movements, the protective elements and the seals for the intermediate spaces are to be seen in a semi-static area.
Es sind verschiedene Massnahmen zur Dämpfung von Vibrationen in einer Brennkammer bekannt. Zum Beispiel können die Ausmasse von Vibrationen reduziert werden, indem die Amplituden und Frequenzen der Vibrationen gedämpft oder gebrochen werden. Dies wird zum Beispiel durch bewusste Steuerung des Verbrennungsprozesses realisiert oder durch akustische Dämpfungselemente in der Brennkammer, welche die Energie der Schwingungen dissipieren.Various measures are known for damping vibrations in a combustion chamber. For example, the magnitude of vibrations can be reduced by attenuating or breaking the amplitudes and frequencies of the vibrations. This is realized for example by deliberately controlling the combustion process or by acoustic damping elements in the combustion chamber which dissipate the energy of the vibrations.
Aus
Es ist der Erfindung die Aufgabe gestellt, eine Brennkammer für eine Gasturbine bereit zu stellen, insbesondere für grosse, stationäre, industrielle Gasturbinen. Die Brennkammer soll insbesondere im Bereich von Schutzelementen an der Gehäusewand der Brennkammer am Brennkammereintritt so ausgestaltet sein, dass möglichst keine Kühlluft zur Kühlung der Schutzelemente in die Brennkammer gelangt, welche den Verbrennungsprozess stören würde. Dies soll insbesondere in dem Fall gewährt sein, dass die grundsätzlich statischen Schutzelemente in einem semi-statischen Bereich sind, indem sie grossen thermischen Bewegungen sowie Vibrationen ausgesetzt sind und die Grösse der Abstände zwischen den Schutzelementen und dem Frontgehäuse entsprechend grossen Schwankungen ausgesetzt sind.It is the object of the invention to provide a combustion chamber for a gas turbine, especially for large, stationary, industrial gas turbines. The combustion chamber should be designed in particular in the region of protective elements on the housing wall of the combustion chamber at the combustion chamber inlet so that as possible no cooling air for cooling the protective elements enters the combustion chamber, which would disturb the combustion process. This should be granted in particular in the case that the basically static protection elements are in a semi-static area by being exposed to large thermal movements and vibrations and the size of the distances between the protective elements and the front housing are exposed to correspondingly large fluctuations.
Diese Aufgabe ist durch eine Brennkammer gemäss Anspruch 1 gelöst.
Eine Brennkammer für eine Gasturbine weist ein Brennkanimergehäuse und ein Frontgehäuseteil auf. Am inneren Umfang der Wand des Brennkammergehäuses sind mehrere thermische Schutzelemente über den Umfang der Brennkammer segmentartig angeordnet, welche das Brennkammergehäuse vor der Strahlung des Verbrennungsprozesses schützen. Zur Kühlung der Schutzelemente führt ein Kühlluftstrom zwischen den thermischen Schutzelementen und der Brennkammergehäusewand hindurch und in der Richtung vom Bereich des Brennkammeraustritts zum Bereich des Brennkammereintritts, wobei die Kühlluft schliesslich in einen Raum ausserhalb des Frontgehäuses der Brennkammer gelangt. Erfindungsgemäss ist zwischen dem Frontgehäuseteil der Brennkammer und den thermischen Schutzelementen eine Bürstendichtung angeordnet, die sich über den Umfang des Frontgehäuseteils erstreckt.This object is achieved by a combustion chamber according to
A combustion chamber for a gas turbine has a Brennkanimergehäuse and a front housing part. At the inner circumference of the wall of the combustion chamber housing a plurality of thermal protection elements over the circumference of the combustion chamber are arranged like a segment, which protect the combustion chamber housing from the radiation of the combustion process. To cool the protective elements, a flow of cooling air passes between the thermal protection elements and the combustion chamber housing wall and in the direction from the region of the combustion chamber exit to the region of the combustion chamber inlet, the cooling air finally passing into a space outside the front housing of the combustion chamber. According to the invention, a brush seal is arranged between the front housing part of the combustion chamber and the thermal protection elements and extends over the circumference of the front housing part.
Die erfindungsgemässe Brennkammer verfügt über eine Bürstendichtung, die den Raum ausserhalb des Frontgehäuseteils, in den die Kühlluft fliesst, vom Brennkammer-Innenraum abdichtet. Sie gewährt insbesondere eine über den Umfang gleichmässige und über die verschiedenen Betriebszustände der Brennkammer zeitlich gleichmässige Dichtung. Sie verhindert ein unkontrolliertes Eindringen von Kühlluft in die Brennkammer hinein und daraus entstehende Einflüsse auf den Verbrennungsprozess. Durch die erfindungsgemässe Brennkammer wird damit eine zeitlich stabile sowie räumlich gleichmässige und reproduzierbare Verbrennung erzielt. Dabei gewährt die Bürstendichtung auch bei grossen, thermisch bedingten Relativbewegungen ("low cycle fatigue movement") der Bauteile eine Dichtungswirkung, da sie inherent über eine grosse elastische Nachgiebigkeit verfügt. Selbst bei thermischen Bewegungen von der Art, bei denen ein Schutzelement sich in entegegengesetzte Richtung krümmt, also statt in angestammter Krümmung gemäss der Form der Brennkammergehäusewand in entegegengesetzter Richtung nach innen krümmt, vermag diese Dichtung eine Kühlluftleckage zu verhindern.
Die erfindungsgemässe Brennkammer ist insbesondere bei grossen, industriellen Gasturbinen vorteilhaft, da dort die thermischen Bewegungen gross und insbesondere im Vergleich zur Genauigkeit gross sind, zu der die Bauteile der Gasturbine aufeinander abgestimmt sind.The inventive combustion chamber has a brush seal, which seals the space outside of the front housing part, in which the cooling air flows, from the combustion chamber interior. It provides in particular a uniform over the circumference and over the various operating conditions of the combustion chamber temporally uniform seal. It prevents uncontrolled penetration of cooling air into the combustion chamber and resulting influences on the combustion process. The combustion chamber according to the invention thus achieves stable, spatially uniform and reproducible combustion. The brush seal ensures even with large, thermally induced relative movements ("low cycle fatigue movement") the components a sealing effect, since it inherently has a large elastic compliance. Even with thermal movements of the kind in which a protective element curves in the opposite direction, ie, curves inwardly in the opposite direction from the original curvature according to the shape of the combustion chamber housing wall, this seal can prevent cooling air leakage.
The inventive combustion chamber is particularly advantageous in large, industrial gas turbines, since there the thermal movements are large and especially large compared to the accuracy to which the components of the gas turbine are coordinated.
Die Bürstendichtung gewährt auch bei hochfrequenten Schwingungen ("high cycle fatigue movement") der mit der Dichtung in Berührung stehenden Bauteile eine zuverlässige Dichtung.The brush seal also provides a reliable seal for high-cycle fatigue movement of components in contact with the seal.
Bei hoch- und niederfrequenten Schwingungen der thermischen Schutzelemente bewirkt die Bürstendichtung, zusätzlich zu ihrer Dichtungsfunktion, eine Dämpfung der hoch- und niederfrequenten Schwingungen. Zum einen ergibt sich dies durch Reibungsdämpfung durch relative Gleitbewegungen des Brennkammergehäuses und den Schutzelementen. Zum anderen ergibt es sich durch Verformung oder Biegung der Borsten aufgrund der Druckkraft, die bei thermischen Bewegungen auf die Borsten ausgeübt wird. Es ergibt sich dabei eine Art Federwirkung. Die Dämpfung der Schwingung kann sich auch durch eine Kombination von Reibungsdämpfung und Verformung der Borsten ergeben.In high and low frequency vibrations of the thermal protection elements causes the brush seal, in addition to its sealing function, a damping of high and low frequency vibrations. On the one hand this results from friction damping by relative sliding movements of the combustion chamber housing and the protective elements. On the other hand, it results from deformation or bending of the bristles due to the compressive force exerted on the bristles during thermal movements. This results in a kind of spring action. The damping of the vibration can also result from a combination of friction damping and deformation of the bristles.
Die Schwingungen werden dabei dissipiert oder gar ausgelöscht, wodurch die Schwingung reduziert wird. Diese Art Schwingungsdämpfung wird für alle Schwingungsfrequenzen erzielt, welche in sämtlichen Betriebszuständen der Brennkammer auftreten. Durch die Dämpfung der Schwingungen der Schutzelemente wird einerseits die Dichtung weiter verbessert und anderseits die Betriebseinsatzdauer der Schutzelemente verlängert.The vibrations are dissipated or even extinguished, which reduces the vibration. This type of vibration damping is achieved for all vibration frequencies that occur in all operating conditions of the combustion chamber. By damping the vibrations of the protective elements, on the one hand, the seal is further improved and, on the other hand, the service life of the protective elements is extended.
Besondere Ausführungsbeispiele werden in den Unteransprüchen offenbart.Particular embodiments are disclosed in the subclaims.
In einer ersten Ausführung der Erfindung ist die Bürstendichtung in Segmenten ausgestaltet, die über den Umfang der Brennkammer aneinander gereiht sind, wobei jedes der Segmente der Bürstendichtung jeweils mit mindestens zwei thermischen Schutzelementen in Berührung steht.In a first embodiment of the invention, the brush seal is configured in segments which are juxtaposed over the circumference of the combustion chamber, each of the segments of the brush seal being in contact with at least two thermal protection elements.
In einer zweiten Ausführung der Erfindung ist die Bürstendichtung in dem Frontgehäuse der Brennkammer befestigt und die Borsten erstrecken sich in Richtung der thermischen Schutzelemente. Dies ist vorteilhaft in Anbetracht dessen, dass die Schwingungen des Frontgehäuses kleiner sind als jene der Schutzelemente. In entsprechenden Situationen ist es auch realisierbar, die Bürstendichtung an den Schutzelementen zu befestigen.In a second embodiment of the invention, the brush seal is mounted in the front housing of the combustion chamber and the bristles extend in the direction of the thermal protection elements. This is advantageous in view of the fact that the vibrations of the front housing are smaller than those of the protective elements. In appropriate situations, it is also feasible to attach the brush seal to the protective elements.
In einer weiteren Ausführung der Erfindung ist die Bürstendichtung so ausgestaltet, indem die Borsten in einem Winkel zur radialen Richtung bezüglich der Brennkammerlängsachse ausgerichtet sind. Genauer sind die Borsten in Richtung der Umfangstangente angewinkelt. Dies erlaubt eine Dichtwirkung auch bei sich veränderndem radialen Abstand zwischen dem Brennkammerfrontgehäuse und thermischen Schutzelementen, welche das Frontgehäuse umfassen. Die Anwinkelung ist beliebig, beträgt jedoch vorzugsweise 45° ± 5°.In a further embodiment of the invention, the brush seal is configured by aligning the bristles at an angle to the radial direction with respect to the combustion chamber longitudinal axis. Specifically, the bristles are angled in the direction of the circumferential tangent. This allows a sealing effect even with varying radial distance between the combustion chamber front housing and thermal protection elements comprising the front housing. The Anwinkelung is arbitrary, but is preferably 45 ° ± 5 °.
In einer bevorzugten Ausführung der Erfindung werden Bürstendichtungen verwendet, die durch Einpressung kraft- und formschlüssig in einer Nut klemmend befestigt sind. Solche Bürstendichtungen gewähren den Vorteil, dass sie auf kleinem Raum und bei Bauteilen mit kleinem beliebigem Krümmungsradius eingebaut werden können.In a preferred embodiment of the invention brush seals are used, the force-locking and positive locking by pressing in a groove are clamped. Such brush seals provide the advantage that they can be installed in a small space and components with a small arbitrary radius of curvature.
In einer weiteren Variante, ist die Oberfläche, mit der die Borsten der Bürstendichtung in Berührung stehen, mit einer Beschichtung zum Schutz gegen Verschleiss versehen. Diese Beschichtung, beispielsweise aus Cr3C2, gewährt eine äusserst glatte Oberfläche, über welche die Borsten gleiten können ohne sich in das Bauteil einzugraben, wodurch der Verschleiss der Borsten stark vermindert ist. Die Beschichtung bewirkt damit eine Erhöhung der Reibungsdämpfung und gewährleistet eine höhere Dichtwirkung bei längerer Betriebslebensdauer der Borsten.In a further variant, the surface with which the bristles of the brush seal are in contact is provided with a coating for protection against wear. This coating, for example of Cr 3 C 2 , provides a very smooth surface over which the bristles can slide without digging into the component, whereby the wear of the bristles is greatly reduced. The coating thus causes an increase in the friction damping and ensures a higher sealing effect with longer service life of the bristles.
In einer weiteren Ausführung der Erfindung besitzen die Borsten der Bürstendichtung eine Vorspannung in axialer Richtung, wobei hier die Richtung der Brennkammerachse gemeint ist Eine Vorspannung gewährt eine gute Dichtung im besonderen Fall eines kleinen Druckabfalls über der Dichtung. Bei der erfindungsgemässen Brennkammer ist der Druckabfall klein im Vergleich zum Druckabfall bei anderen Dichtungen, wie zum Beispiel bei einer Bürstendichtung an einem Turbinenrotor.In a further embodiment of the invention, the bristles of the brush seal have a bias in the axial direction, which means the direction of the combustion chamber axis. A bias provides a good seal in the particular case of a small pressure drop across the seal. In the combustion chamber according to the invention, the pressure drop is small in comparison to Pressure drop in other seals, such as a brush seal on a turbine rotor.
- Figur 1 zeigt einen Schnitt durch ein Segment einer ringförmigen Brennkammer für eine Gasturbine und insbesondere die Anordnung des Kammergehäuses, des Frontgehäuseteils und der thermischen Schutzelemente.Figure 1 shows a section through a segment of an annular combustion chamber for a gas turbine and in particular the arrangement of the chamber housing, the front housing part and the thermal protection elements.
- Figur 2 zeigt das Detail II gemäss Figur 1 und insbesondere die erfindungsgemässe Dichtung zwischen Frontgehäuse und thermischem Schutzelement gegen einen Leckagestrom in die Brennkammer.Figure 2 shows the detail II according to Figure 1 and in particular the inventive seal between the front housing and thermal protection element against a leakage current into the combustion chamber.
- Figur 3 zeigt den in Figur 1 mit III-III bezeichneten Querschnitt und insbesondere die segmentartige Anordnung der thermischen Schutzelemente und der Bürstendichtung.FIG. 3 shows the cross-section designated III-III in FIG. 1 and in particular the segment-like arrangement of the thermal protection elements and of the brush seal.
- Figur 4 zeigt die Bürstendichtung gemäss Detail IV aus Figur 3 und insbesondere ihre Anordnung entlang dem Umfang der ringförmigen Brennkammer.Figure 4 shows the brush seal according to detail IV of Figure 3 and in particular their arrangement along the circumference of the annular combustion chamber.
- Figur 5 zeigt eine Bürstendichtung zum Einpressen mit axialer Vorspannung zur Anwendung in der erfindungsgemässen Brennkammer.Figure 5 shows a brush seal for pressing with axial bias for use in the inventive combustion chamber.
In Figur 1 ist eine Brennkammer 1 für eine Gasturbine im Schnitt entlang der Längsachse 2 eines Brenners 3 gezeigt. Am Brennkammereintritt ist schematisch der Brenner 3 dargestellt, durch den Brennstoff in angezeigter Richtung 4 strömt. Die Brennkammer 1 ist von einem zirkularsymmetrischen Brennkammergehäuse 6 umgeben, welches sich in Längsrichtung vom Brenner 3 bis zum Brennkammeraustritt 5 erstreckt, an dem die erste Leitreihe der Gasturbine (nicht dargestellt) angefügt ist. Die Brennkammer 1 weist ein Frontgehäuse 7 mit einer Aussparung, in welcher der Brenner 3 angeordnet ist. Die innere Oberfläche des Brennkammergehäuses 6, 6' ist mit thermischen Schutzelementen 8 ausgekleidet, welche an der Gehäusewand 6, 6' beispielsweise mittels Trägem (nicht dargestellt) befestigt sind. Um den Temperaturen des Heissgases innerhalb der Brennkammer standzuhalten, sind die thermischen Schutzelemente durch einen Kühlluftstrom 10 gekühlt. Die Kühlluft, die beispielsweise vom Kompressor für die Gasturbine entnommen wird, wird durch Öffnungen 11 im Brennkammergehäuse 6, 6' in den Zwischenraum 12 zwischen der Brennkammergehäusewand 6, 6' und den thermischen Schutzelementen 8 geleitet und in axialer Richtung in der Gegenstromrichtung des Brennstoffes in einen Raum 13 ausserhalb des Frontgehäuses 7 der Brennkammer geleitet. Dort wird sie durch Öffnungen 14 im Gehäuse des Brenners 3 dem Brennstoffstrom zugeführt.
Das Frontgehäuse 7 der Brennkammer 1 ist durch Streben 15 am Brennkammergehäuse 6, 6' befestigt. Es weist eine Öffnung 16 auf, in welcher der Brenner 3 angeordnet ist. Zwischen benachbarten Streben 15 und jeweils zwischen dem Frontgehäuse 7 und dem gegenüberliegenden thermischen Schutzelement 8 befinden sich Bereiche eines möglichen Leckagestroms 17 von Kühlluft in den Innenraum 18 der Brennkammer.
Im Bereich zwischen Frontgehäuse 7 und Schutzelementen 8 ist eine Dichtung 19 angeordnet. Sie ist vorzugsweise in einer im Frontgehäuse 7 eingelassenen Nut 20 befestigt und erstreckt sich bis zur Oberfläche des thermischen Schutzelements 8.
Die thermischen Schutzelemente 8 sind an einem Punkt fix befestigt, beispielsweise im Bereich der ersten Turbinenleitreihe, von dem die thermischen Bewegungen in axialer und radialer Richtung ausgehen.FIG. 1 shows a
The
In the area between the
The
Figur 2 zeigt eine Detailansicht des Bereichs II in Figur 1, in der ein Teil des Frontgehäuses 7 und ein Teil des gegenüber angeordneten thermischen Schutzelements 8 und der Brennkammergehäusewand 6 gezeigt sind. Zwischen der Gehäusewand 6 und dem Schutzelement 8 ist wiederum der Kühlluftstrom 10 dargestellt, der durch den Zwischenraum 12 zwischen Schutzelement und Gehäusewand fliesst Am Frontgehäuse 7 befindet sich an der dem Brennkammergehäuse zugewandten Seite eine Nut 20, die eine Hinterschneidung aufweist. In der Nut 20 ist eine Bürstendichtung 19 angeordnet. Vorzugsweise wird eine Bürstendichtung verwendet, die durch ein Einpressverfahren mittels einer Klammer 21 hergestellt worden ist Die Borsten 22 erstrecken sich in der gezeigten Ebene radial (bezüglich Achse 2) zum Schutzelement.FIG. 2 shows a detailed view of the region II in FIG. 1, in which a part of the
Figur 3 zeigt die die obere Hälfte der ringförmigen Brennkammer in einem Schnitt durch das Frontgehäuse 7 gemäss III-III in Figur 1. Es sind mehrere Öffnungen 16 für die Brenner gezeigt, die entlang dem Umfang der ringförmigen Brennkammer angeordnet sind. Die Streben 15 entlang dem Umfang des Frontgehäuses 7, durch die es am Brennkammergehäuse 6, 6' befestigt ist, sind gestrichelt angedeutet. An der Innenwand des Brennkammergehäuses 6, sowohl an der äusseren Gehäusewand 6 als auch an der inneren Gehäusewand 6' des Ringes, sind die thermischen Schutzelemente 8 befestigt. Sie erstrecken sich jeweils über ein Segment des gesamten Umfangs. Zwischen den einzelnen Schutzelementen 8 sind Dichtungen angebracht, welche verhindern, dass Heissgas in das Brennkammergehäuse 6 gelangt. Zwischen Brennkammergehäusewand 6 und Schutzelementen 8 befindet sich ein Hohlraum 12, durch den der Kühlluftstrom fliesst. Die erfindungsgemässe Dichtung 19 erstreckt sich vom Frontgehäuse 7 zu den Schutzelementen 8, wobei die Borsten in einem Winkel zur Radialen Richtung ausgerichtet sind. Die Dichtung 19 ist segmentartig angeordnet. Ein einzelnes Dichtungssegment 19' steht dabei erfindungsgemäss mit mindestens zwei benachbarten thermischen Schutzelementen 8 in Berührung. Der Übergang von einem Bürstendichtungselement 19' zum nächsten Bürstendichtungselement 19' ist dabei nahezu nahtlos und befindet sich vorzugsweise ungefähr auf Höhe der Mitte eines thermischen Schutzelementes 8. Grundsätzlich können die Übergänge an beliebiger Stelle in bezug auf die Schutzelemente platziert sein, inklusive an Stellen zwischen zwei benachten Schutzelementen.Figure 3 shows the upper half of the annular combustion chamber in a section through the
Figur 4 zeigt ein weiteres Detail gemäss IV in Figur 3. Das Detail zeigt die Ausrichtung der Borsten der Bürstendichtung 19 bezüglich der radialen Richtung der Brennkammer. Die Borsten sind von der Radialen aus in Richtung der Umfangstangente um einen Winkel α in beliebigem Bereich geneigt, vorzugsweise in einem Bereich von 40-50°.Figure 4 shows a further detail according to IV in Figure 3. The detail shows the orientation of the bristles of the
Eine Neigung der Borsten weg von der Radialen und zur Umfangstangente hin bewirkt, dass selbst bei grossen Schwankungen des Abstands zwischen dem Frontgehäuseumfang 7 und dem thermischen Schutzelement 8 die Schnittstelle zuverlässig und über den Umfang gleichmässig abgedichtet ist. Kühlluft gelangt dadurch während allen Betriebszuständen der Gasturbine und des Brenners nicht in das Innere der Brennkammer. Allenfalls gelangt etwas Kühlluft in die Brennkammer hinein, wobei dies jedoch gleichmässig über den Umfang des Frontgehäuses geschieht, was dennoch einen kontrollierten Betrieb der Brennkammer gewährleistet.An inclination of the bristles away from the radial and the peripheral tangent causes even with large variations in the distance between the
In einer weiteren Ausführung der Brennkammer gemäss der Erfindung ist die Bürstendichtung speziell für die Anwendung bei kleinen Druckabfällen ausgestaltet. Die Bürstendichtung ist hier insbesondere mit einer Vorspannung der Borsten in der Gegenrichtung des Leckagestroms ausgestaltet. Die Vorspannung wird dadurch erzeugt, indem bei der Herstellung der Dichtung die Klammer 24 über den Teil der Borsten 25 gelegt wird, der um einen Rundstab 26 gewunden ist, wobei die Enden der Klammer 24 schräg in einem vorbestimmten Winkel, und nicht parallel, zum Verlauf der Borsten 25 stehen, wie in Figur 5 gezeigt Durch das Einpressen in die Nut 20 des Frontgehäuseteils 7 werden die Borsten wieder gerade gestellt wie in Figur 2 dargestellt Dabei erhalten die Borsten eine Vorspannung. Der Winkel wird um so grösser gewählt, je grösser die gewünschte Vorspannung ist.In a further embodiment of the combustion chamber according to the invention, the brush seal is designed especially for use with small pressure drops. The brush seal is designed here in particular with a bias of the bristles in the opposite direction of the leakage current. The bias voltage is thereby generated by the
- 11
- Brennkammercombustion chamber
- 22
- Längsachse eines BrennersLongitudinal axis of a burner
- 33
- Brennerburner
- 44
- Strömungsrichtung des BrennstoffsFlow direction of the fuel
- 55
- Brennkammeraustrittcombustor exit
- 66
- Gehäusewand der BrennkammerHousing wall of the combustion chamber
- 77
- Frontgehäuse der BrennkammerFront housing of the combustion chamber
- 88th
- Thermisches SchutzelementThermal protection element
- 99
- 1010
- KühlluftstromCooling air flow
- 1111
- Öffnung durch Gehäusewand für KühllufteintrittOpening through housing wall for cooling air inlet
- 1212
- Zwischenraumgap
- 1313
- Raum ausserhalb FrontgehäuseSpace outside front housing
- 1414
- Öffnungen für KühlluftstromOpenings for cooling air flow
- 1515
- Strebestrut
- 1616
- Öffnung in Frontgehäuse für BrennerOpening in front housing for burner
- 1717
- Leckagestromleakage current
- 1818
- Innenraum BrennkammerInterior combustion chamber
- 1919
- Dichtungpoetry
- 2020
- Nutgroove
- 2121
- Klammerclip
- 22,2522.25
- Borstenbristles
- 2424
- Klammerclip
- 2626
- Rundstabround bar
- RR
- radiale Richtung von Längsachse der Brennkammer ausgehendRadial direction starting from the longitudinal axis of the combustion chamber
- αα
- Winkel zwischen Radiale und Richtung der Borsten zu Umfangsrichtung hinAngle between the radial and the direction of the bristles towards the circumferential direction
Claims (11)
- Combustion chamber (1) for a gas turbine, wherein the combustion chamber (1) has a casing (6) and a front casing section (7), and thermal protective elements (8) are installed in segments (8') along the inner circumference of the casing (6),
characterized in that
a brush seal (19) is installed between the front casing section (7) and the thermal protective elements (8), which extends along the circumference of the front casing section (7). - Combustion chamber (1) according to Claim 1,
characterized in that
the brush seal is designed in segments (19'), and each segment (19') of the brush seal is in contact with at least two segments (8') of the thermal protective elements (8). - Combustion chamber (1) according to Claim 1,
characterized in that
the brush seal (19) is fastened on the front casing section (7), and the bristles of the brush seal (19) extend from the front casing section (7) to the thermal protective elements (8). - Combustion chamber (1) according to Claim 1,
characterized in that
the bristles (22) of the brush seal (19) extend at an angle (α) to a radial (R) of the combustion chamber and to the circumferential tangent of the combustion chamber. - Combustion chamber (1) according to Claim 4,
characterized in that
the angle (α) to the radial (R) lies within a range of 40 - 50°. - Combustion chamber (1) according to one of the preceding claims,
characterized in that
a slot (20) is located along the circumference of the front casing section (7), and for the brush seal (19) a brush seal is used which by pressing in is fastenable in a frictional and positive locking manner in the slot (20) with clamping effect. - Combustion chamber (1) according to one of the preceding claims,
characterized in that
the surface with which the ends of the bristles (22) of the brush seal (19) are in contact has a coating. - Combustion chamber (1) according to Claim 7,
characterized in that
the coating is a wear-resistant coating. - Combustion chamber (1) according to Claim 1,
characterized in that
the bristles (22) of the brush seal (19) are pretensioned. - Combustion chamber (1) according to Claim 9,
characterized in that
for the brush seal (19), a brush seal is used which is fastened on the front casing section by means of pressing in. - Use of the combustion chamber according to one of the preceding claims in an industrial, stationary gas turbine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH7982004 | 2004-05-05 | ||
| PCT/EP2005/051807 WO2005108869A1 (en) | 2004-05-05 | 2005-04-22 | Combustion chamber for a gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1745245A1 EP1745245A1 (en) | 2007-01-24 |
| EP1745245B1 true EP1745245B1 (en) | 2007-10-03 |
Family
ID=34965312
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP05736060A Not-in-force EP1745245B1 (en) | 2004-05-05 | 2005-04-22 | Combustion chamber for a gas turbine |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US7752846B2 (en) |
| EP (1) | EP1745245B1 (en) |
| CN (1) | CN100510539C (en) |
| AT (1) | ATE374908T1 (en) |
| DE (1) | DE502005001634D1 (en) |
| ES (1) | ES2296165T3 (en) |
| WO (1) | WO2005108869A1 (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2128524A1 (en) * | 2008-05-26 | 2009-12-02 | Siemens Aktiengesellschaft | Component assembly, combustion chamber assembly and gas turbine |
| US9416970B2 (en) * | 2009-11-30 | 2016-08-16 | United Technologies Corporation | Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel |
| GB201119526D0 (en) * | 2011-11-14 | 2011-12-21 | Rolls Royce Plc | Leaf seal |
| FR2998039B1 (en) * | 2012-11-09 | 2014-11-14 | Snecma | COMBUSTION CHAMBER FOR A TURBOMACHINE |
| US9771818B2 (en) | 2012-12-29 | 2017-09-26 | United Technologies Corporation | Seals for a circumferential stop ring in a turbine exhaust case |
| DE102014204466A1 (en) * | 2014-03-11 | 2015-10-01 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber of a gas turbine |
| US20180180289A1 (en) * | 2016-12-23 | 2018-06-28 | General Electric Company | Turbine engine assembly including a rotating detonation combustor |
| FR3061761B1 (en) * | 2017-01-10 | 2021-01-01 | Safran Aircraft Engines | TURBOMACHINE COMBUSTION CHAMBER |
| US11421877B2 (en) * | 2017-08-29 | 2022-08-23 | General Electric Company | Vibration control for a gas turbine engine |
| JP7289752B2 (en) * | 2019-08-01 | 2023-06-12 | 三菱重工業株式会社 | Acoustic dampener, canister assembly, combustor, gas turbine and method of manufacturing canister assembly |
| DE102020203017A1 (en) * | 2020-03-10 | 2021-09-16 | Siemens Aktiengesellschaft | Combustion chamber with ceramic heat shield and seal |
| CN112460630A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Sealing assembly between gap planes of high-temperature zone of gas turbine |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5400586A (en) * | 1992-07-28 | 1995-03-28 | General Electric Co. | Self-accommodating brush seal for gas turbine combustor |
| US5323604A (en) * | 1992-11-16 | 1994-06-28 | General Electric Company | Triple annular combustor for gas turbine engine |
| WO1998016764A1 (en) * | 1996-10-16 | 1998-04-23 | Siemens Westinghouse Power Corporation | Brush seal for gas turbine combustor-transition interface |
| US6186508B1 (en) * | 1996-11-27 | 2001-02-13 | United Technologies Corporation | Wear resistant coating for brush seal applications |
| DE19712088C2 (en) * | 1997-03-22 | 1999-06-24 | Mtu Muenchen Gmbh | Brush seal with bristles inclined in the circumferential direction |
| GB2328011A (en) * | 1997-08-05 | 1999-02-10 | Europ Gas Turbines Ltd | Combustor for gas or liquid fuelled turbine |
| DE69922567T2 (en) * | 1998-04-01 | 2005-12-08 | Mitsubishi Heavy Industries, Ltd. | Sealing arrangement for a gas turbine |
| EP0990851B1 (en) | 1998-09-30 | 2003-07-23 | ALSTOM (Switzerland) Ltd | Gas turbine combustor |
| US6357752B1 (en) | 1999-10-15 | 2002-03-19 | General Electric Company | Brush seal |
| GB2361304A (en) * | 2000-04-14 | 2001-10-17 | Rolls Royce Plc | Combustor wall tile |
| WO2002088601A1 (en) * | 2001-04-27 | 2002-11-07 | Siemens Aktiengesellschaft | Combustion chamber, in particular of a gas turbine |
| JP2003194338A (en) * | 2001-12-14 | 2003-07-09 | R Jan Mowill | Method for controlling gas turbine engine fuel-air premixer with variable geometry exit and for controlling exit velocity |
-
2005
- 2005-04-22 EP EP05736060A patent/EP1745245B1/en not_active Not-in-force
- 2005-04-22 WO PCT/EP2005/051807 patent/WO2005108869A1/en active IP Right Grant
- 2005-04-22 CN CNB2005800226308A patent/CN100510539C/en not_active Expired - Fee Related
- 2005-04-22 DE DE502005001634T patent/DE502005001634D1/en active Active
- 2005-04-22 ES ES05736060T patent/ES2296165T3/en active Active
- 2005-04-22 AT AT05736060T patent/ATE374908T1/en not_active IP Right Cessation
-
2006
- 2006-11-03 US US11/592,277 patent/US7752846B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| DE502005001634D1 (en) | 2007-11-15 |
| WO2005108869A1 (en) | 2005-11-17 |
| CN1981159A (en) | 2007-06-13 |
| CN100510539C (en) | 2009-07-08 |
| EP1745245A1 (en) | 2007-01-24 |
| ES2296165T3 (en) | 2008-04-16 |
| US20080230997A1 (en) | 2008-09-25 |
| ATE374908T1 (en) | 2007-10-15 |
| US7752846B2 (en) | 2010-07-13 |
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