EP0903468A1 - Shroud for an axial turbine - Google Patents

Shroud for an axial turbine Download PDF

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Publication number
EP0903468A1
EP0903468A1 EP97810686A EP97810686A EP0903468A1 EP 0903468 A1 EP0903468 A1 EP 0903468A1 EP 97810686 A EP97810686 A EP 97810686A EP 97810686 A EP97810686 A EP 97810686A EP 0903468 A1 EP0903468 A1 EP 0903468A1
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EP
European Patent Office
Prior art keywords
stator
cover plate
labyrinth
cavity
flow
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
Application number
EP97810686A
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German (de)
French (fr)
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EP0903468B1 (en
Inventor
Franz Kreitmeier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Alstom SA
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to DE59710621T priority Critical patent/DE59710621D1/en
Priority to EP97810686A priority patent/EP0903468B1/en
Priority to US09/153,270 priority patent/US6102655A/en
Priority to JP26168598A priority patent/JP4199855B2/en
Priority to CN98119296.3A priority patent/CN1294341C/en
Publication of EP0903468A1 publication Critical patent/EP0903468A1/en
Application granted granted Critical
Publication of EP0903468B1 publication Critical patent/EP0903468B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • the invention relates to a device for sealing the gap between the Blades and the conical contoured housing one Turbo machine, the blades being provided with circumferential cover plates are, which form radial gaps against the one provided with sealing strips Seal housing.
  • Such devices are known. They make a smooth or stepped Half-labyrinth with pure radial gaps. Such a seal is later on in the descriptive Fig. 2 shown.
  • the invention seeks to remedy this. It is based on the task Buckets of the type mentioned with a new shroud geometry To create a seal, which at the fulfillment of all boundary conditions to one leads to better efficiency.
  • an embodiment of the invention is based on the penultimate Stage of an axially flow-through condensation steam turbine is shown.
  • FIG. 1 are the middle three, each from a leading row Le and a running row
  • the existing stages of low-pressure blading are shown.
  • the Level Le3 / La3 corresponds to the penultimate level.
  • the one with her feet 21 in Rotations of the rotor 9 used blades La are at their Blade ends provided with cover plates 16.
  • the radially outer contours of the Depending on the row, cover plates are geometrically differently graded.
  • Under Formation of labyrinths 15 seal with their steps against sealing strips, which are arranged in a suitable manner in the stator 9.
  • the one with her feet 13 in Turnings of the stator 8 inserted guide blades Le are on their Provide blade ends with cover plates 20. Forming labyrinths 19 they also seal against sealing strips which are arranged in the rotor 9 in a suitable manner are.
  • the flow through channel 50 has the conically extending as the starting position outer contour 51 on the stator and the cylindrical inner contour 11 on the rotor. However, neither is mandatory. Regardless of the actual course in any case, the walls become the outer flow-restricting one Contour 10 in the area of the airfoil through the channel facing Cover plate 16 of the blades La formed.
  • Axial gaps 26, which represent the labyrinth outlets 42 are Usually will the column on the other hand limited by stator parts, which the Take over flow guidance in the non-bladed levels.
  • Fig. 2 is the cover plate seal of the row La3, as the beginning corresponds to the prior art mentioned. It essentially exists from the cover plate 16A, which extends over the entire blade width and with their outer diameter and the four caulked in the stator 8A Sealing strip 17A forms a half-labyrinth with pure radial gaps. Is recognizable the spacious labyrinth inlet 40A and the unfavorably designed labyrinth outlet 42A. With 54 the channel wall is designated when it is in a tap flows.
  • both the geometry of the shroud and its embedding in the stator improved in three ways.
  • the radial cavity at the labyrinth entrance is in its radial Extension divided into two axially offset cavities. i.e. in the Example designed zigzag.
  • the contour of the recess runs in the stator first inwards, then outwards in the axial direction Formation of a prong 41 protruding into the cavity Cover plate 16 configured.
  • It is provided with an understitch 43, which is adapted to the point shape.
  • the axial part of the backstitch is in its diameter so that on the occasion of assembly and Do not touch the cover plate and stator during the operating transients.
  • a Comparison with FIG. 2 shows that in the operating position there is a much smaller one Passage gap 18 between stator and cover plate. The gap mass flow will therefore be significantly reduced with the new measure.
  • a third measure serves to improve the re-inflow of the Maze mass flow in the main channel.
  • the cavity at the labyrinth exit 42 reduced to a permissible minimum dimension in the radial direction Crevice flow is immediately followed by a conical after the general outside stator wall bent. This can be the harmful Cross exchange of flow material significantly reduce and unnecessary Avoid dissipation of the high-energy gap flow as much as possible.
  • the total pressure profile of the Main flow favorably influenced.
  • the flow-limiting wall of the channel 50 is directly on Provide an outlet angle A at the blades La3.
  • This kink angle is dimensioned so that the outflow from the blades with respect to Total pressure and outflow angle is homogenized.
  • the kinked part of the wall runs radially outwards, i.e. it is from the machine axis, not shown directed away.
  • the choice of the articulation angle is based on the following considerations: At the outlet the blades have a divergent flow, with co-rotation on the cylinder. At least the flow in the radially outer zone has an essential higher energy than in the radially inner rotor zone, which is in the form of manifested significantly higher total pressures in the radially outer zone.
  • the idea behind the kink angle is now to have the lowest possible total pressure and outflow angle inhomogeneity to achieve above the bucket height. The equation for that radial balance teaches that this is primarily about the meridian curvature the streamlines can be reached. This has to be influenced primarily by adjusting the articulation angle. A homogeneous total pressure distribution the outer boundary wall can only be achieved if the corresponding one Kink angle A with respect to the conical contour of the channel in each Fall opens to the outside. Here, the desired total pressure reduction in achieved in this area.
  • the wall expediently becomes at least approximately further downstream in the entrance area of the guide vanes of the following stage, not shown a bend angle B directed radially inwards.
  • the wall with this bend angle B in the foot area of the downstream guide vane then runs again at the counter kink angle radially inwards so that the resulting flow restricting wall, which between the guide blade root and the following blade cover plate is interrupted by the axial gap 18, at least approximately in the plane of the Blade entry of this subsequent stage has a common point P with that Original straight channel contour.
  • FIG. 3 illustrates by means of that wall which is located upstream of the cavity and which and possibly the flow-restricting part of the previous one Guide blade root can be.
  • the counter-kink angle on the upstream wall increases the negative pressure or lowers the plus pressure over the downstream labyrinth, resulting in a leads to a further reduction in the gap mass flow.
  • FIG. 3 shows a solution in which the shroud has the same taper of approx. Has 25 ° as that in Fig. 2 and 3.
  • the cavity at the entrance to the labyrinth is in its radial extent in three axially offset cavities 40a, 40b and 40c divided.
  • three are caulked into the stator Sealing strip 17 arranged.
  • the main channel is the cavity at the labyrinth outlet 42 immediately behind the last sealing strip in the radial direction to an admissible minimum dimension reduced.
  • this minimum dimension is also in the front cavities intended.
  • the cover plate 16 is step-shaped. With in her the first section approximately horizontally and then curved Sealing strips 52 are used to seal the individual cavities. These sealing strips 52 are preferably with their horizontally extending section in the axially extending Housing parts caulked. It goes without saying that others Fastening methods and geometries are possible.
  • Fig. 4 shows the cover plate in the normal operating position.
  • the front Sealing strips 52 act on the front edges of the horizontally directed cover plate gradations.
  • the rear sealing strips 17 act horizontally on the last one directional cover plate gradation.
  • the cover plate is in its extreme positions on a somewhat reduced scale shown, namely in the case of transients such as those when starting and leaving of the machine. It can be seen that in the dash-dotted position the sealing strips 52 in the intersection between axially and radially directed Intervene in the step part. One of the ways to make this easier is the radial one Step part formed obliquely against the flow direction. In addition, the Curvature of the sealing strips a problem-free evasion in the event that the Cover plate would take an even more extreme position. In this position continues to seal the foremost of the sealing strips 17 against the horizontally directed rear cover plate part. The sealing strips are in the dashed position 52 no longer engaged. Here only the last of the sealing strips 17 and thus prevents working fluid from flowing uncontrolled through the gap 42.
  • Fig. 6 shows the new solution for a cover plate with a taper of only approx. 10 ° as used in the front stages of low pressure parts Steam turbines.
  • the cavity here is divided into two partial cavities 40a and 40c. These partial cavities are separated by one in its first section sealing strip 52 which runs approximately horizontally and is then curved. This strip acts on a simply stepped cover plate 16.
  • the rest Sealing strips 17 are arranged in such a way that at least one, even in extreme situations strip 52 or 17 is effective.
  • FIG. 7 finally shows the new solution for a cover plate with a taper of approximately 45 °, as used in the rear low pressure stages of Steam turbines. It can be seen here that even with such extreme channel openings the solution of FIG. 4 is easily transferable. It also offers Solution the advantage that the above described radially inward and aerodynamically damaging bend angles B at the inlet avoided can be. This means that the cover band contour corresponds to the globally specified one Channel contour.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Shroud plates (16) on the rotor blade ends (La3) project into cavities in the stator. At the labyrinth entry (40), the cavity is divided radially into two or more axially offset part cavities. The shroud plate is stepped, and has at least two throttle points against the stator. Horizontal curved sealing strips (17) on the stator enclose eddy chambers and each act on a shroud plate step. The radial outward facing surfaces of the shroud are angled against the flow direction.

Description

Technisches GebietTechnical field

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 unter Bildung von Radialspalten gegen das mit Dichtstreifen versehene Gehäuse dichten.The invention relates to a device for sealing the gap between the Blades and the conical contoured housing one Turbo machine, the blades being provided with circumferential cover plates are, which form radial gaps against the one provided with sealing strips Seal housing.

Stand der TechnikState of the art

Derartige Vorrichtungen sind bekannt. Sie bilden ein glattes oder ein gestuftes Halb-Labyrinth mit reinen Radialspalten. Eine solche Dichtung ist in der später zu beschreibenden Fig. 2 dargestellt.Such devices are known. They make a smooth or stepped Half-labyrinth with pure radial gaps. Such a seal is later on in the descriptive Fig. 2 shown.

Infolge des besseren Wirkungsgrades und der grösseren Zuverlässigkeit wird diese Art von Spaltdichtung inzwischen auch bereits bei den Laufschaufeln der vorletzen Stufe von Kondensationsdampfturbinen angewendet. Die mechanischen Anforderungen sind hier mit Umfangsgeschwindigkeiten von 450 m/sec recht hoch, während die thermischen Bedingungen mit ca. 90°C bescheiden sind. Problematisch sind die geometrischen Anforderungen. Einerseits wegen der starken Konizität, die zu tiefen Kavitäten der bekannten Dichtvorrichtung in der Gehäusewand führt; andererseits wegen der grossen Differenzdehnungen zwischen Rotor und Gehäuse, die zu breiten Kavitäten mit den oben genannten Halb-Labyrinthen führt.

  • Die dabei gebildete grosse Kavität im Eintrittsbereich der Dichtung bewirkt einen ungünstigen Queraustausch von Strömungsmaterial mit der Hauptströmung im Schaufelkanal. Dieser Queraustausch ist begünstigt durch die in der Ebene der Schaufelvorderkante ausserordentlich grosse Schwankung der Druckdifferenz zwischen zwei benachbarten Schaufeln. Ausserdem wird in diesem Bereich durch die Hauptströmung und die Seitenwand des Deckbandes ein starker Wirbel angetrieben.
  • Wenig wirksam ist das Halb-Labyrinth mit den Dichtstreifen, mit denen das Gehäuse versehen ist und die gegen das umlaufende Deckband dichten. Dies, weil bei den vorliegenden Verhältnissen das Betriebsspiel eine Grösse von ca. 1/3 der freien Kammerhöhe aufweisen muss. Auch mehrere Dichtstreifen sind deshalb nicht wesentlich effektiver als ein einziger.
  • Schliesslich erlaubt auch die grosse Kavität im Austrittsbereich der Dichtung einen unerwünschten Queraustausch mit der Hauptströmung im Schaufelkanal, da auch hier die Druckdifferenz zwischen zwei benachbarten Schaufelspitzen grossen Schwankungen unterliegt. Zudem geht in diesem Bereich die Führung der Hauptströmung vollständig verloren.
  • Von Nachteil ist ausserdem bei diesen Dichtungen der hinter den aussen liegenden Dichtstreifen gebildete grosse Wirbelraum, welcher eine grosse Dissipation der austrittsseitigen Spaltströmung bewirkt.
As a result of better efficiency and greater reliability, this type of gap seal is already being used in the blades of the penultimate stage of condensation steam turbines. The mechanical requirements are quite high here with peripheral speeds of 450 m / sec, while the thermal conditions are modest at around 90 ° C. The geometric requirements are problematic. On the one hand because of the strong conicity, which leads to deep cavities of the known sealing device in the housing wall; on the other hand because of the large differential expansion between the rotor and the housing, which leads to wide cavities with the above-mentioned half-labyrinths.
  • The large cavity formed in the inlet area of the seal causes an unfavorable cross exchange of flow material with the main flow in the blade channel. This cross exchange is favored by the extraordinarily large fluctuation in the pressure difference between two adjacent blades in the plane of the blade leading edge. In addition, a strong vortex is driven in this area by the main flow and the side wall of the shroud.
  • The semi-labyrinth with the sealing strips with which the housing is provided and which seal against the circumferential cover band is not very effective. This is because, given the prevailing conditions, the operating clearance must be around 1/3 of the free chamber height. This means that several sealing strips are not much more effective than one.
  • Finally, the large cavity in the outlet area of the seal also permits undesired cross-exchange with the main flow in the blade channel, since here too the pressure difference between two adjacent blade tips is subject to large fluctuations. In addition, the guidance of the main flow is completely lost in this area.
  • Another disadvantage of these seals is the large swirl space formed behind the outer sealing strips, which causes a large dissipation of the gap-side flow on the outlet side.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Ihr liegt die Aufgabe zugrunde, bei Schaufeln der eingangs genannten Art mit einer neuen Deckbandgeometrie eine Dichtung zu schaffen, welche bei Erfüllung aller Randbedingungen zu einem besseren Wirkungsgrad führt. The invention seeks to remedy this. It is based on the task Buckets of the type mentioned with a new shroud geometry To create a seal, which at the fulfillment of all boundary conditions to one leads to better efficiency.

Erfindungsgemäss wird dies mit den kennzeichnenden Merkmalen des Patentanspruchs 1 erreicht.According to the invention, this is done with the characterizing features of the patent claim 1 reached.

Der Vorteil der Erfindung ist unter anderem darin zu sehen, dass bei der neuen Dichtung nur kleine Spaltmengen auftreten. 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 the new Seal only small amounts of gap occur. In addition, a good introduction of the Crevice flow reached in the main flow.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand der vorletzten Stufe einer axialdurchströmten Kondensationsdampfturbine dargestellt.In the drawing, an embodiment of the invention is based on the penultimate Stage of an axially flow-through condensation steam turbine is shown.

Es zeigen:

Fig. 1
; einen Teillängsschnitt einer Niederdruck-Dampfturbine mit Deckplattendichtung;
Fig. 2
einen Teillängsschnitt der Laufschaufelspitze der vorletzten Stufe mit Deckplattendichtung gemäss Stand der Technik;
Fig. 3
einen Teillängsschnitt der Laufschaufelspitze der vorletzten Stufe mit Deckplattendichtung gemäss Erfindung;
Fig. 4 und 5
einen Teillängsschnitt der Laufschaufelspitze der vorletzten Stufe mit einer Deckplatten-Ausführungsvariante;
Fig. 6
einen Teillängsschnitt der Laufschaufelspitze einer Stufe mit schwacher Konizität mit einer Deckplatten-Ausführungsvariante;
Fig. 7
einen Teillängsschnitt der Laufschaufelspitze einer Stufe mit starker Konizität mit einer Deckplatten-Ausführungsvariante.
Show it:
Fig. 1
; a partial longitudinal section of a low-pressure steam turbine with cover plate seal;
Fig. 2
a partial longitudinal section of the blade tip of the penultimate stage with cover plate seal according to the prior art;
Fig. 3
a partial longitudinal section of the blade tip of the penultimate stage with cover plate seal according to the invention;
4 and 5
a partial longitudinal section of the blade tip of the penultimate stage with a cover plate embodiment;
Fig. 6
a partial longitudinal section of the blade tip of a stage with weak taper with a cover plate embodiment;
Fig. 7
a partial longitudinal section of the blade tip of a step with strong taper with a cover plate design variant.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung des Arbeitsmittels ist mit Pfeilen bezeichnet. They are only the elements essential for understanding the invention shown. The direction of flow of the working fluid is indicated by arrows.

Weg zur Ausführung der ErfindungWay of carrying out the invention

Gemäss Figur. 1 sind die mittleren drei, aus je einer Leitreihe Le und einer Laufreihe La bestehenden Stufen einer Niederdruckbeschaufelung dargestellt. Die Stufe Le3/La3 entspricht dabei der vorletzten Stufe. Die mit ihren Füssen 21 in Eindrehungen des Rotors 9 eingesetzten Laufschaufeln La sind an ihren Schaufelenden mit Deckplatten 16 versehen. Die radial äusseren Konturen der Deckplatten sind je nach Laufreihe geometrisch unterschiedlich gestuft. Unter Bildung von Labyrinthen 15 dichten sie mit ihren Stufen gegen Dichtstreifen, welche im Stator 9 auf geeignete Art angeordnet sind. Die mit ihren Füssen 13 in Eindrehungen des Stators 8 eingesetzten Leitschaufeln Le sind an ihren Schaufelenden mit Deckplatten 20 versehen. Unter Bildung von Labyrinthen 19 dichten auch sie gegen Dichtstreifen, welche im Rotor 9 auf geeignete Art angeordnet sind.According to the figure. 1 are the middle three, each from a leading row Le and a running row The existing stages of low-pressure blading are shown. The Level Le3 / La3 corresponds to the penultimate level. The one with her feet 21 in Rotations of the rotor 9 used blades La are at their Blade ends provided with cover plates 16. The radially outer contours of the Depending on the row, cover plates are geometrically differently graded. Under Formation of labyrinths 15 seal with their steps against sealing strips, which are arranged in a suitable manner in the stator 9. The one with her feet 13 in Turnings of the stator 8 inserted guide blades Le are on their Provide blade ends with cover plates 20. Forming labyrinths 19 they also seal against sealing strips which are arranged in the rotor 9 in a suitable manner are.

Der durchströmte Kanal 50 hat als Ausgangslage die konisch verlaufende äussere Kontur 51 am Stator und die zylindrisch verlaufende innere Kontur 11 am Rotor. Beides ist indes nicht zwingend. Unabhängig vom tatsächlichen Verlauf der Wandungen wird in jedem Fall die äussere strömungsbegrenzende Kontur 10 im Bereich des Laufschaufelblattes durch die dem Kanal zugekehrte Deckplatte 16 der Laufschaufeln La gebildet. Unmittelbar stromaufwärts der Deckplatten 16, 20 befinden sich Axialspalte 18, welche die Labyrinth-Eintritte 40 darstellen. Unmittelbar stromabwärts dieser Deckplatten 16, 20 befinden sich Axialspalte 26,welche die Labyrinth-Austritte 42 darstellen. In der Regel werden die genannten Spalte anderseits begrenzt durch Statorteile, welche die Strömungsführung in den nichtbeschaufelten Ebenen übernehmen.The flow through channel 50 has the conically extending as the starting position outer contour 51 on the stator and the cylindrical inner contour 11 on the rotor. However, neither is mandatory. Regardless of the actual course in any case, the walls become the outer flow-restricting one Contour 10 in the area of the airfoil through the channel facing Cover plate 16 of the blades La formed. Immediately upstream of the Cover plates 16, 20 are axial gaps 18, which are the labyrinth entrances 40 represent. Immediately downstream of these cover plates 16, 20 are Axial gaps 26, which represent the labyrinth outlets 42. Usually will the column on the other hand limited by stator parts, which the Take over flow guidance in the non-bladed levels.

In Fig. 2 ist die Deckplattendichtung der Laufreihe La3, wie sie dem eingangs erwähnten Stand der Technik entspricht, gezeigt. Sie besteht im wesentlichen aus der Deckplatte 16A, die sich über die ganze Schaufelbreite erstreckt und mit ihrem äusseren Durchmesser und den vier im Stator 8A eingestemmten Dichtstreifen 17A ein Halblabyrinth mit reinen Radialspalten bildet. Erkennbar ist der grossräumige Labyrinth-Eintritt 40A und der ungünstig gestaltete Labyrinth-Austritt 42A. Mit 54 ist die Kanalwand bezeichnet, wenn sie in eine Anzapfung mündet.In Fig. 2 is the cover plate seal of the row La3, as the beginning corresponds to the prior art mentioned. It essentially exists from the cover plate 16A, which extends over the entire blade width and with their outer diameter and the four caulked in the stator 8A Sealing strip 17A forms a half-labyrinth with pure radial gaps. Is recognizable the spacious labyrinth inlet 40A and the unfavorably designed labyrinth outlet 42A. With 54 the channel wall is designated when it is in a tap flows.

Wie in Fig. 3 gezeigt, wird nunmehr gemäss der Erfindung sowohl die Geometrie des Deckbandes als auch dessen Einbettung im Stator in dreifacher Weise verbessert.As shown in Fig. 3, according to the invention, both the geometry of the shroud and its embedding in the stator improved in three ways.

Um den Queraustausch von Strömungsmaterial und die Wirbelintensität zu reduzieren, wird die radial gerichtete Kavität am Labyrinth-Eintritt in ihrer radialer Erstreckung in zwei, axial gegeneinander versetzte Kavitäten unterteilt . d.h. im Beispielsfall zickzackförmig gestaltet. Hierzu verläuft die Kontur der Eindrehung im Stator zunächst materialeinwärts, danach in Axialrichtung auswärts unter Bildung eines in die Kavität hineinragenden Zackens 41. Entsprechend wird die Deckplatte 16 konfiguriert. Sie wird mit einem Hinterstich 43 versehen, welcher der Zackenform angepasst ist. Der axial verlaufende Teil des Hinterstiches ist in seinem Durchmesser so bemessen, dass sich anlässlich der Montage und während der Betriebstransienten Deckplatte und Stator nicht berühren. Ein Vergleich mit Fig. 2 zeigt, dass sich in der Betriebsstellung ein wesentlich kleinerer Durchlass-Spalt 18 zwischen Stator und Deckplatte einstellt. Der Spaltmassenstrom wird demnach mit der neuen Massnahme beträchtlich abgesenkt.To the cross exchange of flow material and the vortex intensity too reduce, the radial cavity at the labyrinth entrance is in its radial Extension divided into two axially offset cavities. i.e. in the Example designed zigzag. For this, the contour of the recess runs in the stator first inwards, then outwards in the axial direction Formation of a prong 41 protruding into the cavity Cover plate 16 configured. It is provided with an understitch 43, which is adapted to the point shape. The axial part of the backstitch is in its diameter so that on the occasion of assembly and Do not touch the cover plate and stator during the operating transients. A Comparison with FIG. 2 shows that in the operating position there is a much smaller one Passage gap 18 between stator and cover plate. The gap mass flow will therefore be significantly reduced with the new measure.

Weiter wird das bekannte Halb-Labyrinth durch ein Voll-Labyrinth ersetzt. Hierzu ist der äussere Durchmesser der Deckplatte gestuft und mit nur zwei Drosselstellen versehen. Zwei in den Stator eingestemmte Dichtstreifen 17, die jeweils auf eine Stufe wirken, begrenzen eine gut funktionierende Wirbelkammer 22. Durch die radiale Versetzung der Drosselstellen beeinflussen diese sich nicht gegenseitig. Mit diesem Vollabyrinth wird eine weitere Reduzierung des Spaltmassenstromes erzielt.Furthermore, the well-known half-labyrinth is replaced by a full-labyrinth. For this the outer diameter of the cover plate is stepped and with only two throttling points Mistake. Two sealing strips 17 caulked into the stator, each on a step, limit a well-functioning vortex chamber 22. By the radial displacement of the throttle points does not influence each other. With this full labyrinth a further reduction of the gap mass flow becomes achieved.

Eine dritte Massnahme dient der Verbesserung der Wiedereinströmung des Labyrinthmassenstromes in den Hauptkanal. Hierzu wird die Kavität am Labyrinth-Austritt 42 in radialer Richtung auf ein zulässiges Mindestmass reduziert.Die Spaltströmung wird sofort durch eine gegenüber der allgemeinen Konizität nach aussen abgeknickte Statorwand übernommen. Damit lässt sich der schädliche Queraustausch von Strömungsmaterial wesentlich reduzieren und die unnötige Dissipation der hochenergetischen Spaltströmung weitgehend vermeiden. Darüberhinaus wird durch die abgeknickte Statorwand das Totaldruck-Profil der Hauptströmung günstig beeinflusst.A third measure serves to improve the re-inflow of the Maze mass flow in the main channel. For this purpose, the cavity at the labyrinth exit 42 reduced to a permissible minimum dimension in the radial direction Crevice flow is immediately followed by a conical after the general outside stator wall bent. This can be the harmful Cross exchange of flow material significantly reduce and unnecessary Avoid dissipation of the high-energy gap flow as much as possible. In addition, the total pressure profile of the Main flow favorably influenced.

Hierfür wird die strömungsbegrenzende Wand des Kanals 50 unmittelbar am Austritt der Laufschaufeln La3 mit einem Knickwinkel A versehen. Dieser Knickwinkel ist so bemessen, dass die Abströmung aus den Laufschaufeln bezüglich Totaldruck und Abströmwinkel homogenisiert wird. Im Beispielsfall bedeutet dies, dass der gezeigte Winkel A als positiv definiert wird. Der abgeknickte Wandteil verläuft radial nach aussen, d.h. er ist von der nicht gezeigten Maschinenachse weggerichtet. Mit dieser Ausbildung wird der durch das teilungsabhängige Druckfeld induzierte Queraustausch von Strömungsmaterial reduziert. Dieser kann nämlich die Ursache sein von Ablösung an der besonders empfindlichen Saugseite der Schaufeln.For this purpose, the flow-limiting wall of the channel 50 is directly on Provide an outlet angle A at the blades La3. This kink angle is dimensioned so that the outflow from the blades with respect to Total pressure and outflow angle is homogenized. In the example, this means that the angle A shown is defined as positive. The kinked part of the wall runs radially outwards, i.e. it is from the machine axis, not shown directed away. With this training, the division-dependent pressure field induced cross exchange of flow material reduced. This can namely the cause of detachment on the particularly sensitive suction side the shovels.

Der Wahl des Knickwinkels liegen folgende Überlegungen zugrunde: Am Austritt der Laufschaufeln liegt eine divergente Strömung vor, mit Mitdrall am Zylinder. Zumindest weist die Strömung in der radial äusseren Zone eine wesentlich höhere Energie auf als in der radial inneren Rotorzone, was sich in Form von wesentlich höheren Totaldrücken in der radial äusseren Zone manifestiert. Mit der Knickwinkel-Idee gilt es nun, eine möglichst geringe Totaldruck-und Abströmwinkel-Inhomogenität über der Schaufelhöhe zu erzielen. Die Gleichung für das radiale Gleichgewicht lehrt, dass dies in erster Linie über die Meridiankrümmung der Stromlinien errreicht werden kann. Diese muss also primär beeinflusst werden durch Anpassung des Knickwinkels. Eine homogene Totaldruckverteilung an der äusseren Begrenzungswand lässt sich nur dann erzielen, wenn der entsprechende Knickwinkel A gegenüber der konischen Kontur des Kanals in jedem Fall nach aussen öffnet. Hierbei wird die gewünschte Totaldruckerniedrigung in diesem Bereich erzielt.The choice of the articulation angle is based on the following considerations: At the outlet the blades have a divergent flow, with co-rotation on the cylinder. At least the flow in the radially outer zone has an essential higher energy than in the radially inner rotor zone, which is in the form of manifested significantly higher total pressures in the radially outer zone. With The idea behind the kink angle is now to have the lowest possible total pressure and outflow angle inhomogeneity to achieve above the bucket height. The equation for that radial balance teaches that this is primarily about the meridian curvature the streamlines can be reached. This has to be influenced primarily by adjusting the articulation angle. A homogeneous total pressure distribution the outer boundary wall can only be achieved if the corresponding one Kink angle A with respect to the conical contour of the channel in each Fall opens to the outside. Here, the desired total pressure reduction in achieved in this area.

Eine vollständige Umsetzung dieser Knickwinkel-Idee setzt eine saubere Führung der Strömung über einen gewissen Bereich voraus. Dies erfolgt aus der Erkenntnis, dass sich erst in einer Distanz - welche dem halben Abstand zwischen Laufschaufelaustritt und Leitschaufeleintritt geteilt durch die Schaufelteilung entspricht - langsam die von der Schaufelzirkulation herrührenden Strömungsinhomogenitäten verlieren.A complete implementation of this articulation angle idea requires a clean guide ahead of the flow over a certain range. This is done from the Realization that there is only a distance - which is half the distance between the blade outlet and the guide blade inlet divided by the blade pitch corresponds - slowly to those resulting from the blade circulation Lose flow inhomogeneities.

Zweckmässigerweise wird die Wand weiter stromabwärts zumindest annähernd im Eintrittsbereich der Leitschaufeln der nicht dargestellten folgenden Stufe mit einem radial einwärts gerichteten Knickwinkel B versehen.The wall expediently becomes at least approximately further downstream in the entrance area of the guide vanes of the following stage, not shown a bend angle B directed radially inwards.

Die mit diesem Knickwinkel B versehene Wand im Fussbereich der stromabwärts gelegenen Leitschaufel verläuft anschliessend an den Gegenknickwinkel wieder radial einwärts, so dass die resultierende strömungsbegrenzende Wandung, welche zwischen Leitschaufelfuss und darauffolgender Laufschaufeldeckplatte durch den Axialspalt 18 unterbrochen ist, zumindest annähernd in der Ebene des Laufschaufel-Eintritts dieser folgenden Stufe einen gemeinsamen Punkt P mit der urprünglichen geraden Kanalkontur aufweist. Dieser Sachverhalt ist in Fig. 3 anhand jener Wand illustriert, welche sich stromaufwärts der Kavität befindet und welche und u.U. die strömungsbegrenzende Partie des vorangelegenen Leitschaufelfusses sein kann.The wall with this bend angle B in the foot area of the downstream guide vane then runs again at the counter kink angle radially inwards so that the resulting flow restricting wall, which between the guide blade root and the following blade cover plate is interrupted by the axial gap 18, at least approximately in the plane of the Blade entry of this subsequent stage has a common point P with that Original straight channel contour. This is shown in FIG. 3 illustrated by means of that wall which is located upstream of the cavity and which and possibly the flow-restricting part of the previous one Guide blade root can be.

Der Gegenknickwinkel an der stromaufwärtigen Wand steigt den Minusdruck bzw. senkt den Plusdruck über dem stromabwärtigen Labyrinth, was zu einer weiteren Senkung des Spaltmassenstromes führt.The counter-kink angle on the upstream wall increases the negative pressure or lowers the plus pressure over the downstream labyrinth, resulting in a leads to a further reduction in the gap mass flow.

Bei den nachstehend erläuterten Ausführungsbeispielen sind die funktionsgleichen Elemente mit den selben Bezugszeichen versehen wie in Fig. 3. Fig. 4 zeigt eine Lösung, bei welcher das Deckband die gleiche Konizität von ca. 25° aufweist wie jenes in Fig. 2 und 3. Die Kavität am Labyrinth-Eintritt ist in ihrer radialer Erstreckung in drei axial gegeneinander versetzte Kavitäten 40a, 40b und 40c unterteilt. Am Labyrinth-Austritt sind drei in den Stator eingestemmte Dichtstreifen 17 angeordnet.In the exemplary embodiments explained below, the functions are the same Provide elements with the same reference numerals as in FIG. 3. 4 shows a solution in which the shroud has the same taper of approx. Has 25 ° as that in Fig. 2 and 3. The cavity at the entrance to the labyrinth is in its radial extent in three axially offset cavities 40a, 40b and 40c divided. At the labyrinth exit, three are caulked into the stator Sealing strip 17 arranged.

Zur Verbesserung der Wiedereinströmung des Labyrinthmassenstromes in den Hauptkanal ist auch hier die Kavität am Labyrinth-Austritt 42 unmittelbar hinter dem letzten Dichtstreifen in radialer Richtung auf ein zulässiges Mindestmass reduziert. In der Regel wird dieses Mindestmass auch in den vorderen Kavitäten vorgesehen. Hierzu ist die Deckplatte 16 stufenförmig ausgebildet. Mit in ihrem ersten Abschnitt annähernd horizontal verlaufenden und danach abgekrümmten Dichtstreifen 52 werden die einzelnen Kavitäten gedichtet. Diese Dichtstreifen 52 sind vorzugsweise mit ihrem horizontal verlaufenden Abschnitt in den axial verlaufenden Gehäuseteilen eingestemmt. Es versteht sich, dass auch andere Befestigungsmethoden und Geometrien möglich sind.To improve the re-inflow of the labyrinth mass flow into the Here too, the main channel is the cavity at the labyrinth outlet 42 immediately behind the last sealing strip in the radial direction to an admissible minimum dimension reduced. As a rule, this minimum dimension is also in the front cavities intended. For this purpose, the cover plate 16 is step-shaped. With in her the first section approximately horizontally and then curved Sealing strips 52 are used to seal the individual cavities. These sealing strips 52 are preferably with their horizontally extending section in the axially extending Housing parts caulked. It goes without saying that others Fastening methods and geometries are possible.

Fig. 4 zeigt die Deckplatte in der normalen Betriebsposition. Die vorderen Dichtstreifen 52 wirken auf die Vorderkanten der horizontal gerichteten Deckplattenabstufungen. Die hinteren Dichtstreifen 17 wirken auf die letzte horizontal gerichtete Deckplattenabstufung.Fig. 4 shows the cover plate in the normal operating position. The front Sealing strips 52 act on the front edges of the horizontally directed cover plate gradations. The rear sealing strips 17 act horizontally on the last one directional cover plate gradation.

In Fig. 5 ist in etwas verkleinertem Masstab die Deckplatte in ihren Extremstellungen gezeigt, nämlich bei Transienten, wie sie beim Anfahren und Abfahren der Maschine vorkommen. Zu erkennen ist, dass in der strichpunktierten Stellung die Dichtstreifen 52 in den Schnittpunkt zwischen axial und radial gerichtetem Stufenteil eingreifen. Unter anderem um dies zu erleichtern, ist der radiale Stufenteil gegen die Strömungsrichtung schräg ausgebildet. Zudem erlaubt die Krümmung der Dichtstreifen ein problemloses Ausweichen für den Fall, dass die Deckplatte eine noch extremere Stellung einnehmen würde. Bei dieser Stellung dichtet weiterhin der vorderste der Dichtstreifen 17 gegen den horizontal gerichteten hinteren Deckplattenteil. In der strichlierten Stellung sind die Dichtstreifen 52 nicht mehr im Eingriff. Hier dichtet nur noch der letzte der Dichtstreifen 17 und verhindert damit, dass unkontrolliert Arbeitsmittel durch den Spalt 42 durchströmt.5, the cover plate is in its extreme positions on a somewhat reduced scale shown, namely in the case of transients such as those when starting and leaving of the machine. It can be seen that in the dash-dotted position the sealing strips 52 in the intersection between axially and radially directed Intervene in the step part. One of the ways to make this easier is the radial one Step part formed obliquely against the flow direction. In addition, the Curvature of the sealing strips a problem-free evasion in the event that the Cover plate would take an even more extreme position. In this position continues to seal the foremost of the sealing strips 17 against the horizontally directed rear cover plate part. The sealing strips are in the dashed position 52 no longer engaged. Here only the last of the sealing strips 17 and thus prevents working fluid from flowing uncontrolled through the gap 42.

Fig. 6 zeigt die neue Lösung bei einer Deckplatte mit einer Konizität von lediglich ca. 10°, wie sie Anwendung findet in Frontstufen von Niederdruckteilen von Dampfturbinen. Die Kavität ist hier in zwei Teilkavitäten 40a und 40c unterteilt. Getrennt werden diese Teilkavitäten durch einen in seinem ersten Abschnitt annähernd horizontal verlaufenden und danach abgekrümmten Dichtstreifen 52. Dieser Streifen wirkt auf eine einfach gestufte Deckplatte 16. Die übrigen Dichtstreifen 17 sind so angeordnet, dass auch in Extremlagen mindesten einer der Streifen 52 oder 17 wirksam ist.Fig. 6 shows the new solution for a cover plate with a taper of only approx. 10 ° as used in the front stages of low pressure parts Steam turbines. The cavity here is divided into two partial cavities 40a and 40c. These partial cavities are separated by one in its first section sealing strip 52 which runs approximately horizontally and is then curved. This strip acts on a simply stepped cover plate 16. The rest Sealing strips 17 are arranged in such a way that at least one, even in extreme situations strip 52 or 17 is effective.

Fig. 7 schliesslich zeigt die neue Lösung bei einer Deckplatte mit einer Konizität von ca. 45°, wie sie Anwendung findet in den hinteren Niederdruckstufen von Dampfturbinen. Hier ist zu erkennen, dass auch bei solchen extremen Kanalöffnungen die Lösung nach Fig. 4 ohne weiteres übertragbar ist. Zudem bietet diese Lösung den Vorteil, dass der oben beschriebene radial einwärts gerichtete und an sich strömungsmechanisch schädliche Knickwinkel B am Eintritt vermieden werden kann. D.h, die Deckbandkontur entspricht hier der global vorgegebenen Kanalkontur.7 finally shows the new solution for a cover plate with a taper of approximately 45 °, as used in the rear low pressure stages of Steam turbines. It can be seen here that even with such extreme channel openings the solution of FIG. 4 is easily transferable. It also offers Solution the advantage that the above described radially inward and aerodynamically damaging bend angles B at the inlet avoided can be. This means that the cover band contour corresponds to the globally specified one Channel contour.

Alle bisher gezeigten und beschriebenen Lösungen weisen gegenüber dem Stand der Technik den Vorteil auf, dass infolge der Abstufung und insbesondere der schräg verlaufenden Radialteile eine wesentlich erhöhte Dichtlänge zur Verfügung steht. Darüberhinaus weisen zumindest die Deckplatten nach den Fig. 4, 6 und 7 auch geringere Deckplattenmassen auf. All the solutions shown and described so far point towards that State of the art has the advantage that due to the gradation and in particular of the inclined radial parts to a significantly increased sealing length Available. In addition, at least the cover plates according to FIGS. 4, 6 and 7 also lower cover plate masses.

BezugszeichenlisteReference list

88th
Statorstator
99
Rotorrotor
1010th
statorseitige strömungsbegrenzende Wandflow limiting wall on the stator side
1111
rotorseitige strömungsbegrenzende Wandflow-limiting wall on the rotor side
1313
Fussplatte der Leitschaufeln LeBase plate of the guide blades Le
1515
Laufschaufel-LabyrinthBlade labyrinth
1616
Deckplatte der Laufschaufel LaCover plate of the blade La
1717th
DichtstreifenSealing strips
1818th
AxialspaltAxial gap
1919th
Leitschaufel-LabyrinthGuide vane labyrinth
2020th
Deckplatte der Leitschaufel LeCover plate of the guide vane Le
2121
Fussplatte der Laufschaufel LaBase plate of the blade La
2222
WirbelkammerVortex chamber
4040
Labyrinth-EintrittMaze entrance
40a, 40b, 40c40a, 40b, 40c
Kavitätcavity
4141
ZackenPink
4242
Labyrinth-AustrittMaze exit
4343
HinterstichBackstitch
5050
durchströmter Kanalflowed channel
5151
äussere Kanalkonturouter channel contour
5252
horizontale Dichtstreifenhorizontal sealing strips
5454
Kanalkontur bei AnzapfungChannel contour when tapping
La, La3 ...La, La3 ...
LaufschaufelnBlades
Le, Le3 ...Be, Be3 ...
LeitschaufelnGuide vanes
AA
Knickwinkel aussen hinter LaufradBuckling angle outside behind the impeller
BB
Knickwinkel aussen vor LaufradKink angle outside in front of the impeller
PP
Intersektion mit gerader äusserer KanalkonturIntersection with a straight outer channel contour

Claims (7)

Vorrichtung zum Dichten des Spaltes zwischen den Laufschaufeln und dem mit konischer Kontur (51) ausgebilde§ten Stator (8) einer Turbomaschine, wobei die Laufschaufeln (La3) am Schaufelende mit umlaufenden Deckplatten (16) versehen sind, welche in eine Kavität im Stator hineinragen und unter Bildung von Radialspalten gegen den mit Dichtstreifen (17) versehenen Stator dichten,
dadurch gekennzeichnet,
dass die Kavität am Labyrinth-Eintritt (40) in ihrer radialer Erstreckung in mindestens zwei, axial gegeneinander versetzte Kavitäten unterteilt ist und dass die Deckplatte (16) gestuft ausgeführt ist mit mindestens zwei Drosselstellen gegen den Stator, wobei die Dichtstreifen (17) unter Einschluss einer Wirbelkammer (22) auf je eine Stufe wirken.Device for sealing the gap between the rotor blades and the stator (8) of a turbomachine designed with a conical contour (51), the rotor blades (La3) at the blade end being provided with circumferential cover plates (16) which protrude into a cavity in the stator and form radial gaps against the stator provided with sealing strips (17),
characterized,
that the radial extension of the cavity at the labyrinth inlet (40) is subdivided into at least two cavities axially offset from one another and that the cover plate (16) is designed in a stepped manner with at least two throttle points against the stator, the sealing strips (17) being included a vortex chamber (22) act on one level each. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass am Labyrinth-Eintritt (40) die Kontur der Kavität im Stator (8) zunächst materialeinwärts verläuft, danach in Axialrichtung auswärts gerichtet ist unter Bildung eines in die Kavität hineinragenden Zackens (41) und dass die Deckplatte (16) mit einem Hinterstich (43) versehen ist, welcher der Form des Zackens (41) angepasst ist. (Fig. 3) Apparatus according to claim 1, characterized in that on Labyrinth entrance (40), the contour of the cavity in the stator (8) initially towards the material runs, then directed axially outwards under Formation of a prong (41) protruding into the cavity and that the Cover plate (16) is provided with an understitch (43), which is the shape of the point (41) is adjusted. (Fig. 3) Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Deckplatte (16) stufenförmig ausgebildet ist, wobei auf jede Stufe ein zumindest annähernd horizontal verlaufender, gekrümmter Dichtstreifen (52) wirkt. (Fig. 4, 6, 7)Device according to claim 1, characterized in that the cover plate (16) is step-shaped, with an at least on each step approximately horizontal, curved sealing strip (52) acts. (Fig. 4, 6, 7) Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass die radial auswärts gerichteten Flächen der Deckplattenstufen gegen die Strömungsrichtung schräg ausgebildet sind.Device according to claim 3, characterized in that the radial outward facing surfaces of the cover plate steps against the Flow direction are formed obliquely. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Kavität (42) am Labyrinth-Austritt radial eingezogen ist zwecks Bildung eines Minimalmass aufweisenden Engspaltes.Device according to claim 1, characterized in that the cavity (42) is drawn in radially at the labyrinth exit to form a Minimal narrow gap. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die innere strömungsbegrenzende Wand der Deckplatte (16) unmittelbar an der Hinterkante des Schaufelblattes mit einem radial auswärts gerichteten Knickwinkel (A) versehen ist.Device according to claim 1, characterized in that the inner flow-limiting wall of the cover plate (16) directly on the Trailing edge of the airfoil with a radially outward Kink angle (A) is provided. Vorrichtung nach Anspruch 1 dadurch gekennzeichnet, dass die strömungsbegrenzende Wand des Kanals (50) unmittelbar am Labyrinth-Eintritt (40) mit einem radial einwärts gerichteten Knickwinkel (B) versehen ist.Device according to claim 1, characterized in that the flow-limiting wall of the channel (50) directly at the entrance to the labyrinth (40) with a radially inward bend angle (B) is.
EP97810686A 1997-09-19 1997-09-19 Gap sealing device Expired - Lifetime EP0903468B1 (en)

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DE59710621T DE59710621D1 (en) 1997-09-19 1997-09-19 Gap sealing device
EP97810686A EP0903468B1 (en) 1997-09-19 1997-09-19 Gap sealing device
US09/153,270 US6102655A (en) 1997-09-19 1998-09-14 Shroud band for an axial-flow turbine
JP26168598A JP4199855B2 (en) 1997-09-19 1998-09-16 Shroud band for axial turbine
CN98119296.3A CN1294341C (en) 1997-09-19 1998-09-18 Enclosing belt for axial flow steam turbine

Applications Claiming Priority (1)

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EP97810686A EP0903468B1 (en) 1997-09-19 1997-09-19 Gap sealing device

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EP0903468B1 EP0903468B1 (en) 2003-08-20

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JP (1) JP4199855B2 (en)
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Also Published As

Publication number Publication date
EP0903468B1 (en) 2003-08-20
US6102655A (en) 2000-08-15
CN1294341C (en) 2007-01-10
JPH11148308A (en) 1999-06-02
DE59710621D1 (en) 2003-09-25
CN1212321A (en) 1999-03-31
JP4199855B2 (en) 2008-12-24

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