EP0903468B1 - Dispositif d'étanchéité pour un interstice - Google Patents

Dispositif d'étanchéité pour un interstice Download PDF

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Publication number
EP0903468B1
EP0903468B1 EP97810686A EP97810686A EP0903468B1 EP 0903468 B1 EP0903468 B1 EP 0903468B1 EP 97810686 A EP97810686 A EP 97810686A EP 97810686 A EP97810686 A EP 97810686A EP 0903468 B1 EP0903468 B1 EP 0903468B1
Authority
EP
European Patent Office
Prior art keywords
stator
flow
labyrinth
shroud
cavity
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP97810686A
Other languages
German (de)
English (en)
Other versions
EP0903468A1 (fr
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
Alstom Schweiz AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP97810686A priority Critical patent/EP0903468B1/fr
Priority to DE59710621T priority patent/DE59710621D1/de
Priority to US09/153,270 priority patent/US6102655A/en
Priority to JP26168598A priority patent/JP4199855B2/ja
Priority to CN98119296.3A priority patent/CN1294341C/zh
Publication of EP0903468A1 publication Critical patent/EP0903468A1/fr
Application granted granted Critical
Publication of EP0903468B1 publication Critical patent/EP0903468B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

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.
  • labyrinth seals are also known, in which the The cover band of the blades seals against a honeycomb arrangement.
  • there Prongs of the cover tape form either a smooth or a stepped labyrinth with pure radial gaps or, as discussed in EP 0536575, with radial and Diagonatspalten.
  • a brush against certain transient operating phases is relatively unproblematic in this type of gap seals, since the Honeycomb inserts are made of an abradable material. in case of a When rubbed, there is a local abrasion of the wear layer, the then, however, in the case of flow channels of pronounced conicity among the important stationary nominal operating conditions again large column and so that big company games can result.
  • 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 8.
  • the with their 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.
  • Radial gaps 26, which represent the labyrinth outlets 42 are 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 sealing strips caulked in the stator 8A 17A forms a half-labyrinth with pure radial gaps. The are recognizable spacious labyrinth entry 40A and the unfavorably designed labyrinth exit 42A. With 54 the channel wall is designated when it is in a tap empties.
  • the contour runs in the stator 8 initially radially outwards and against the flow direction, then downstream in the axial direction, forming a protruding into the cavity Jagged 41.
  • the cover plate 16 is configured accordingly. You will be with provided with an understitch 43 which is adapted to the shape of the prongs.
  • the axial The running part of the backstitch is dimensioned in such a way that during the assembly and during the operating transient cover plate and Do not touch the stator.
  • With approximately horizontal in its first section running and then curved sealing strips 52 are the individual Partial cavities 40a and 40c sealed. These sealing strips 52 are preferred with its horizontally running section in the axially running housing parts caulked.
  • a comparison with Fig. 2 shows that in the operating position a much smaller passage gap 18 between the stator and Cover plate adjusts. The flow forms within the partial cavity 40c damping vortex chamber 22.
  • the known half-labyrinth is through after this embodiment replaced a full maze.
  • the outer diameter of the cover plate 16 stepped and provided with only two throttling points.
  • Two caulked into the stator 8 limit radial sealing strips 17, each acting on one step a well functioning vortex chamber 22. Due to the radial displacement of the Throttling points do not influence each other. With this full labyrinth a further reduction in the gap mass flow is achieved.
  • a third measure serves to improve the re-inflow of the Maze mass flow in the main channel.
  • the stator housing on Labyrinth outlet 42 reduced to a permissible minimum dimension in the radial direction Crevice flow is immediately compared to the general one Tapered outward stator wall taken over. With that you can significantly reduce the harmful cross exchange of flow material and the unnecessary dissipation of the high-energy gap flow largely avoid.
  • the total pressure profile is through the kinked stator wall the main flow favorably influenced.
  • the flow-limiting wall of the cover plate 16 is directly on Provide outlet blades La3 with an articulation angle A.
  • This kink angle is dimensioned so that the outflow from the blades with respect to Total pressure and outflow angle is homogenized.
  • the broken 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 swirl at 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 total pressure and outflow angle inhomogeneity be as low as possible 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.
  • the desired total pressure reduction in achieved in this area is based on the following considerations: At the outlet the blades have a divergent flow, with swirl at the cylinder. At least the flow
  • FIG. 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 labyrinth entrance is in its radial extension in three axially offset partial cavities 40a, 40b and 40c divided.
  • three are caulked into the stator radial sealing strips 17 arranged.
  • main channel 50 is the cavity at the labyrinth outlet 42 immediately behind the last radial sealing strip 17 in the radial direction to an allowable Minimum dimensions reduced. As a rule, this minimum dimension is also used in the front cavities provided.
  • the cover plate 16 is step-shaped educated. With approximately horizontal in its first section and then curved sealing strips 52 become the individual partial cavities 40a, 40b, 40c sealed. These sealing strips 52 are preferably with their horizontally extending section in the axially extending housing parts caulked. It is understood that other fastening methods and Geometries are possible.
  • the partial cavities separated by the sealing strips 52 40b and 40c form vortex chambers 22.
  • Fig. 4 shows the cover plate in the normal operating position.
  • the front sealing strips 52 act on the front edges of the horizontally oriented cover plate gradations.
  • the rear radial sealing strips 17 act horizontally on the last one directional cover plate gradation.
  • the cover plate 16 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.
  • the sealing strips 52 in the intersection between axially and radially directed Intervene in the step part.
  • 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 radial sealing strips 17 against the horizontal facing rear cover plate part. The sealing strips are in the dashed position 52 no longer engaged. Only the last of the radial seals here Sealing strip 17 and thus prevents uncontrolled working fluid through the Flow through 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 is divided into two partial cavities 40a and 40c. These partial cavities 40a and 40c are separated by one in its first Section approximately horizontal and then curved sealing strips 52. This strip acts on a simply stepped cover plate 16. Die remaining sealing strips 17 are arranged so that at least in extreme positions one of the strips 52 or 17 is effective.
  • FIG. 7 finally shows the new solution for a cover plate 16 with a Taper of approx. 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. moreover this solution offers the advantage that the radially inward and in itself aerodynamically damaging kink angles at the inlet can be avoided can. This means that the cover band contour corresponds to the globally specified one Channel contour.

Landscapes

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

Claims (5)

  1. Dispositif pour réaliser l'étanchéité de l'interstice entre des pales (La) tournant dans un canal d'écoulement (50) s'élargissant en forme conique d'une turbomachine et le contour extérieur du canal (51) du stator (8), les pales (La) étant pourvues à leur extrémité de plaques de recouvrement (16) périphériques, qui pénètrent dans une cavité dans le stator (8), et une garniture à labyrinthe réalisant l'étanchéité d'interstices radiaux entre le stator (8) et les plaques de recouvrement périphériques (16) au moyen de bandes d'étanchéité fixées sur le stator, une partie des bandes d'étanchéité étant disposée radialement, la cavité (40) à l'entrée du labyrinthe étant divisée dans son étendue radiale en au moins deux cavités partielles décalées axialement l'une par rapport à l'autre, et la plaque de recouvrement (16) étant réalisée en forme de gradins avec au moins deux étranglements vers le stator (8), et des bandes d'étanchéité agissant sur un gradin respectif en incluant uen chambre de tourbillonnement (22), caractérisé en ce qu'une bande d'étanchéité (52) recourbée à son extrémité libre, s'étendant approximativement horizontalement dans sa première portion, agit sur au moins un gradin de la plaque de recouvrement (16) réalisée en forme de gradins.
  2. Dispositif selon la revendication 1, caractérisé en ce que les surfaces des gradins de la plaque de recouvrement orientées radialement vers l'extérieur sont réalisées obliquement à l'encontre du sens de l'écoulement.
  3. Dispositif selon la revendication 1, caractérisé en ce que sur l'entrée du labyrinthe, le contour de la cavité (40) dans le stator (8) s'étend d'abord radialement vers l'extérieur et à l'encontre du sens de l'écoulement, puis est orienté vers l'aval dans la direction axiale en formant une pointe (41) pénétrant dans la cavité (40), et en ce que la plaque de recouvrement (16) est pourvue d'une contre-dépouille (43) qui est adaptée à la forme de la pointe (41).
  4. Dispositif selon la revendication 1, caractérisé en ce que le carter du stator est renfoncé radialement au niveau de la sortie du labyrinthe (42) afin de former un interstice étroit présentant une masse minime.
  5. Dispositif selon la revendication 1, caractérisé en ce que la paroi interne de la plaque de recouvrement (16) limitant l'écoulement est pourvue directement sur l'arête arrière de la pale d'un angle d'inflexion (A) orienté radialement vers l'extérieur.
EP97810686A 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice Expired - Lifetime EP0903468B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810686A EP0903468B1 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice
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 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice

Publications (2)

Publication Number Publication Date
EP0903468A1 EP0903468A1 (fr) 1999-03-24
EP0903468B1 true EP0903468B1 (fr) 2003-08-20

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810686A Expired - Lifetime EP0903468B1 (fr) 1997-09-19 1997-09-19 Dispositif d'étanchéité pour un interstice

Country Status (5)

Country Link
US (1) US6102655A (fr)
EP (1) EP0903468B1 (fr)
JP (1) JP4199855B2 (fr)
CN (1) CN1294341C (fr)
DE (1) DE59710621D1 (fr)

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CN103375185A (zh) * 2012-04-13 2013-10-30 通用电气公司 具有平行壳体配置的涡轮机叶冠

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Cited By (1)

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Publication number Priority date Publication date Assignee Title
CN103375185A (zh) * 2012-04-13 2013-10-30 通用电气公司 具有平行壳体配置的涡轮机叶冠

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
EP0903468A1 (fr) 1999-03-24
CN1212321A (zh) 1999-03-31

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