EP0536575A1 - Shroud band for axial flow turbine - Google Patents
Shroud band for axial flow turbine Download PDFInfo
- Publication number
- EP0536575A1 EP0536575A1 EP92116009A EP92116009A EP0536575A1 EP 0536575 A1 EP0536575 A1 EP 0536575A1 EP 92116009 A EP92116009 A EP 92116009A EP 92116009 A EP92116009 A EP 92116009A EP 0536575 A1 EP0536575 A1 EP 0536575A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- gap
- cover plates
- cover plate
- blade end
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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. They essentially consist of cover plates with tines running in the circumferential direction, 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 object of the invention is to ensure clean guidance of the main flow in the case of blades of the type mentioned at the beginning and to provide a shroud which, in addition to good sealing action, is also accessible to good cooling.
- the cover plate arranged at the blade end has four throttling points against the housing, the throttling 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 through 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. 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 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 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 serrations 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 suitably configured honeycomb arrangement 26.
- the operating position is thus shown in FIG. 2, that is to say the position in which the diagonal gap 19 represents the operating play.
- the axial expansion is thus 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 vortex 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 so-called gap losses overall.
- 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 teeth 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)
Abstract
Bei einer Vorrichtung zur Dichtung des Spaltes zwischen den Laufschaufeln und dem mit konischer Kontur (28) ausgebildeteten Gehäuse (2) einer Turbomaschine sind die Laufschaufeln (6) mit umlaufenden Deckplatten (11) versehen, welche mit Zacken (12, 13, 14, 15) unter Bildung von Radialspalten (16, 17, 18) gegen das Gehäuse dichten. Die am Schaufelende angeordnete Deckplatte (11) weist vier Drosselstellen gegen das Gehäuse auf, wobei die eintrittseitige Drosselstelle einen Diagonalspalt (19) begrenzt und die austrittseitige Drosselstelle einen Radialspalt (16) bildet. <IMAGE>In a device for sealing the gap between the rotor blades and the housing (2) of a turbomachine which is designed with a conical contour (28), the rotor blades (6) are provided with circumferential cover plates (11) which have teeth (12, 13, 14, 15) ) seal against the housing to form radial gaps (16, 17, 18). The cover plate (11) arranged at the blade end has four throttle points against the housing, the throttle point on the inlet side delimiting a diagonal gap (19) and the throttle point on the outlet side forming a radial gap (16). <IMAGE>
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. 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. They essentially consist of cover plates with tines running in the circumferential direction, 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 vortex 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 object of the invention is to ensure clean guidance of the main flow in the case of blades of the type mentioned at the beginning and to provide a shroud which, in addition to good sealing action, is also accessible to 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.According to the invention, this is achieved in that the cover plate arranged at the blade end has four throttling points against the housing, the throttling 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 through 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. 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 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 plan view of the blade ends of the second row.
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 which is customary 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 vortex 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
- 1212
- 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)
dadurch gekennzeichnet,
dass die am Schaufelende angeordnete Deckplatte (11) vier Drosselstellen gegen das Gehäuse aufweist, wobei die eintrittseitige Drosselstelle im stationären Betriebszustand einen Diagonalspalt (19) bildet.Device for sealing the gap between the rotor blades and the housing (2) of a turbomachine which is designed with a conical contour (28), the rotor blades (6) being provided with circumferential cover plates (11) which have teeth (12, 13, 14, 15 ) seal against the housing to form radial gaps (16, 17, 18),
characterized,
that the cover plate (11) arranged at the blade end has four throttle points against the housing, the inlet-side throttle point forming a diagonal gap (19) in the stationary operating state.
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 true EP0536575A1 (en) | 1993-04-14 |
| EP0536575B1 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) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0903468A1 (en) * | 1997-09-19 | 1999-03-24 | Asea Brown Boveri AG | Shroud for an axial turbine |
| EP1267042A2 (en) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
| WO2009138057A2 (en) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Shroud for rotating blades of a turbo machine, and turbo machine |
| EP2551460A1 (en) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Blade group |
| CN103184900A (en) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | Stage of a gas turbine engine and corresponding method of retrofitting |
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- 1992-09-28 US US07/951,839 patent/US5290144A/en not_active Expired - Lifetime
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- 1992-10-07 JP JP26836992A patent/JP3307692B2/en not_active Expired - Lifetime
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| FR2264964A1 (en) * | 1974-03-21 | 1975-10-17 | Maschf Augsburg Nuernberg Ag | Method for raising the dynamic power limit of turbines and compressors and means for its implementation |
| FR2406074A1 (en) * | 1977-10-11 | 1979-05-11 | Snecma | SAFETY DEVICE FOR AXIAL ROTATING MACHINE |
| EP0194957A2 (en) * | 1985-03-11 | 1986-09-17 | United Technologies Corporation | Compressor blade tip seal |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0903468A1 (en) * | 1997-09-19 | 1999-03-24 | Asea Brown Boveri AG | Shroud for an axial turbine |
| US6102655A (en) * | 1997-09-19 | 2000-08-15 | Asea Brown Boveri Ag | Shroud band for an axial-flow turbine |
| EP1267042A2 (en) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
| EP1267042A3 (en) * | 2001-06-14 | 2009-06-17 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
| EP2280149A1 (en) * | 2001-06-14 | 2011-02-02 | Mitsubishi Heavy Industries, Ltd. | Shroud integral type moving blade and split ring of gas turbine |
| WO2009138057A2 (en) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Shroud for rotating blades of a turbo machine, and turbo machine |
| WO2009138057A3 (en) * | 2008-05-13 | 2010-08-26 | Mtu Aero Engines Gmbh | Shroud for rotating blades of a turbo machine |
| EP2551460A1 (en) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Blade group |
| CN103184900A (en) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | Stage of a gas turbine engine and corresponding method of retrofitting |
| CN103184900B (en) * | 2012-01-03 | 2017-10-24 | 通用电气公司 | For turbine shroud to the cellular seal of front step |
| EP3399152A3 (en) * | 2017-05-01 | 2018-11-14 | General Electric Company | Turbine nozzle-to-shroud interface |
| KR20200126773A (en) * | 2019-04-30 | 2020-11-09 | 두산중공업 주식회사 | Sealing module of turbine and gas turbine having the same |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH05195988A (en) | 1993-08-06 |
| PL296074A1 (en) | 1993-05-17 |
| JP3307692B2 (en) | 2002-07-24 |
| DE59201833D1 (en) | 1995-05-11 |
| EP0536575B1 (en) | 1995-04-05 |
| US5290144A (en) | 1994-03-01 |
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