EP0903468A1 - Deckband für axialdurchströmte Turbine - Google Patents
Deckband für axialdurchströmte Turbine Download PDFInfo
- 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
- Authority
- 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
Links
- 238000007789 sealing Methods 0.000 claims abstract description 31
- 239000000463 material Substances 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 210000003027 ear inner Anatomy 0.000 description 16
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000005494 condensation Effects 0.000 description 2
- 238000009833 condensation Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 241001295925 Gegenes Species 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000010079 rubber tapping Methods 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
Images
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
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
Description
- 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.
- 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.
- 8
- Stator
- 9
- Rotor
- 10
- statorseitige strömungsbegrenzende Wand
- 11
- rotorseitige strömungsbegrenzende Wand
- 13
- Fussplatte der Leitschaufeln Le
- 15
- Laufschaufel-Labyrinth
- 16
- Deckplatte der Laufschaufel La
- 17
- Dichtstreifen
- 18
- Axialspalt
- 19
- Leitschaufel-Labyrinth
- 20
- Deckplatte der Leitschaufel Le
- 21
- Fussplatte der Laufschaufel La
- 22
- Wirbelkammer
- 40
- Labyrinth-Eintritt
- 40a, 40b, 40c
- Kavität
- 41
- Zacken
- 42
- Labyrinth-Austritt
- 43
- Hinterstich
- 50
- durchströmter Kanal
- 51
- äussere Kanalkontur
- 52
- horizontale Dichtstreifen
- 54
- Kanalkontur bei Anzapfung
- La, La3 ...
- Laufschaufeln
- Le, Le3 ...
- Leitschaufeln
- A
- Knickwinkel aussen hinter Laufrad
- B
- Knickwinkel aussen vor Laufrad
- P
- Intersektion mit gerader äusserer Kanalkontur
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. - 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)
- 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)
- Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass die radial auswärts gerichteten Flächen der Deckplattenstufen gegen die Strömungsrichtung schräg ausgebildet sind.
- Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Kavität (42) am Labyrinth-Austritt radial eingezogen ist zwecks Bildung eines Minimalmass aufweisenden Engspaltes.
- 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.
- 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.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97810686A EP0903468B1 (de) | 1997-09-19 | 1997-09-19 | Vorrichtung zur Spaltdichtung |
DE59710621T DE59710621D1 (de) | 1997-09-19 | 1997-09-19 | Vorrichtung zur Spaltdichtung |
US09/153,270 US6102655A (en) | 1997-09-19 | 1998-09-14 | Shroud band for an axial-flow turbine |
JP26168598A JP4199855B2 (ja) | 1997-09-19 | 1998-09-16 | 軸流タービンのためのシュラウドバンド |
CN98119296.3A CN1294341C (zh) | 1997-09-19 | 1998-09-18 | 用于轴流式汽轮机的围带 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97810686A EP0903468B1 (de) | 1997-09-19 | 1997-09-19 | Vorrichtung zur Spaltdichtung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0903468A1 true EP0903468A1 (de) | 1999-03-24 |
EP0903468B1 EP0903468B1 (de) | 2003-08-20 |
Family
ID=8230394
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97810686A Expired - Lifetime EP0903468B1 (de) | 1997-09-19 | 1997-09-19 | Vorrichtung zur Spaltdichtung |
Country Status (5)
Country | Link |
---|---|
US (1) | US6102655A (de) |
EP (1) | EP0903468B1 (de) |
JP (1) | JP4199855B2 (de) |
CN (1) | CN1294341C (de) |
DE (1) | DE59710621D1 (de) |
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1997
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1998
- 1998-09-14 US US09/153,270 patent/US6102655A/en not_active Expired - Lifetime
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- 1998-09-18 CN CN98119296.3A patent/CN1294341C/zh not_active Expired - Fee Related
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1001139B1 (de) * | 1998-11-10 | 2004-01-07 | ALSTOM (Switzerland) Ltd | Spitzendichtung für Turbinenlaufschaufeln |
DE102009042857A1 (de) * | 2009-09-24 | 2011-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbine mit Deckband-Labyrinthdichtung |
DE102009052314A1 (de) * | 2009-11-07 | 2011-05-12 | Mtu Aero Engines Gmbh | Dichtanordnung für eine Gasturbine und eine derartige Gasturbine |
WO2011054341A3 (de) * | 2009-11-07 | 2011-07-07 | Mtu Aero Engines Gmbh | Dichtanordnung für eine gasturbine und eine derartige gasturbine |
Also Published As
Publication number | Publication date |
---|---|
DE59710621D1 (de) | 2003-09-25 |
JPH11148308A (ja) | 1999-06-02 |
US6102655A (en) | 2000-08-15 |
JP4199855B2 (ja) | 2008-12-24 |
CN1294341C (zh) | 2007-01-10 |
CN1212321A (zh) | 1999-03-31 |
EP0903468B1 (de) | 2003-08-20 |
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