EP0536575B1 - Shroud band for axial flow turbine - Google Patents
Shroud band for axial flow turbine Download PDFInfo
- Publication number
- EP0536575B1 EP0536575B1 EP92116009A EP92116009A EP0536575B1 EP 0536575 B1 EP0536575 B1 EP 0536575B1 EP 92116009 A EP92116009 A EP 92116009A EP 92116009 A EP92116009 A EP 92116009A EP 0536575 B1 EP0536575 B1 EP 0536575B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gap
- casing
- blade
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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, see e.g. the previously published document FR-A-2 406 074. They consist essentially of cover plates with circumferential tines which seal against the housing or against a honeycomb arrangement (honeycomb). 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 which has two sealing prongs, is shown in FIG. 1 to be described later with reference to the rotor blade of the first stage.
- the invention has for its object to ensure clean guidance of the main flow in blades of the type mentioned and to create a shroud which is accessible to good cooling and good cooling.
- the cover plate arranged at the blade end has four throttle points against the housing, the throttle point on the inlet side forming a diagonal gap in the stationary operating state.
- the outlet-side throttle point preferably forms a radial 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. As a result, high efficiencies can be achieved. In addition, a good introduction of the gap flow into the main flow is achieved.
- cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this design, the inevitable leakage flow between the cover plates is deflected in the direction of the main flow.
- the parting line is provided with four 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 inlet-side 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, together with the associated cover plate part, projects 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.
- the housing is provided with honeycomb arrangements at the four 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.
- the tines of the cover plates forming 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 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 arrangement
- the cover plates which extend across the entire blade width, form a classified labyrinth with pure radial gaps.
- the highly loaded blades 6 of the outlet barrel row 6c are each provided with a cover plate 30 arranged centrally at the blade end, which forms three throttle points against the blade carrier 2.
- the blades of the middle row of races are provided with cover plates 11 which, according to FIG. 2, counter four throttling points form the blade carrier 2.
- the plates are provided with circumferential teeth 12, 13, 14 and 15 in four different radial planes.
- the outlet-side prongs 15, together with a honeycomb arrangement 25 inserted in the blade carrier 2, form a radial gap 16.
- the middle prongs 13 and 14 likewise form radial gaps 17 and 28 with the opposite honeycomb arrangements 27 and 28. 18.
- the entry-side prong 12 runs diagonally and forms a diagonal gap 19 together with a correspondingly configured honeycomb arrangement 26.
- 2 shows the operating position, 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 four prongs enclose three vortex chambers 20, 21, 22, the radial displacement of the throttle points not influencing one another.
- the new type of seal at the outlet by means of a radial gap results in a cleanly guided outflow into the channel through which the previous free swirl spaces exist, as is contained in the cover plate seal 8 in the first row 5b.
- the wall 29 of the channel through which the honeycomb arrangement 25 adjoins is initially rounded off slightly before it changes into the slope of the channel contour. With this measure, a deflecting Coanda effect is exerted on the gap stream emerging from the radial gap 16, so that the main flow is impaired as little as possible.
- the blade end is provided with a positive offset 10 on the inlet side.
- This offset is formed in that the blade tip has a smaller value than the taper 32 of the channel contour.
- the offset 10 projects together with the cover plate part belonging to it a gap relief chamber 31 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 23 between adjacent cover plates run in the direction of the chord.
- the circumferential sides of the cover plates are provided with four steps 24. These steps run in the axial plane of the four 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 prongs 12, 13, 14 and 15 are tapered in the circumferential direction on the two overhangs of each cover plate. These tapers 12a, 13a, 14a and 15a contribute significantly to the weight saving of the cover plates.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (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, siehe z.B. das vorveröffentlichte Dokument FR-A-2 406 074. Sie bestehen im wesentlichen aus Deckplatten mit in Umfangsrichtung verlaufenden Zacken, die gegen das Gehäuse oder gegen eine Honigwabenanordnung (honeycomb) dichten. 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, zwei Dichtzacken aufweisende Dichtung ist in der später zu beschreibenden Fig. 1 anhand der Laufschaufel der ersten Stufe dargestellt.Such devices are known, see e.g. the previously published document FR-A-2 406 074. They consist essentially of cover plates with circumferential tines which seal against the housing or against a honeycomb arrangement (honeycomb). 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, which has two sealing prongs, is shown in FIG. 1 to be described later with reference to the rotor blade of the first stage.
Von Nachteil sind bei diesen Dichtungen die beiden vor und hinter den Zacken gebildeten grossen Wirbelräume, welche eine grosse Dissipation bewirken. Zudem erschweren die offenen Räume die Kühlung der Deckplatten.A disadvantage of these seals is the two large swirl spaces that are formed in front of and behind the teeth cause a large dissipation. In addition, the open spaces make it difficult to cool the cover plates.
Die Erfindung liegt die Aufgabe zugrunde, bei Schaufeln der eingangs genannten Art eine saubere Führung der Hauptströmung zu gewährleisten und ein Deckband zu schaffen, welches neben guter Dichtwirkung auch einer guten Kühlung zugänglich ist.The invention has for its object to ensure clean guidance of the main flow in blades of the type mentioned and to create a shroud which is accessible to good cooling and good cooling.
Erfindungsgemäss wird dies dadurch erreicht, dass die am Schaufelende angeordnete Deckplatte vier Drosselstellen gegen das Gehäuse aufweist, wobei die eintrittseitige Drosselstelle im stationären Betriebszustand einen Diagonalspalt bildet. Vorzugsweise bildet die austrittseitige Drosselstelle einen Radialspalt.This is achieved according to the invention in that the cover plate arranged at the blade end has four throttle points against the housing, the throttle point on the inlet side forming a diagonal gap in the stationary operating state. The outlet-side throttle point preferably forms a radial gap.
Der Vorteil der Erfindung ist unter anderem darin zu sehen, dass bei der neuen Dichtung nur kleine Spaltmengen auftreten. Hierdurch können hohe Wirkungsgrade erzielt werden. Zudem wird eine gute Einführung der Spaltströmung in die Hauptströmung erreicht.The advantage of the invention can be seen, inter alia, in the fact that only small amounts of gap occur in the new seal. As a result, high efficiencies can be achieved. In addition, a good introduction of the gap flow into the main flow is achieved.
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 design, the inevitable leakage flow between the cover plates is deflected in the direction of the main flow.
Ferner ist es vorteilhaft, wenn die Trennfuge mit vier 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 Wir kung.It is also advantageous if the parting line is provided with four 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 eintrittsseitige 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 zusammen mit dem zugehörigen Deckplattenteil 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 inlet-side 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, together with the associated cover plate part, projects 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.
Ist darüberhinaus das Gehäuse an den vier 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.If, in addition, the housing is provided with honeycomb arrangements at the four 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 tines of the cover plates forming 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 zweiten Laufreihe;
- Fig. 3
- die teilweise Abwicklung einer Draufsicht auf die Schaufelenden der zweiten Laufreihe.
- Fig. 1
- a partial longitudinal section of the gas turbine;
- Fig. 2
- a partial cross section through the sealing device of the second row of runs;
- Fig. 3
- the partial settlement of a top view of the blade ends of the second 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 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 eingestuftes Labyrinth mit reinen Radialspalten.The three-stage gas turbine in FIG. 1 essentially consists of the
Die hoch belasteten Laufschaufeln 6 der Austrittslaufreihe 6c mit je einer mittig am Schaufelende angeordneten Deckplatte 30 versehen, welche drei Drosselstellen gegen den Schaufelträger 2 bildet.The highly loaded
Die Schaufeln der mittleren Laufreihe sind mit Deckplatten 11 versehen, welche gemäss Fig. 2 vier Drosselstellen gegen den Schaufelträger 2 bilden. Hierzu sind die Platten in vier verschiedenen Radialebenen mit umlaufenden Zacken 12, 13, 14 und 15 versehen. Der austrittseitige Zacken 15 bildet zusammen mit einer im Schaufelträger 2 eingesetzten Honigwabenanordnung 25 einen Radialspalt 16. Die mittleren Zacken 13 und 14 bilden mit den gegenüberliegenden Honigwabenanordnungen 27 und 28 ebenfalls Radialspalte 17 resp. 18. Der eintrittseitige Zacken 12 verläuft diagonal und bildet zusammen mit einer entsprechend konfigurierten Honigwabenanordnung 26 einen Diagonalspalt 19. Im vorliegenden Fall sei angenommen, dass während des Betriebes der Rotor und das Gehäuse anlässlich der grossen relativen Axialdehnungen auf einander zulaufen. In Fig. 2 ist somit 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 blades of the middle row of races are provided with cover plates 11 which, according to FIG. 2, counter four throttling points form the
Die vier Zacken schliessen drei Wirbelkammern 20, 21, 22 ein, wobei durch die radiale Versetzung der Drosselstellen diese sich gegenseitig nicht beeinflussen.The four prongs enclose three
Die neue Art der Dichtung am Austritt mittels Radialspalt bewirkt eine sauber geführte Abströmung in den durchströmten Kanal gegenüber der bisherigen freien Wirbelräume an dieser Stelle, wie sie die Deckplattendichtung 8 bei der ersten Laufreihe 5b beinhaltet. Die an die Honigwabenanordnung 25 angrenzende Wandung 29 des durchströmten Kanals ist zunächst leicht abgerundet, bevor sie in die Schräge der Kanalkontur übergeht. Mit dieser Massnahme wird auf den aus dem Radialspalt 16 austretenden Spaltstrom ein umlenkender Coanda-Effekt ausgeübt, so dass die Hauptströmung möglichst wenig beeinträchtigt wird.The new type of seal at the outlet by means of a radial gap results in a cleanly guided outflow into the channel through which the previous free swirl spaces exist, as is contained in the
Gemäss Fig. 2 ist das Schaufelende eintrittseitig mit einem positiven Versatz 10 versehen. Dieser Versatz wird dadurch gebildet, dass die Schaufelspitze gegenüber der Konizität 32 der Kanalkontur einen kleineren Wert aufweist. Der Versatz 10 ragt zusammen mit dem ihm zugehörigen Deckplattenteil in eine im Schaufelträger 2 angeordnete SpaltentlastungsKammer 31 hinein. Die Innenkontur der Spaltentlastungs-Kammer ist 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 10 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 23 zwischen benachbarten Deckplatten verlaufen in Richtung der Profilsehne. Die in Umfangsrichtung gelegenen Seiten der Deckplatten sind mit vier Stufen 24 versehen. Diese Stufen verlaufen in der Axialebene der vier 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, 14 und 15 sind an den beiden Überhängen jeder Deckplatte in Umfangsrichtung verjüngt. Diese Verjüngungen 12a, 13a, 14a und 15a tragen wesentlich zur Gewichtsersparnis der Deckplatten bei.In Fig. 3 it can be seen that the cover plates 11 are rotationally symmetrical. The parting lines 23 between adjacent cover plates run in the direction of the chord. The circumferential sides of the cover plates are provided with four
- 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
- Deckplattendichtung für 6aCover plate seal for 6a
- 99
- Honigwabenanordnung radialHoneycomb arrangement radial
- 1010th
- positiver Versatz am Schaufelende von 6bpositive offset at the blade end of 6b
- 1111
- Deckplatte für 6bCover plate for 6b
- 1212th
- ZackenPink
- 12a12a
- Verjüngungrejuvenation
- 1313
- ZackenPink
- 13a13a
- Verjüngungrejuvenation
- 1414
- ZackenPink
- 14a14a
- Verjüngungrejuvenation
- 1515
- ZackenPink
- 15a15a
- Verjüngungrejuvenation
- 1616
- RadialspaltRadial gap
- 1717th
- RadialspaltRadial gap
- 1818th
- RadialspaltRadial gap
- 1919th
- DiagonalspaltDiagonal gap
- 2020th
- WirbelkammerVortex chamber
- 2121
- WirbelkammerVortex chamber
- 2222
- WirbelkammerVortex chamber
- 2323
- TrennfugeParting line
- 2424th
- Stufestep
- 2525th
- HonigwabenanordnungHoneycomb arrangement
- 2626
- HonigwabenanordnungHoneycomb arrangement
- 2727
- HonigwabenanordnungHoneycomb arrangement
- 2828
- HonigwabenanordnungHoneycomb arrangement
- 2929
- WandungWall
- 3030th
- Deckplatte für 6cCover plate for 6c
- 3131
- Spaltentlastungs-KammerGap relief chamber
- 3232
- KonizitätTaper
Claims (9)
- 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 provided with circumferential shroud plates (11), which seal by means of serrations (12, 13, 14, 15) against the casing with the formation of radial gaps (16, 17, 18), characterized in that the shroud plate (11), which is arranged at the end of the blade, has four throttle locations relative to the casing, the inlet end throttle location forming a diagonal gap (19) in the steady-state operating condition.
- Device according to Claim 1, characterized in that the outlet end throttle location forms a radial gap (16).
- Device according to Claim 1, characterized in that the shroud plates (11) are configured so as to be symmetrical about the axis of rotation.
- Device according to Claim 1, characterized in that the dividing lines (23) between adjacent shroud plates (11) extend in the direction of the profile chord.
- Device according to Claim 4, characterized in that the dividing line (11) is provided with four steps (24), the steps extending in the axial plane of the serrations (12, 13, 14).
- Device according to Claim 1, characterized in that the casing is provided with honeycomb arrangements (25, 26, 27, 28) at the four throttle locations.
- Device according to Claim 1, characterized in that the end of the blade has a smaller hade angle than the casing profile (32) at the inlet end, such that the resulting positive offset (10) at the end of the blade protrudes together with the associated shroud plate part into a gap relief chamber (31) formed in the casing (2).
- Device according to Claim 1, characterized in that the serrations (12, 13, 14, 15) of the shroud plates (11) forming the throttle locations are tapered (12a, 13a, 14a, 15a) in the circumferential direction at the shroud plate overhangs.
- Device according to Claim 1, characterized in that the flow duct wall (29) which adjoins the outlet end honeycomb arrangement (25) is slightly rounded before it makes the transition to the slope of the duct profile.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH2965/91 | 1991-10-08 | ||
| CH296591 | 1991-10-08 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0536575A1 EP0536575A1 (en) | 1993-04-14 |
| EP0536575B1 true EP0536575B1 (en) | 1995-04-05 |
Family
ID=4245626
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP92116009A Expired - Lifetime EP0536575B1 (en) | 1991-10-08 | 1992-09-18 | Shroud band for axial flow turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5290144A (en) |
| EP (1) | EP0536575B1 (en) |
| JP (1) | JP3307692B2 (en) |
| DE (1) | DE59201833D1 (en) |
| PL (1) | PL296074A1 (en) |
Families Citing this family (36)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
| JP3477347B2 (en) * | 1997-07-30 | 2003-12-10 | 三菱重工業株式会社 | Gas turbine interstage seal device |
| DE59710621D1 (en) * | 1997-09-19 | 2003-09-25 | Alstom Switzerland Ltd | Gap sealing device |
| US6231301B1 (en) | 1998-12-10 | 2001-05-15 | United Technologies Corporation | Casing treatment for a fluid compressor |
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| KR102238435B1 (en) * | 2019-04-30 | 2021-04-09 | 두산중공업 주식회사 | Sealing module of turbine and power generating turbine apparatus having the same |
| JP2021110291A (en) * | 2020-01-10 | 2021-08-02 | 三菱重工業株式会社 | Rotor blade and axial flow rotary machine |
| CN113266431B (en) * | 2021-06-03 | 2022-08-09 | 西安交通大学 | Radial turbine blade tip clearance ultrasonic sealing structure |
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-
1992
- 1992-09-18 EP EP92116009A patent/EP0536575B1/en not_active Expired - Lifetime
- 1992-09-18 DE DE59201833T patent/DE59201833D1/en not_active Expired - Lifetime
- 1992-09-28 PL PL29607492A patent/PL296074A1/en unknown
- 1992-09-28 US US07/951,839 patent/US5290144A/en not_active Expired - Lifetime
- 1992-10-07 JP JP26836992A patent/JP3307692B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| US5290144A (en) | 1994-03-01 |
| EP0536575A1 (en) | 1993-04-14 |
| DE59201833D1 (en) | 1995-05-11 |
| JPH05195988A (en) | 1993-08-06 |
| PL296074A1 (en) | 1993-05-17 |
| JP3307692B2 (en) | 2002-07-24 |
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