EP0528138B1 - Blade shroud for axial turbine - Google Patents
Blade shroud for axial turbine Download PDFInfo
- Publication number
- EP0528138B1 EP0528138B1 EP92110494A EP92110494A EP0528138B1 EP 0528138 B1 EP0528138 B1 EP 0528138B1 EP 92110494 A EP92110494 A EP 92110494A EP 92110494 A EP92110494 A EP 92110494A EP 0528138 B1 EP0528138 B1 EP 0528138B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- casing
- gap
- shroud
- throttle
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
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- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- the invention relates to a device for sealing the gap between the rotor blades and the housing of a turbomachine which is designed with a conical contour, the rotor blades being provided with circumferential cover plates which seal against the housing with prongs to form radial gaps.
- Such devices are known. They essentially consist of cover plates with tines running in the circumferential direction, which seal against the housing or against a honeycomb arrangement (honeycomb). Such an arrangement is known, for example, from FR-A-2 406 074, but the housing therein is cylindrical. They form a smooth or a stepped labyrinth with pure radial gaps. As a rule, these cover plates extend over the entire blade width.
- a known seal is shown in FIG. 1 to be described later on the basis of the rotor blade of the second stage. With the mechanically and / or thermally highly loaded blades of the last stage, for example a gas turbine, such a solution with conventional materials is no longer possible.
- a damper device which can be a damper wire, for example, is absolutely necessary for free-standing, long blades with a low natural frequency.
- blades with tip seals and means for preventing vibrations have the disadvantage of large dissipation on the damper wire and in the tip seal.
- GB-A-10179 A.D. 1912 discloses cover bands arranged centrally on the blade tips.
- the invention tries to avoid all these disadvantages. Furthermore, it is based on the additional task of ensuring the guidance of the main flow in the case of blades of the type mentioned at the beginning.
- this is achieved in that the conical end of the blades seals on the inlet and outlet sides with the tip against the housing and in that the cover plate arranged in the middle at the blade end has three throttle points against the housing, the throttle point on the inlet side forming a diagonal gap.
- the advantage of the invention can be seen, inter alia, in the fact that only small amounts of gap occur in the new seal, which is particularly important in the case of output stages. In this way, high efficiencies of the combination power amplifier / diffuser can be achieved. In addition, low friction losses are to be expected due to the narrow shroud at the high peripheral speeds.
- cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this training, the inevitable Leakage flow deflected between the cover plates in the direction of the main flow.
- the parting line is provided with three steps, the steps running in the axial plane of the three throttling points.
- the blades come into contact between adjacent cover plates when the blades are unwinding. This creates the necessary damping effect.
- the blade end advantageously has a lower inclination than the housing contour.
- This inclination should be such that there is a positive offset at the blade end, which has its greatest value in the area of the blade leading edge and which protrudes into a gap relief chamber arranged in the housing. With this gap relief, a reduction in the leakage flow over the shroud is achieved by pushing the main flow near the gap.
- cover plate spike which forms the middle throttle point, is in the axial plane of the blade's heavy line, additional bending moments on the blade are avoided.
- honeycomb seals also ensure that the heat generated when touching remains as low as possible. This means that the strength properties of the highly stressed elements involved remain intact.
- the teeth of the cover plates which form the throttling points are preferably tapered in the circumferential direction on the cover plate overhangs.
- the three-stage gas turbine in FIG. 1 essentially consists of the bladed rotor 1 and the blade carrier 2 equipped with guide blades.
- the blade carrier which has a strongly conical channel contour of 40 °, is suspended in a turbine housing (not shown).
- the term blade carrier is synonymous with the term housing.
- the working medium enters the turbine from the outlet of the combustion chamber 3.
- the channel through which it flows opens into the exhaust gas housing, of which only the inner walls 4 of the diffuser are shown.
- the blading consists of three guide rows 5a, 5b and 5c and three run rows 6a, 6b and 6c.
- the blades of the guide rows seal against the rotor 1 by means of cover strips 7.
- the blades of the first rotor row 6a are free-standing; ie they seal with the blade tip against the blade carrier 2.
- the blades of the middle row 6b are provided with the cover plate seal 8 known per se, mentioned at the beginning.
- the actual seal consists of tines running in the circumferential direction, which run against a honeycomb arrangement (honeycomb) 9.
- honeycomb honeycomb
- the cover plates which extend across the entire blade width, form a stepped labyrinth with pure radial gaps. In the present case it is assumed that the rotor and the housing converge during operation due to the large relative axial expansions. For this reason, a further honeycomb arrangement 10 is provided on the blade carrier opposite the entry-side part of the cover plates against axial rubbing.
- the highly loaded blades 6 of the outlet row 6c have a pitch / chord ratio of approximately 1 in the radially outer region. They work at high peripheral speeds of up to 650 m / sec in a temperature range of up to 650 ° C.
- they are each provided with a cover plate 11 arranged centrally at the end of the blade, which plate forms three throttle points against the blade carrier 2.
- the plates are provided with circumferential serrations 12, 13, 14 in three different radial planes.
- the exit-side prong 14 forms, together with a honeycomb arrangement 15 inserted in the blade carrier 2, a radial gap 16.
- the entry-side prong 12 runs diagonally and, together with a correspondingly configured honeycomb arrangement 18, forms a diagonal gap 19.
- the operating position is shown in FIG. 2, that is to say the position in which the diagonal gap 19 represents the operating play.
- the axial expansion is therefore used to create a throttle gap.
- the three prongs enclose two vortex chambers 20, 21, the radial displacement of the throttle points not influencing one another.
- the conical end of the blades seals on the inlet and outlet sides with the tip 24, respectively. 29 against the housing.
- An additional throttle point 22 is thus formed at the blade inlet via this tip seal.
- the tip seal at the outlet also forms an additional throttling point 23 instead of the previous free swirl spaces at this point, as is contained in the cover plate seal 8 in the middle row 6b. This new type of tip seal at the outlet ensures a clean flow into the diffuser.
- the blade end is provided with a positive offset 31 on the inlet side.
- This offset is formed in that the blade tip has a smaller value than the taper 28 of the channel contour.
- the offset 31 projects into a gap relief chamber 25 arranged in the blade carrier 2.
- the inner contour of the gap relief chamber is adapted to the taper of the blade tip. This results in an aerodynamic relief of the blade gap. The pressure difference across the blade gap drops and the deflection is improved. This reduces the overall gap losses.
- Fig. 3 it can be seen that the cover plates 11 are rotationally symmetrical.
- the parting lines 26 between adjacent cover plates run in the direction of the chord.
- the circumferential sides of the cover plates are provided with three steps 27. These steps run in the axial plane of the three sealing teeth to ensure a continuous seal on the sealing surfaces. In addition, these stages take over the mechanical coupling of the cover plates to one another in order to achieve the damping effect.
- the teeth 12, 13 and 14 are tapered in the circumferential direction on the two overhangs of each cover plate. This Tapering 12a, 13a and 14a contribute significantly to the weight saving of the cover plates.
- the invention is not limited to the exemplary embodiment shown and described.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die Erfindung betrifft eine Vorrichtung zur Dichtung des Spaltes zwischen den Laufschaufeln und dem mit konischer Kontur ausgebildeteten Gehäuse einer Turbomaschine, wobei die Laufschaufeln mit umlaufenden Deckplatten versehen sind, welche mit Zacken unter Bildung von Radialspalten gegen das Gehäuse dichten.The invention relates to a device for sealing the gap between the rotor blades and the housing of a turbomachine which is designed with a conical contour, the rotor blades being provided with circumferential cover plates which seal against the housing with prongs to form radial gaps.
Derartige Vorrichtungen sind bekannt. Sie bestehen im wesentlichen aus Deckplatten mit in Umfangsrichtung verlaufenden Zacken, die gegen das Gehäuse oder gegen eine Honigwabenanordnung (honeycomb) dichten. Eine solche Anordnung ist z.B. aus der FR-A-2 406 074 bekannt, allerdings ist das Gehäuse darin zylindrisch ausgebildet. Dabei bilden sie ein glattes oder ein gestuftes Labyrinth mit reinen Radialspalten. In der Regel erstrecken sich diese Deckplatten über die ganze Schaufelbreite. Eine derartige bekannte Dichtung ist in der später zu beschreibenden Fig. 1 anhand der Laufschaufel der zweiten Stufe dargestellt. Bei den mechanisch und/oder thermisch hochbelasteten Laufschaufeln der letzten Stufe beispielsweise einer Gasturbine ist eine derartige Lösung mit herkömmlichen Werkstoffen nicht mehr möglich.Such devices are known. They essentially consist of cover plates with tines running in the circumferential direction, which seal against the housing or against a honeycomb arrangement (honeycomb). Such an arrangement is known, for example, from FR-A-2 406 074, but the housing therein is cylindrical. They form a smooth or a stepped labyrinth with pure radial gaps. As a rule, these cover plates extend over the entire blade width. Such a known seal is shown in FIG. 1 to be described later on the basis of the rotor blade of the second stage. With the mechanically and / or thermally highly loaded blades of the last stage, for example a gas turbine, such a solution with conventional materials is no longer possible.
Abhilfe schafft hier die klassische Spitzendichtung mit Dämpfervorrichtung in der Hauptströmung. Eine solche Dämpfervorrichtung, welche beispielsweise ein Dämpferdraht sein kann, ist unbedingt erforderlich bei freistehenden langen Schaufeln mit tiefer Eigenfrequenz. Schaufeln mit Spitzendichtung und Mitteln zur Schwingungsverhütung weisen indes den Nachteil von grosser Dissipation am Dämpferdraht und in der Spitzendichtung auf. Aus GB-A-10179 A.D.1912 sind mittig an den Schaufelspitzen angeordneten Deckbänder bekannt.This can be remedied by the classic tip seal with a damper device in the main flow. Such a damper device, which can be a damper wire, for example, is absolutely necessary for free-standing, long blades with a low natural frequency. However, blades with tip seals and means for preventing vibrations have the disadvantage of large dissipation on the damper wire and in the tip seal. GB-A-10179 A.D. 1912 discloses cover bands arranged centrally on the blade tips.
Die Erfindung versucht all diese Nachteile zu vermeiden. Desweiteren liegt ihr noch die zusätzliche Aufgabe zugrunde, bei Schaufeln der eingangs genannten Art die Führung der Hauptströmung zu gewährleisten.The invention tries to avoid all these disadvantages. Furthermore, it is based on the additional task of ensuring the guidance of the main flow in the case of blades of the type mentioned at the beginning.
Erfindungsgemäss wird dies dadurch erreicht, dass das konische Ende der Schaufeln eintrittseitig und austrittseitig mit der Spitze gegen das Gehäuse dichtet und dass die mittig am Schaufelende angeordnete Deckplatte drei Drosselstellen gegen das Gehäuse aufweist, wobei die eintrittseitige Drosselstelle einen Diagonalspalt bildet.According to the invention, this is achieved in that the conical end of the blades seals on the inlet and outlet sides with the tip against the housing and in that the cover plate arranged in the middle at the blade end has three throttle points against the housing, the throttle point on the inlet side forming a diagonal gap.
Der Vorteil der Erfindung ist unter anderem darin zu sehen, dass bei der neuen Dichtung nur kleine Spaltmengen auftreten, was insbesondere wichtig ist bei Endstufen. Hierdurch können hohe Wirkungsgrade der Kombination Endstufe/ Diffusor erzielt werden. Darüberhinaus sind durch das schmale Deckband bei den hohen Umfangsgeschwindigkeiten geringe Reibungsverluste zu erwarten.The advantage of the invention can be seen, inter alia, in the fact that only small amounts of gap occur in the new seal, which is particularly important in the case of output stages. In this way, high efficiencies of the combination power amplifier / diffuser can be achieved. In addition, low friction losses are to be expected due to the narrow shroud at the high peripheral speeds.
Es ist besonders zweckmässig, wenn die Deckplatten rotationssymmetrisch ausgebildet sind und wenn die Trennfugen zwischen benachbarten Deckplatten in Richtung der Profilsehne verlaufen. Bei dieser Ausbildung wird die unvermeidliche Leckströmung zwischen den Deckplatten in Richtung der Hauptströmung umgelenkt.It is particularly expedient if the cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this training, the inevitable Leakage flow deflected between the cover plates in the direction of the main flow.
Ferner ist es vorteilhaft, wenn die Trennfuge mit drei Stufen versehen ist, wobei die Stufen in der Axialebene der drei Drosselstellen verlaufen. Anlässlich des Betriebes der Turbomaschine kommt es in diesen Stufen zwischen benachbarten Deckpatten bei der Entwindung der Schaufeln zur Anlage. Hierdurch entsteht die erforderliche dämpfende Wirkung.It is also advantageous if the parting line is provided with three steps, the steps running in the axial plane of the three throttling points. On the occasion of the operation of the turbomachine, the blades come into contact between adjacent cover plates when the blades are unwinding. This creates the necessary damping effect.
Mit Vorteil weist das Schaufelende gegenüber der Gehäusekontur eine geringere Neigung auf. Dies Neigung soll so bemessen sein, dass ein positiver Versatz am Schaufelende entsteht, welcher seinen grössten Wert im Bereich der Schaufeleintrittskante aufweist und welcher in eine im Gehäuse angeordnete Spaltentlastungs-Kammer hineinragt. Mit dieser Spaltentlastung wird eine Reduktion des Leckagestromes über das Deckband erzielt, indem die Hauptströmung in Spaltnähe abgedrängt wird.The blade end advantageously has a lower inclination than the housing contour. This inclination should be such that there is a positive offset at the blade end, which has its greatest value in the area of the blade leading edge and which protrudes into a gap relief chamber arranged in the housing. With this gap relief, a reduction in the leakage flow over the shroud is achieved by pushing the main flow near the gap.
Sofern sich der Deckplatten-Zacken, welcher die mittlere Drosselstelle bildet, in der Axialebene der Schaufelschwerlinie befindet, werden zusätzliche Biegemomente auf das Schaufelblatt vermieden.If the cover plate spike, which forms the middle throttle point, is in the axial plane of the blade's heavy line, additional bending moments on the blade are avoided.
Ist darüberhinaus das Gehäuse an den drei Drosselstellen mit Honigwabenanordnungen versehen, so sind bei einem allfälligen Anstreifen keine Beschädigungen am hochempfindlichen Deckband zu erwarten; Diese Honigwabendichtungen bewirken auch, dass die Wärmeentwicklung beim Anstreifen möglichst gering bleibt. Damit bleiben auch die Festigkeitseigenschaften der beteiligten hochbelasteten Elemente intakt.In addition, if the housing is provided with honeycomb arrangements at the three throttling points, no damage to the highly sensitive cover tape is to be expected if it is touched; These honeycomb seals also ensure that the heat generated when touching remains as low as possible. This means that the strength properties of the highly stressed elements involved remain intact.
Schliesslich werden zur Gewichtsreduktion der Deckplatten vorzugsweise die die Drosselstellen bildenden Zacken der Deckplatten an den Deckplattenüberhängen in Umfangsrichtung verjüngt ausgebildet.Finally, in order to reduce the weight of the cover plates, the teeth of the cover plates which form the throttling points are preferably tapered in the circumferential direction on the cover plate overhangs.
In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand einer axialdurchströmten Gasturbine dargestellt.
Es zeigen:
- Fig. 1
- einen Teillängsschnitt der Gasturbine;
- Fig. 2
- einen Teilquerschnitt durch die Dichtvorrichtung der letzten Laufreihe;
- Fig. 3
- die teilweise Abwicklung einer Draufsicht auf die Schaufelenden der letzten Laufreihe.
Show it:
- Fig. 1
- a partial longitudinal section of the gas turbine;
- Fig. 2
- a partial cross section through the sealing device of the last row of runs;
- Fig. 3
- the partial processing of a top view of the blade ends of the last row of runs.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Nur angedeutet sind beispielsweise die angrenzenden Anlageteile wie Brennkammer und Austrittsdiffusor sowie die Schaufelfüsse. Nicht dargestellt ist die bei dieser Art von Maschinen übliche Schaufelkühlung. Die Strömungsrichtung der Arbeitsmittel ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The adjacent parts of the system, such as the combustion chamber and outlet diffuser, as well as the blade roots, are only indicated. The blade cooling that is common in this type of machine is not shown. The direction of flow of the work equipment is indicated by arrows.
Die dreistufige Gasturbine in Fig. 1 besteht im wesentlichen aus dem beschaufelten Rotor 1 und dem mit Leitschaufeln bestückten Schaufelträger 2. Der Schaufelträger, der eine stark konische Kanalkontur von 40° aufweist, ist in einem nichtgezeigten Turbinengehäuse eingehängt. Nachstehend ist der Begriff Schaufelträger gleichbedeutend mit dem Begriff Gehäuse. Vom Austritt der Brennkammer 3 gelangt das Arbeitsmittel in die Turbine. Deren durchströmter Kanal mündet in das Abgasgehäuse, von dem bloss die Innenwandungen 4 des Diffusors gezeigt sind. Die Beschaufelung besteht aus drei Leitreihen 5a, 5b und 5c sowie drei Laufreihen 6a, 6b und 6c. Die Schaufeln der Leitreihen dichten mittels Deckbändern 7 gegen den Rotor 1. Die Schaufeln der ersten Laufreihe 6a sind freistehend; d.h. sie dichten mit der Schaufelspitze gegen den Schaufelträger 2. Die Schaufeln der mittleren Laufreihe 6b sind mit der eingangs erwähnten, an sich bekannten Deckplattendichtung 8 versehen. Die eigentliche Dichtung besteht aus in Umfangsrichtung verlaufenden Zacken, die gegen eine Honigwabenanordnung (honeycomb) 9 laufen. Die sich über die ganze Schaufelbreite erstreckenden Deckplatten bilden dabei ein gestuftes Labyrinth mit reinen Radialspalten. Im vorliegenden Fall sei angenommen, dass während des Betriebes der Rotor und das Gehäuse anlässlich der grossen relativen Axialdehnungen aufeinander zulaufen. Deshalb ist gegen axiales Anstreifen eine weitere Honigwabenanordnung 10 am Schaufelträger gegenüber der eintrittsseitigen Partie der Deckplatten vorgesehen.The three-stage gas turbine in FIG. 1 essentially consists of the bladed rotor 1 and the
Die hoch belasteten Laufschaufeln 6 der Austrittslaufreihe 6c weisen im radial äusseren Bereich ein Verhältnis Teilung/Sehne von ca. 1 auf. Sie arbeiten mit grossen Spitzenumfangsgeschwindigkeiten von bis zu 650 m/sec in einem Temperaturbereich von bis zu 650°C. Sie sind gemäss Fig. 2 mit je einer mittig am Schaufelende angeordneten Deckplatte 11 versehen, welche drei Drosselstellen gegen den Schaufelträger 2 bildet. Hierzu sind die Platten in drei verschiedenen Radialebenen mit umlaufenden Zacken 12, 13, 14 versehen. Der austrittseitige Zacken 14 bildet zusammen mit einer im Schaufelträger 2 eingesetzten Honigwabenanordnung 15 einen Radialspalt 16. Der mittlere Zacken 13, welcher sich in der Axialebene der Schaufelschwerlinie 30 befindet, bildet zusammen mit der gleichen, an entsprechender Stelle abgestuften Honigwabenanordnung 15 ebenfalls einen Radialspalt 17. Der eintrittseitige Zacken 12 verläuft diagonal und bildet zusammen mit einer entsprechend konfigurierten Honigwabenanordnung 18 einen Diagonalspalt 19. In Fig. 2 ist die Betriebsposition gezeigt, jene Stellung also, bei welcher der Diagonalspalt 19 das Betriebsspiel darstellt. Die Axialdehnung wird also ausgenutzt, um einen Drosselspalt zu kreieren.The highly loaded
Die drei Zacken schliessen zwei Wirbelkammern 20, 21 ein, wobei durch die radiale Versetzung der Drosselstellen diese sich gegenseitig nicht beeinflussen. Das konische Ende der Schaufeln dichtet eintrittseitig und austrittseitig mit der Spitze 24 resp. 29 gegen das Gehäuse. Am Schaufeleintritt wird somit über diese Spitzendichtung eine zusätzliche Drosselstelle 22 gebildet. Die Spitzendichtung am Austritt bildet ebenfalls eine zusätzliche Drosselstelle 23 anstelle der bisherigen freien Wirbelräume an dieser Stelle, wie sie die Deckplattendichtung 8 bei der mittleren Laufreihe 6b beinhaltet. Diese neue Art der Spitzendichtung am Austritt bewirkt eine sauber geführte Abströmung in den Diffusor.The three prongs enclose two
Gemäss Fig. 2 ist das Schaufelende eintrittseitig mit einem positiven Versatz 31 versehen. Dieser Versatz wird dadurch gebildet, dass die Schaufelspitze gegenüber der Konizität 28 der Kanalkontur einen kleineren Wert aufweist. Der Versatz 31 ragt in eine im Schaufelträger 2 angeordnete Spaltentlastungs-Kammer 25 hinein. Zur Bildung der dortigen Spitzendichtung ist die Innenkontur der Spaltentlastungs-Kammer an die Konizität der Schaufelspitze angepasst. Hierdurch wird eine aerodynamische Entlastung des Schaufelspaltes bewirkt. Die Druckdifferenz über dem Schaufelspalt sinkt und die Umlenkung wird verbessert. Dadurch werden insgesamt die sogenannten Spaltverluste reduziert.2, the blade end is provided with a positive offset 31 on the inlet side. This offset is formed in that the blade tip has a smaller value than the
In Fig. 3 ist erkennbar, dass die Deckplatten 11 rotationssymmetrisch ausgebildet sind. Die Trennfugen 26 zwischen benachbarten Deckplatten verlaufen in Richtung der Profilsehne. Die in Umfangsrichtung gelegenen Seiten der Deckplatten sind mit drei Stufen 27 versehen. Diese Stufen verlaufen in der Axialebene der drei Dichtzacken, um an den Dichtflächen eine durchgehende Dichtung zu gewährleisten. Darüberhinaus übernehmen diese Stufen die mechanische Kopplung der Deckplatten untereinander zwecks Erzielung der dämpfenden Wirkung. Die Zacken 12, 13 und 14 sind an den beiden Überhängen jeder Deckplatte in Umfangsrichtung verjüngt. Diese Verjüngungen 12a, 13a und 14a tragen wesentlich zur Gewichtsersparnis der Deckplatten bei.In Fig. 3 it can be seen that the
Selbstverständlich ist die Erfindung nicht auf das gezeigte und beschriebene Ausführungsbeispiel beschränkt. In Abweichung zur in Fig. 2 gezeigten Ausbildung könnte es zweckmässig sein, die Deckplatte mitsamt der Diagonaldichtung näher zur Schaufeleintrittskante heranzuziehen, ggfs sogar bündig mit der Eintrittskante zu gestalten, sofern dies die Festigkeitserfordernisse zulassen.Of course, the invention is not limited to the exemplary embodiment shown and described. In deviation from the design shown in FIG. 2, it could be expedient to pull the cover plate together with the diagonal seal closer to the blade leading edge, possibly even to make it flush with the leading edge, provided that the strength requirements permit this.
- 11
- Rotorrotor
- 22nd
- Schaufelträger, GehäuseBlade carrier, housing
- 33rd
- BrennkammerCombustion chamber
- 44th
- Innenwandungen des DiffusorsInner walls of the diffuser
- 66
- LaufschaufelBlade
- 5a,b,c5a, b, c
- LeitreiheGuiding series
- 6a,b,c6a, b, c
- LaufreiheRunning row
- 77
- DeckbänderShrouds
- 88th
- DeckplattendichtungCover plate seal
- 99
- Honigwabenanordnung radialHoneycomb arrangement radial
- 1010th
- Honigwabenanordnung axialHoneycomb arrangement axial
- 1111
- DeckplatteCover plate
- 1212th
- ZackenPink
- 12a12a
- Verjüngungrejuvenation
- 1313
- ZackenPink
- 13a13a
- Verjüngungrejuvenation
- 1414
- ZackenPink
- 14a14a
- Verjüngungrejuvenation
- 1515
- HonigwabenanordnungHoneycomb arrangement
- 1616
- RadialspaltRadial gap
- 1717th
- RadialspaltRadial gap
- 1818th
- HonigwabenanordnungHoneycomb arrangement
- 1919th
- DiagonalspaltDiagonal gap
- 2020th
- WirbelkammerVortex chamber
- 2121
- WirbelkammerVortex chamber
- 2222
- DrosselstelleThrottling point
- 2323
- DrosselstelleThrottling point
- 2424th
- Schaufelspitze eintrittseitigBlade tip on the inlet side
- 2525th
- Spaltentlastungs-KammerGap relief chamber
- 2626
- TrennfugeParting line
- 2727
- Stufestep
- 2828
- KonizitätTaper
- 2929
- Schaufelspitze austrittseitigBlade tip on the outlet side
- 3030th
- SchaufelschwerlinieHeavy bucket line
- 3131
- positiver Versatz am Schaufelendepositive offset at the end of the bucket
Claims (8)
- Device for sealing the gap between the rotor blades and the casing (2) of a turbomachine, configured with a conical profile (28), in which the rotor blades (6) are fitted with circumferential shroud plates (11), which seal by means of serrations (12, 13, 14) against the casing with the formation of radial gaps (16, 17), characterized in that the tips (24, 29) of the conical ends of the blades (6) seal against the casing (2) at the inlet and outlet ends, and the shroud plate (11), located centrally at the end of the blade, has three throttle locations relative to the casing, the inlet end throttle location forming a diagonal gap (19).
- Device according to Claim 1, characterized in that the shroud plates (11) are configured so as to be symmetrical with respect to the axis of rotation.
- Device according to Claim 1, characterized in that the dividing lines (26) between adjacent shroud plates (11) extend in the direction of the profile chord.
- Device according to Claim 3, characterized in that the dividing line (11) [sic] is provided with three steps (27), the steps extending in the axial plane of the serrations (12, 13, 14).
- Device according to Claim 1, characterized in that the end of the blade has a smaller hade angle than the casing profile (28) in such a way that the positive offset (31) produced at the end of the blade protrudes into a gap relief chamber (25) located in the casing (2).
- Device according Claim 1, characterized in that the shroud plate serration (13) forming the central throttle location is situated at least approximately in the axial plane of the blade's centre of gravity (16).
- Device according to Claim 1, characterized in that the casing at the three throttle locations is fitted with honeycomb arrangements (15, 18).
- Device according to Claim 1, characterized in that the serrations (12, 13, 14) of the shroud plates (11) forming the throttle locations are tapered (12a, 13a, 14a) in the circumferential direction on the shroud plate overhangs.
(Fig. 2)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH234991 | 1991-08-08 | ||
| CH2349/91 | 1991-08-08 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0528138A1 EP0528138A1 (en) | 1993-02-24 |
| EP0528138B1 true EP0528138B1 (en) | 1995-05-17 |
Family
ID=4231716
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP92110494A Expired - Lifetime EP0528138B1 (en) | 1991-08-08 | 1992-06-22 | Blade shroud for axial turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5238364A (en) |
| EP (1) | EP0528138B1 (en) |
| JP (1) | JPH05195815A (en) |
| CA (1) | CA2074326A1 (en) |
| DE (1) | DE59202211D1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106988797A (en) * | 2015-11-11 | 2017-07-28 | 通用电气公司 | System for the section of the integration of turbine |
Families Citing this family (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19821365C2 (en) * | 1998-05-13 | 2001-09-13 | Man Turbomasch Ag Ghh Borsig | Cooling a honeycomb seal in the part of a gas turbine charged with hot gas |
| US6231301B1 (en) | 1998-12-10 | 2001-05-15 | United Technologies Corporation | Casing treatment for a fluid compressor |
| EP1026367A1 (en) * | 1999-02-05 | 2000-08-09 | Siemens Aktiengesellschaft | Turbomachine rotor blade tip sealing |
| US6241471B1 (en) * | 1999-08-26 | 2001-06-05 | General Electric Co. | Turbine bucket tip shroud reinforcement |
| US6896483B2 (en) | 2001-07-02 | 2005-05-24 | Allison Advanced Development Company | Blade track assembly |
| RU2302534C2 (en) * | 2001-12-11 | 2007-07-10 | Альстом (Свитзерлэнд) Лтд. | Gas-turbine device |
| US6805530B1 (en) * | 2003-04-18 | 2004-10-19 | General Electric Company | Center-located cutter teeth on shrouded turbine blades |
| US6890150B2 (en) * | 2003-08-12 | 2005-05-10 | General Electric Company | Center-located cutter teeth on shrouded turbine blades |
| US6913445B1 (en) * | 2003-12-12 | 2005-07-05 | General Electric Company | Center located cutter teeth on shrouded turbine blades |
| DE102004025321A1 (en) * | 2004-05-19 | 2005-12-08 | Alstom Technology Ltd | Turbomachine blade |
| US20070273104A1 (en) * | 2006-05-26 | 2007-11-29 | Siemens Power Generation, Inc. | Abradable labyrinth tooth seal |
| EP1862641A1 (en) | 2006-06-02 | 2007-12-05 | Siemens Aktiengesellschaft | Annular flow channel for axial flow turbomachine |
| US8568095B2 (en) * | 2006-12-29 | 2013-10-29 | Carrier Corporation | Reduced tip clearance losses in axial flow fans |
| GB2445952B (en) * | 2007-01-25 | 2011-07-20 | Siemens Ag | A gas turbine engine |
| US7901180B2 (en) * | 2007-05-07 | 2011-03-08 | United Technologies Corporation | Enhanced turbine airfoil cooling |
| US8534993B2 (en) * | 2008-02-13 | 2013-09-17 | United Technologies Corp. | Gas turbine engines and related systems involving blade outer air seals |
| DE102008023326A1 (en) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Shroud for blades of a turbomachine and turbomachine |
| DE102008038038A1 (en) * | 2008-08-16 | 2010-02-18 | Mtu Aero Engines Gmbh | Blade system for a blade row of a turbomachine |
| US8608424B2 (en) * | 2009-10-09 | 2013-12-17 | General Electric Company | Contoured honeycomb seal for a turbomachine |
| WO2011070636A1 (en) * | 2009-12-07 | 2011-06-16 | 三菱重工業株式会社 | Turbine and turbine rotor blade |
| US8821114B2 (en) | 2010-06-04 | 2014-09-02 | Siemens Energy, Inc. | Gas turbine engine sealing structure |
| DE102011086775A1 (en) * | 2011-07-20 | 2013-01-24 | Mtu Aero Engines Gmbh | Method for producing an inlet lining, inlet system, turbomachine and vane |
| JP5464233B2 (en) * | 2012-05-25 | 2014-04-09 | 株式会社Ｉｈｉ | Compressor blade |
| EP2998517B1 (en) * | 2014-09-16 | 2019-03-27 | Ansaldo Energia Switzerland AG | Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement |
| JP6571322B2 (en) * | 2014-10-06 | 2019-09-04 | 時夫 大川 | Air-water thermal power generation system |
| US10808539B2 (en) * | 2016-07-25 | 2020-10-20 | Raytheon Technologies Corporation | Rotor blade for a gas turbine engine |
| DE102019216646A1 (en) * | 2019-10-29 | 2021-04-29 | MTU Aero Engines AG | BLADE ARRANGEMENT FOR A FLOW MACHINE |
| JP2021110291A (en) * | 2020-01-10 | 2021-08-02 | 三菱重工業株式会社 | Rotor blade and axial flow rotary machine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE485833C (en) * | 1929-11-08 | J A Maffei A G | Process for the production of blades for turbo machines, in particular for steam or gas turbines | |
| GB191210179A (en) * | 1911-05-04 | 1912-06-20 | Heinrich Holzer | Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids. |
| GB804922A (en) * | 1956-01-13 | 1958-11-26 | Rolls Royce | Improvements in or relating to axial-flow fluid machines for example compressors andturbines |
| FR1403799A (en) * | 1964-05-13 | 1965-06-25 | Rateau Soc | Turbine wheel subjected to partial injection |
| CH414681A (en) * | 1964-11-24 | 1966-06-15 | Bbc Brown Boveri & Cie | Turbo machine |
| US3677660A (en) * | 1969-04-08 | 1972-07-18 | Mitsubishi Heavy Ind Ltd | Propeller with kort nozzle |
| GB1423833A (en) * | 1972-04-20 | 1976-02-04 | Rolls Royce | Rotor blades for fluid flow machines |
| US4370094A (en) * | 1974-03-21 | 1983-01-25 | Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft | Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors |
| DE2745130C2 (en) * | 1977-10-07 | 1980-01-03 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Sealing device for the free blade ends of axial turbines |
| FR2406074A1 (en) * | 1977-10-11 | 1979-05-11 | Snecma | SAFETY DEVICE FOR AXIAL ROTATING MACHINE |
| FR2452601A1 (en) * | 1979-03-30 | 1980-10-24 | Snecma | REMOVABLE SEALING COVER FOR TURBOJET BLOWER HOUSING |
| US4576551A (en) * | 1982-06-17 | 1986-03-18 | The Garrett Corporation | Turbo machine blading |
| FR2552159B1 (en) * | 1983-09-21 | 1987-07-10 | Snecma | DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS |
| US4606699A (en) * | 1984-02-06 | 1986-08-19 | General Electric Company | Compressor casing recess |
| JPS6123804A (en) * | 1984-07-10 | 1986-02-01 | Hitachi Ltd | Turbine stage structure |
| US4710102A (en) * | 1984-11-05 | 1987-12-01 | Ortolano Ralph J | Connected turbine shrouding |
| JPS61207802A (en) * | 1985-03-11 | 1986-09-16 | ユナイテツド・テクノロジーズ・コーポレイシヨン | Gas turbine engine |
| GB2215407A (en) * | 1988-03-05 | 1989-09-20 | Rolls Royce Plc | A bladed rotor assembly |
-
1992
- 1992-06-22 DE DE59202211T patent/DE59202211D1/en not_active Expired - Fee Related
- 1992-06-22 EP EP92110494A patent/EP0528138B1/en not_active Expired - Lifetime
- 1992-07-21 CA CA002074326A patent/CA2074326A1/en not_active Abandoned
- 1992-07-22 US US07/916,709 patent/US5238364A/en not_active Expired - Fee Related
- 1992-08-07 JP JP4211334A patent/JPH05195815A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106988797A (en) * | 2015-11-11 | 2017-07-28 | 通用电气公司 | System for the section of the integration of turbine |
| CN106988797B (en) * | 2015-11-11 | 2020-10-23 | 通用电气公司 | System for integrated section of turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| DE59202211D1 (en) | 1995-06-22 |
| EP0528138A1 (en) | 1993-02-24 |
| CA2074326A1 (en) | 1993-02-09 |
| US5238364A (en) | 1993-08-24 |
| JPH05195815A (en) | 1993-08-03 |
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