WO2005073518A1 - Ensemble d'étanchéité - Google Patents

Ensemble d'étanchéité Download PDF

Info

Publication number
WO2005073518A1
WO2005073518A1 PCT/DE2005/000131 DE2005000131W WO2005073518A1 WO 2005073518 A1 WO2005073518 A1 WO 2005073518A1 DE 2005000131 W DE2005000131 W DE 2005000131W WO 2005073518 A1 WO2005073518 A1 WO 2005073518A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
walls
sealing
honeycomb
rotation
Prior art date
Application number
PCT/DE2005/000131
Other languages
German (de)
English (en)
Inventor
Reinhold Meier
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Priority to US10/588,141 priority Critical patent/US20070273103A1/en
Priority to DE502005007136T priority patent/DE502005007136D1/de
Priority to EP05706719A priority patent/EP1711689B1/fr
Publication of WO2005073518A1 publication Critical patent/WO2005073518A1/fr

Links

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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the invention relates to a sealing arrangement, in particular for a gas turbine or an aircraft engine, according to the preamble of patent claim 1.
  • Gas turbines consist of several assemblies, for example a fan, a combustion chamber, preferably several compressors and several turbines.
  • the preferably several turbines are in particular a high-pressure turbine and a low-pressure turbine, and the several compressors are in particular a high-pressure compressor and a low-pressure compressor.
  • a plurality of guide vane rings are positioned one behind the other in a turbine and a compressor of a gas turbine in the axial direction or in the flow direction of the gas turbine, each guide vane ring having a plurality of guide vanes which are arranged distributed over the circumference.
  • a rotor blade ring which has a plurality of rotor blades, is positioned between each two adjacent guide vane rings. The rotor blades are assigned to a rotor and rotate together with the rotor with respect to a fixed housing and also the guide vanes of the guide vane rings, which are also designed to be stationary.
  • honeycomb seal comprising a plurality of honeycomb sealing cells to the stator, that is to say the fixed housing or the radially inner ends of the stationary guide vanes, the honeycomb sealing cells being separated from one another by walls.
  • the walls that separate the honeycomb cells of the honeycomb seal run exactly in the radial direction, so that, for example, the sealing fins are oriented perpendicular to the walls of the honeycomb sealing cells that run transversely to the direction of rotation of the sealing fins.
  • the rotor in particular the sealing fin
  • the rotor is rubbed into the stator-side honeycomb seal, the rotor therefore strikes the walls of the honeycomb seal cells perpendicular to the direction of rotation of the honeycomb seal cells in the axial direction of view, as a result of which the rotation or rotation of the rotor is opposed by a resistance force.
  • Walls of the honeycomb sealing cells that run in this way are in fact relatively stiff, as a result of which the walls of the honeycomb sealing cells hardly deform.
  • the rotor, in particular the sealing fin runs into the honeycomb seal, the walls of the honeycomb sealing cells are removed at least in certain areas according to the prior art. Accordingly, the honeycomb seal is damaged and the gap to be sealed is enlarged, which is disadvantageous overall.
  • the present invention is based on the problem of creating a novel sealing arrangement, in particular for a gas turbine or an aircraft engine.
  • a sealing arrangement according to claim 1 At least the walls of the honeycomb sealing cells which run transversely to the direction of rotation of the rotor are positioned radially obliquely in the direction of rotation of the rotor.
  • the walls of the honeycomb sealing cells running transversely to the direction of rotation of the rotor are inclined radially in the direction of rotation of the rotor. Accordingly, the walls of the sealing cells no longer run perpendicular to the rotor, in particular to the rotor-side sealing fins in the axial direction of view, but rather these walls run at a certain angle to the rotor.
  • This provides a deformability of the walls of the honeycomb seal cells, so that when the rotor, in particular the sealing fins on the rotor side, is rubbed into the honeycomb seal, the walls are prevented from being worn or cracked.
  • an effective sealing of a gap between a rotor and a stator is therefore possible.
  • the walls of the honeycomb sealing cells running transversely to the direction of rotation of the rotor are preferably inclined in the direction of rotation of the rotor such that edges of these walls facing the rotor are offset in relation to the rotor in the direction of rotation of the rotor.
  • the edges of these walls facing the rotor and / or the edges of these walls facing away from the rotor are curved or run in a straight line.
  • the walls of the honeycomb sealing cells which run in the direction of rotation of the rotor are also inclined.
  • Figure 1 is a highly schematic side view in the axial direction of view of a honeycomb seal of a sealing arrangement according to the prior art comprising several honeycomb sealing cells.
  • FIG. 2 shows a highly schematic plan view in the radial direction of view of the honeycomb seal according to FIG. 1 comprising a plurality of honeycomb sealing cells;
  • FIG. 3 shows a highly schematic side view in the axial direction of view of a honeycomb seal of a sealing arrangement comprising a plurality of honeycomb sealing cells according to a first exemplary embodiment of the present invention
  • FIG. 4 shows a highly schematic plan view in the radial direction of view of the honeycomb seal according to FIG. 3 comprising several honeycomb sealing cells;
  • FIG. 5 shows a highly schematic plan view in the radial viewing direction of a honeycomb seal of a sealing arrangement comprising a plurality of honeycomb sealing cells, according to a second exemplary embodiment of the present invention.
  • FIG. 6 shows a highly schematic plan view in the radial direction of view of a honeycomb seal of a sealing arrangement comprising a plurality of honeycomb sealing cells according to a third exemplary embodiment of the present invention.
  • FIG. 1 and 2 show a highly schematized honeycomb seal 10 of a sealing arrangement according to the prior art between a rotor, not shown, and a stator, also not shown, of a gas turbine.
  • 1 shows a schematic side view of the honeycomb seal 10 in the axial direction of view
  • FIG. 2 shows a schematic top view sees the same in a radial viewing direction.
  • the X-coordinate of the coordinate systems shown is the radial direction
  • the Y-coordinate is the circumferential direction
  • the Z-coordinate is the axial direction. 1 can be seen on the XY plane, in the radial direction of FIG. 2 one can see the YZ plane.
  • the honeycomb seal 10 is formed by a plurality of honeycomb seal cells 11, the honeycomb seal rows 11 in FIGS. 1 and 2 having a rectangular cross-sectional area. At this point it should be pointed out that the honeycomb seals can of course also have a hexagonal cross-sectional profile.
  • honeycomb seal cells 11 of the honeycomb seal 10 are delimited by several walls. For the purposes of the present invention, a distinction should be made between walls which run transversely or longitudinally to the direction of rotation of a rotor.
  • the direction of rotation of a rotor not shown, is illustrated in FIGS. 1 and 2 by an arrow 12.
  • Walls of the honeycomb seal cells 11 which run transversely to the direction of rotation 12 are identified by the reference number 13
  • walls of the honeycomb seal cells 11 which run longitudinally or parallel to the direction of rotation 12 are identified by the reference number 14.
  • the walls 13 extending transversely to the direction of rotation of the rotor form a resistance for the rotor 12, since walls 13 designed in this way are relatively rigid and can deform only slightly, if at all.
  • the walls 13 are accordingly removed and thus damaged.
  • FIGS. 3 and 4 show a honeycomb seal 15 of a sealing arrangement according to the invention according to a first embodiment of the invention in different representations or viewing directions, the viewing directions of FIGS. 3 and 4 corresponding to the viewing directions of FIGS. 1 and 2.
  • the honeycomb seal 15 of FIGS. 3 and 4 also consists of several honeycomb seal cells 16, the honeycomb seal cells 16 having a rectangular contour in cross section.
  • the honeycomb sealing cells 16 are in turn delimited by a plurality of walls, which in the sense of the present invention fertilizer are aligned optimally relative to the direction of rotation (arrow 17) of a rotor.
  • the walls 18 of the honeycomb sealing cells 17, which run transversely to the direction of rotation of the rotor, are set radially obliquely in the direction of rotation of the rotor. This can best be seen in FIG. 3 (corresponds to the axial viewing direction), from which the radial inclination of the walls 18 can be seen.
  • the walls 18 of the honeycomb sealing cells 16, which run transversely to the direction of rotation 17 of the rotor, are inclined such that an edge 20 facing the rotor is offset in the direction of rotation of the rotor relative to an edge 21 facing away from the rotor, which means that the edge 20 facing the rotor is positioned in the direction of rotation 17 forward or downstream of the edge 21 facing away from the rotor.
  • the offset edges 20 and 21 of the walls 18 running transversely to the direction of rotation 17 of the rotor are shown as lines running parallel to one another. The edges 20, 21 of the walls 18 therefore run in a straight line.
  • FIGS. 5 and 6 show two further exemplary embodiments of honeycomb seals or sealing arrangements according to the invention. Since the exemplary embodiments of FIGS. 5 and 6 essentially correspond to the exemplary embodiment of FIGS. 3 and 4, the same reference numbers are used to avoid unnecessary repetitions for the same assemblies.
  • the exemplary embodiment in FIG. 5 differs from the exemplary embodiment in FIGS. 3 and 4 in that, in the honeycomb seal 22 in FIG. 5, the edges 20 of the walls 18 which run toward the rotor and which run transversely to the direction of rotation 17 of the rotor do not run in a straight line, but rather are curved or are arched. The curvature extends in the direction of rotation 17 of the rotor. The edges 21 of the walls 18 which run away from the rotor and run transversely to the direction of rotation of the rotor, however, run in a straight line. It should be noted that, in contrast to the solution shown in FIG.
  • the edges 21 facing away from the rotor as well as the edges 20 of the walls 18 facing the rotor can of course also be curved or curved.
  • 6 shows a further exemplary embodiment of a honeycomb seal 23 according to the invention, wherein in the honeycomb seal 23 according to FIG. 6, in addition to the walls 18 running transversely to the direction of rotation 17 of the rotor, the walls 19 of the honeycomb seal cells 16 running in the direction of rotation of the rotor are also inclined.
  • All of the exemplary embodiments shown have in common that at least the walls 18 of the honeycomb sealing cells 16, which run transversely to the direction of rotation 17 of the rotor, are radially inclined in the direction of rotation of the rotor.
  • the edges 20, 21, which delimit the walls 18 running transversely to the direction of rotation of the rotor are offset from one another.
  • the edges 20, 21 either run straight and / or curved. This enables good elastic and plastic deformability of the walls of the honeycomb seal cells, without the walls of the honeycomb seal cells being damaged or removed when the rotor or sealing fins on the rotor are rubbed into the honeycomb seal. The stress on the honeycomb seal can therefore be reduced, which increases the life of the honeycomb.
  • the sealing arrangement according to the invention serves in particular to seal a radial gap between the radially inner ends of guide vanes and a rotor.
  • the honeycomb seals are then assigned to the radially inner ends of the guide blades or corresponding inner shrouds of the guide blades, sealing fins assigned to the rotor interacting with the honeycomb seal. It is also possible to use such a sealing arrangement to seal a gap between the radially outer ends of the rotating blades and a stationary housing.
  • the use of the sealing arrangement in the compressor region or turbine region of a gas turbine, in particular an aircraft engine, is preferred.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

L'invention concerne un ensemble d'étanchéité notamment pour une turbine à gaz telle qu'un groupe motopropulseur. Cet ensemble d'étanchéité sert à fermer un interstice entre un rotor et un stator, notamment un interstice entre les extrémités orientées radialement vers l'intérieur de pales fixes et un rotor et/ou un interstice entre les extrémités orientées radialement vers l'extérieur d'aubes directrices rotatives et un carter fixe, au stator étant associée une garniture d'étanchéité alvéolaire (15) comprenant plusieurs alvéoles (16) séparées les uns des autres par des parois (18, 19). L'invention est caractérisée en ce qu'au moins les parois (18) des alvéoles (16) de la garniture d'étanchéité orientées transversalement au sens de rotation (17) du rotor sont radialement inclinées dans le sens de rotation (17) du rotor.
PCT/DE2005/000131 2004-01-31 2005-01-28 Ensemble d'étanchéité WO2005073518A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US10/588,141 US20070273103A1 (en) 2004-01-31 2005-01-28 Sealing Device
DE502005007136T DE502005007136D1 (de) 2004-01-31 2005-01-28 Dichtungsanordnung
EP05706719A EP1711689B1 (fr) 2004-01-31 2005-01-28 Ensemble d' étanchéité

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004004915.7 2004-01-31
DE102004004915A DE102004004915A1 (de) 2004-01-31 2004-01-31 Dichtungsanordnung

Publications (1)

Publication Number Publication Date
WO2005073518A1 true WO2005073518A1 (fr) 2005-08-11

Family

ID=34801375

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2005/000131 WO2005073518A1 (fr) 2004-01-31 2005-01-28 Ensemble d'étanchéité

Country Status (4)

Country Link
US (1) US20070273103A1 (fr)
EP (1) EP1711689B1 (fr)
DE (2) DE102004004915A1 (fr)
WO (1) WO2005073518A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10385783B2 (en) 2012-01-23 2019-08-20 MTU Aero Engines AG Turbomachine seal arrangement

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010062087A1 (de) * 2010-11-29 2012-05-31 Siemens Aktiengesellschaft Strömungsmaschine mit Dichtstruktur zwischen drehenden und ortsfesten Teilen sowie Verfahren zur Herstellung dieser Dichtstruktur
US10794489B2 (en) 2015-12-01 2020-10-06 Saint-Gobain Performance Plastics Corporation Annular seals
CN108412556A (zh) * 2018-03-15 2018-08-17 哈尔滨工业大学 一种用于控制涡轮动叶叶尖泄漏流动的棱柱型凹腔叶顶

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB793886A (en) * 1955-01-24 1958-04-23 Solar Aircraft Co Improvements in or relating to sealing means between relatively movable parts
US3649033A (en) * 1969-12-24 1972-03-14 Nippon Denso Co Honeycomb rotor-sealing device and method of manufacture
US4218066A (en) * 1976-03-23 1980-08-19 United Technologies Corporation Rotary seal
EP0716218A1 (fr) * 1994-12-05 1996-06-12 United Technologies Corporation Virole de compresseur

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4477089A (en) * 1982-07-26 1984-10-16 Avco Corporation Honeycomb seal for turbine engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB793886A (en) * 1955-01-24 1958-04-23 Solar Aircraft Co Improvements in or relating to sealing means between relatively movable parts
US3649033A (en) * 1969-12-24 1972-03-14 Nippon Denso Co Honeycomb rotor-sealing device and method of manufacture
US4218066A (en) * 1976-03-23 1980-08-19 United Technologies Corporation Rotary seal
EP0716218A1 (fr) * 1994-12-05 1996-06-12 United Technologies Corporation Virole de compresseur

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10385783B2 (en) 2012-01-23 2019-08-20 MTU Aero Engines AG Turbomachine seal arrangement

Also Published As

Publication number Publication date
EP1711689A1 (fr) 2006-10-18
EP1711689B1 (fr) 2009-04-22
US20070273103A1 (en) 2007-11-29
DE502005007136D1 (de) 2009-06-04
DE102004004915A1 (de) 2005-08-18

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