EP1167696B1 - Labyrinthdichtung für eine rotierende Welle - Google Patents
Labyrinthdichtung für eine rotierende Welle Download PDFInfo
- Publication number
- EP1167696B1 EP1167696B1 EP01112342A EP01112342A EP1167696B1 EP 1167696 B1 EP1167696 B1 EP 1167696B1 EP 01112342 A EP01112342 A EP 01112342A EP 01112342 A EP01112342 A EP 01112342A EP 1167696 B1 EP1167696 B1 EP 1167696B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- labyrinth seal
- sealing strips
- rotor
- stator
- relief
- 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
Links
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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
Definitions
- the invention is a labyrinth seal for rotor and Stator labyrinths according to the preamble of claim 1.
- Labyrinth seals as a seal between rotating and static Parts of axial flow machines are generally known from the prior art Technology known.
- the published documents DE-A1-35 23 469, EP-A1-982 475, EP-A1-799 973 or EP-A1-943 784 describe such Turbo machines with sealing strips and those in between Labyrinths in different designs.
- These sealing strips are usually caulked into a circumferential groove of the rotor or stator, as can also be seen, for example, in FIG. 1 of EP-A1-982 475.
- there is different ways of designing the labyrinth seal So there are single and double seals. Especially with big ones Pressure differences can also be several over the length of the Labyrinths distributed sealing strips are used.
- the geometric arrangement of the Sealing strips limited to the rotor or stator.
- the thermal load on the sealing strips is due to the changing temperature fields and the resulting Temperature gradients very high. This leads above all to the surface thermal stresses and thus cyclical fatigue.
- the circumferential grooves act as notches that the axial Increase the stress component.
- the entire labyrinth can be increased, for example Labyrinth section and appropriately designed transition radii from remaining component are set down, especially the first and the last groove relieved.
- the other grooves have a certain relief effect due to the adjacent grooves achieved, i.e. the notch factor of a groove inside such an arrangement of several grooves is smaller than that of a single one free-standing groove of the same geometry.
- relief grooves can therefore not be optimally arranged in any way.
- such statements lead to the relocation of the problems and not to a solution.
- deeper cuts should be avoided in order to avoid swirling of the leakage flow in these cuts and the associated heating of the flowing medium.
- individual relief grooves which are the same depth or deeper than the sealing strip grooves, generally have a worse notch factor than the sealing strips, so that the fatigue problem is shifted to the relief groove. This is very undesirable, especially for seals on shafts.
- the aim of this invention is to avoid the disadvantages mentioned.
- the Invention solves the problem of a known labyrinth seal optimize that the thermal stresses or deformations between two sealing strips can be checked in a targeted manner, thereby avoiding the above to avoid the damage mechanisms mentioned, and that an additional The component is heated by swirling the leakage flow can be avoided.
- this is done in a labyrinth seal according to the Preamble of claim 1 achieved in that the axial rigidity of the Rotor or stator between the two sealing strips is largely continuous.
- a flat relief groove embedded between two sealing strips which over a larger one Extends the area between the two adjacent sealing strips. It is also conceivable to provide a plurality of flat relief grooves, the Length spread is correspondingly smaller. In a preferred one Embodiment, the depth of the relief grooves is reduced to the extent that there is only a corrugated surface between the two neighboring ones Sealing strip results. In this way, the task can be advantageous can be solved, the increased number of relief grooves a very targeted voltage reduction enables. Stiffness jumps between the Grooves and the rotor or stator are avoided or become as small as kept possible. This advantageously reduces the notch factor.
- the previously known depths can also be used Relief grooves are used, provided that they are filled with a filler consists of a suitable elastic material, are filled.
- a filler consists of a suitable elastic material
- the measure serves the same purpose, as stated above, of controlled Distribution of the axial tension evenly on the rotor or Stator section between two sealing strips.
- the Relief grooves may be completely or partially filled with the filling material.
- the same wire can be used as filler material, which is also used for caulking the sealing strips.
- any material - preferably in wire form - can be used, which at the operating temperature of the seal the required elasticity and Shows long-term durability.
- All embodiments are also advantageous because, in addition to the improved voltage absorption or distribution, a defective Avoid eddy formation in the labyrinth or within the relief grooves. Such vortex formation can lead to undesirable heating of the Flow medium and thus the entire rotor or stator section to lead.
- FIGS. 1 to 4 Is shown in all Figures 1 to 4, a turbine blade 8 of a thermal Turbo machine with a rotor or stator 1. It is the Turbine blade 8 around a guide or moving blade. Located in all figures on the rotor or stator 1 sealing strip 2, which in a Sealing strip groove 3 embedded in the rotor or stator 1 or caulked and fastened with a caulking wire 4. The sealing strips 2 are arranged opposite the turbine blade 8. In all figures 1 to 4 are 2 relief grooves between the two sealing strips shown 6 arranged. According to the invention occur in the axial rigidity of the rotor or stator 1 despite the existing relief grooves 6 between the two Sealing strip 2 no big jumps and the axial rigidity is in the essentially steady.
- FIG. 1 This is achieved in FIG. 1 by a single flat relief groove 6, which extends over a large area between the two sealing strips 2 extends.
- FIG Relief grooves 6 arranged.
- the ratio of depth to axial distance the relief grooves 6 must correspond to the respective load situation of the labyrinth can be optimized.
- the maximum depth of relief grooves 6 is at the depth of the sealing strip groove 3.
- To meet the requirement of constant axial To satisfy rigidity should optimally be the depth of the relief grooves 6 lie between 25% and 50% of the depth of the sealing strip groove 3.
- the goal Such an optimization is the transient axial deformation of the Labyrinth section as evenly as possible on the actual sealing strip groove 3 and to divide the relief grooves 6. This will strain the Sealing strip groove 3 reduces the relief grooves 6 without comparison to burden excessively.
- FIG. 3 shows a further embodiment of the invention Relief grooves 6.
- the relief grooves 6 are so flat and accordingly numerous that there is only a corrugated surface between the sealing strip 2 on the rotor or stator 1 results.
- FIG. 4 shows a further embodiment of the invention Relief grooves 6, with which deeper grooves 6 can also be used.
- the relief grooves 6 are wholly or partially with a filler material 7 filled, both possibilities in the relief grooves 6 of FIG. 4 are visible.
- the caulking wire 4 of the sealing strip grooves 3 can this material can be caulked into the relief grooves 6.
- the filling material with regard to the elastic Properties and the coefficient of thermal expansion can do that Deformation behavior of the filled relief groove 6 and thus the axial Rigidity of the labyrinth area can be controlled within certain limits.
- the same wire can be used as filler material, which is also used for caulking the sealing strips.
- any material - preferably in the form of a wire - can be used, that the required elasticity at the operating temperature of the seal and Shows long-term durability.
- the filling material also makes it possible the deeper relief grooves known from the prior art use without tightening the cyclical Lifetime problem occurs.
- the same wire can be used, which is also used for caulking the sealing strips is used.
- any material - preferably in Wire shape - can be used because at the operating temperature of the seal shows the required elasticity and long-term durability.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Fig. 1
- eine erste Ausführungsform von Labyrinthdichtung gemäss der vorliegenden Erfindung zeigt,
- Fig. 2
- eine zweite Ausführungsform von Labyrinthdichtung gemäss der vorliegenden Erfindung zeigt
- Fig. 3
- eine dritte Ausführungsform von Labyrinthdichtung gemäss der vorliegenden Erfindung zeigt und
- Fig. 4
- eine vierte Ausführungsform von Labyrinthdichtung gemäss der vorliegenden Erfindung zeigt.
- 1
- Rotor bzw. Stator
- 2
- Dichtstreifen
- 3
- Dichtstreifennut
- 4
- Stemmdraht
- 5
- Labyrinth
- 6
- Entlastungsnuten
- 7
- Füllmaterial
- 8
- Turbinenschaufel
Claims (8)
- Labyrinthdichtung zwischen rotierenden und statischen Teilen (1, 8) einer axialen Strömungsmaschine mit einem Rotor und einem Stator (1), welche Labyrinthdichtung aus zwischen den rotierenden und statischen Teilen (1, 8) angeordneten Dichtstreifen (2) besteht, wobei die Dichtstreifen (2) in einer Dichtstreifennut (3) am Rotor oder Stator (1) angebracht sind, und wobei sich zwischen zwei Dichtstreifen (2) mindestens eine Entlastungsnut (6) am Rotor oder Stator (1) befindet,
dadurch gekennzeichnet, dass
die axiale Steifigkeit des Rotors oder Stators (1) zwischen den zwei Dichtstreifen (2) weitgehend stetig ist. - Labyrinthdichtung nach Anspruch 1,
dadurch gekennzeichnet, dass
sich zwischen zwei Dichtstreifen (2) mindestens eine Entlastungsnut (6), welche maximal die Tiefe der Dichtstreifennut (3) hat, befindet. - Labyrinthdichtung nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
sich zwischen den zwei Dichtstreifen (2) eine Vielzahl von Entlastungsnuten (6) welche maximal die Tiefe der Dichtstreifennut (3) haben, befinden. - Labyrinthdichtung nach einem der Ansprüche 2 oder 3,
dadurch gekennzeichnet, dass
die Entlastungsnut(en) (6) maximal die Tiefe von 25% bis 50% der Tiefe der Dichtstreifennut (3) hat/haben. - Labyrinthdichtung nach Anspruch 4,
dadurch gekennzeichnet, dass
die Entlastungsnuten (6) aus einer gewellten Rotor- oder Statoroberfläche zwischen den zwei Dichtstreifen (2) bestehen. - Labyrinthdichtung nach Anspruch 1,
dadurch gekennzeichnet, dass
die mindestens eine Entlastungsnut (6) ganz oder teilweise mit einem elastischen Füllmaterial (7) gefüllt ist. - Labyrinthdichtung nach Anspruch 6,
dadurch gekennzeichnet, dass
das Füllmaterial (7) ein Draht ist. - Labyrinthdichtung nach einem der vorangehenden Ansprüche,
dadurch gekennzeichnet, dass
es sich um eine Dichtung zwischen einer Turbinenschaufel (8), also einer Leit- oder Laufschaufel, und dem Rotor oder Stator (1) handelt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10030820 | 2000-06-23 | ||
DE10030820A DE10030820A1 (de) | 2000-06-23 | 2000-06-23 | Labyrinthdichtung für eine rotierende Welle |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1167696A2 EP1167696A2 (de) | 2002-01-02 |
EP1167696A3 EP1167696A3 (de) | 2003-11-12 |
EP1167696B1 true EP1167696B1 (de) | 2004-12-15 |
Family
ID=7646669
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01112342A Expired - Lifetime EP1167696B1 (de) | 2000-06-23 | 2001-05-21 | Labyrinthdichtung für eine rotierende Welle |
Country Status (3)
Country | Link |
---|---|
US (1) | US6575693B2 (de) |
EP (1) | EP1167696B1 (de) |
DE (2) | DE10030820A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9752455B2 (en) | 2013-10-08 | 2017-09-05 | MTU Aero Engines AG | Component support and turbomachine |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10205092A1 (de) * | 2002-02-07 | 2003-08-21 | Cft Gmbh | Backenbrecher mit durchgehender Antriebswelle |
GB0308147D0 (en) * | 2003-04-09 | 2003-05-14 | Rolls Royce Plc | A seal |
WO2004113771A2 (en) * | 2003-06-20 | 2004-12-29 | Elliott Company | Hybrid abradable labyrinth damper seal |
WO2004113769A2 (en) * | 2003-06-20 | 2004-12-29 | Elliott Company | Stepped labyrinth damper seal |
US7806410B2 (en) | 2007-02-20 | 2010-10-05 | United Technologies Corporation | Damping device for a stationary labyrinth seal |
US8876484B2 (en) * | 2011-08-05 | 2014-11-04 | Hamilton Sundstrand Corporation | Turbine blade pocket pin stress relief |
US8967955B2 (en) * | 2011-09-26 | 2015-03-03 | Honeywell International Inc. | Turbocharger with variable nozzle having labyrinth seal for vanes |
DE102013017710A1 (de) | 2013-10-24 | 2015-04-30 | Man Diesel & Turbo Se | Dichtungssystem |
US9995161B2 (en) | 2014-11-12 | 2018-06-12 | Borgwarner Inc. | Modular turbocharger clearance seal |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE675124C (de) * | 1937-06-02 | 1939-04-29 | Aeg | Stopfbuechse fuer Dampf- oder Gasturbinen mit hohen Betriebstemperaturen |
IT1063035B (it) * | 1975-05-09 | 1985-02-11 | Maschf Augsburg Nuernberg Ag | Apparato per la realizzazione del procedimento per elevare il limite dinamico di potenza di turbine a vapore od a gas o di compressori |
DE3523469A1 (de) | 1985-07-01 | 1987-01-08 | Bbc Brown Boveri & Cie | Beruehrungsfreie spaltdichtung fuer turbomaschinen |
DE59609405D1 (de) | 1996-04-01 | 2002-08-08 | Alstom | Wandkontur für eine axiale Strömungsmaschine |
EP0943784A1 (de) | 1998-03-19 | 1999-09-22 | Asea Brown Boveri AG | Konturierter Kanal einer axialen Strömungsmaschine |
EP0982475A1 (de) | 1998-08-28 | 2000-03-01 | Asea Brown Boveri AG | Beschaufelung einer axial durchströmten Turbomaschine mit Deckbändern |
US6168377B1 (en) * | 1999-01-27 | 2001-01-02 | General Electric Co. | Method and apparatus for eliminating thermal bowing of steam turbine rotors |
-
2000
- 2000-06-23 DE DE10030820A patent/DE10030820A1/de not_active Withdrawn
-
2001
- 2001-05-21 EP EP01112342A patent/EP1167696B1/de not_active Expired - Lifetime
- 2001-05-21 DE DE50104807T patent/DE50104807D1/de not_active Expired - Lifetime
- 2001-06-25 US US09/887,009 patent/US6575693B2/en not_active Expired - Lifetime
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9752455B2 (en) | 2013-10-08 | 2017-09-05 | MTU Aero Engines AG | Component support and turbomachine |
Also Published As
Publication number | Publication date |
---|---|
EP1167696A3 (de) | 2003-11-12 |
US20020006330A1 (en) | 2002-01-17 |
EP1167696A2 (de) | 2002-01-02 |
DE50104807D1 (de) | 2005-01-20 |
US6575693B2 (en) | 2003-06-10 |
DE10030820A1 (de) | 2002-01-03 |
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