EP1711689B1 - Ensemble d' étanchéité - Google Patents

Ensemble d' étanchéité Download PDF

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Publication number
EP1711689B1
EP1711689B1 EP05706719A EP05706719A EP1711689B1 EP 1711689 B1 EP1711689 B1 EP 1711689B1 EP 05706719 A EP05706719 A EP 05706719A EP 05706719 A EP05706719 A EP 05706719A EP 1711689 B1 EP1711689 B1 EP 1711689B1
Authority
EP
European Patent Office
Prior art keywords
rotor
walls
honeycomb
sealing
rotation
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 - Fee Related
Application number
EP05706719A
Other languages
German (de)
English (en)
Other versions
EP1711689A1 (fr
Inventor
Reinhold Meier
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.)
MTU Aero Engines AG
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
Publication of EP1711689A1 publication Critical patent/EP1711689A1/fr
Application granted granted Critical
Publication of EP1711689B1 publication Critical patent/EP1711689B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/001—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 components, such as, inter alia, a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines.
  • the preferably several turbines are, in particular, a high-pressure turbine and a low-pressure turbine, with the plurality of compressors in particular a high-pressure compressor and a low-pressure compressor.
  • a plurality of guide vane rings are positioned behind one another in the axial direction or in the direction of flow of the gas turbine, each guide vane ring having a plurality of guide vanes distributed over the circumference.
  • each a rotor blade ring is positioned, which has a plurality of blades. The blades are associated with a rotor and rotate together with the rotor relative to a fixed housing and the also stationary formed vanes of the vane rings.
  • the walls, which 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 walls of the honeycomb cells extending transversely to the direction of rotation of the sealing fins.
  • the rotor rubs against the stator-side honeycomb seal
  • the rotor accordingly strikes the walls of the honeycomb sealing cells running transversely to the direction of rotation of the rotor in the axial direction of view, as a result of which a rotation or rotation of the rotor is opposed by a resisting force.
  • walls of the honeycomb cells extending in this way are relatively stiff, as a result of which the walls of the honeycomb sealing cells do not deform as much as possible.
  • the rotor, in particular the sealing fins runs into the honeycomb seal, according to the prior art, the walls of the honeycomb sealing cells are at least partially removed. In this case, therefore, the honeycomb seal is damaged and the gap to be sealed increases, which is disadvantageous overall.
  • the document GB 793 886 A relates to a seal assembly for a rotor / stator seal, in which the stator is associated with a honeycomb seal with a plurality of honeycomb seal cells.
  • the walls of the honeycomb cells can be vertical or radial (FIG. FIG. 1 ) or inclined ( FIG. 2 ) may be arranged on a support.
  • the honeycomb sealing cells are arranged on the inside of an annular carrier inclined in the circumferential direction, deviating from the radial seal.
  • the open ends of the cells have obliquely in the direction of rotation of the sealed blade tips.
  • the cell walls can deform without being removed immediately, which also protects the blade tips.
  • the disadvantage here is the elaborate production of a honeycomb structure with a defined inclination of each complete honeycomb cell.
  • the document EP-A-0 716 218 relates to a housing structure for the compressor of a gas turbine in the form of a honeycomb configuration, the honeycomb cells are inclined with the open ends opposite to the direction of rotation of the blades.
  • the purpose of the cells is to energize the sluggish blade tip flow and thereby increase the stall margin of the compactor.
  • Such a structure is often referred to as casing treatment.
  • the squeal behavior of such a geometry is very unfavorable, since the cell walls set up radially inwardly on blade contact and penetrate even deeper into the blade path.
  • a honeycomb seal for the production of which sheets are provided with deep nubs (embossed sheet) and applied to a carrier, the still closed nubs protruding from the carrier. Then the studded floors are removed, creating honeycomb cells with curved or arched walls. These are perpendicular to the carrier.
  • the present invention is based on the problem to provide a simplified seal arrangement, in particular for a gas turbine or an aircraft engine, with favorable Anstreif .
  • a sealing arrangement according to claim 1.
  • at least the transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set radially obliquely in the direction of rotation of the rotor.
  • a deformability of the walls of the honeycomb sealing cells is provided, so that when rubbing the rotor, in particular the rotor-side sealing fins, in the honeycomb seal a removal or cracking of the walls is avoided.
  • the present sealing arrangement therefore, an effective sealing of a gap between a rotor and a stator is possible.
  • the transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set in the direction of rotation of the rotor so inclined that the rotor facing edges of these walls are offset from the rotor facing edges of these walls in the direction of rotation of the rotor.
  • the edges of these walls facing the rotor are curved, the edges of these walls facing away from the rotor extending in a straight line.
  • This geometry makes it possible, for example, to start from a sheet metal structure with square or rectangular honeycomb seal cells and to permanently deform a part of the cell walls. This is much easier than making oblique honeycombs.
  • the walls of the honeycomb sealing cells extending transversely to the direction of rotation of the rotor are inclined as well.
  • FIGS. 5 and 6 Embodiments of the present invention will be explained in more detail below with reference to FIG Fig. 1 to 4 two known from the prior art sealing arrangements will be described.
  • FIG. 1 and 2 highly schematic of a honeycomb seal 10 of a seal assembly according to the prior art between a non-illustrated rotor and a likewise not shown stator of a gas turbine.
  • Fig. 1 shows a schematic side view of the honeycomb seal 10 in the axial direction
  • Fig. 2 shows a schematic plan view the same in the radial direction.
  • the X-coordinate of the represented coordinate systems is the radial direction
  • the Y-coordinate is the circumferential direction
  • the Z-coordinate the axial direction is visualized.
  • the axial direction according to Fig. 1 one sees therefore on the XY-plane, in radial direction according to Fig. 2 you can see the YZ-plane.
  • the honeycomb seal 10 is formed by a plurality of honeycomb seal cells 11, wherein the honeycomb seal cells 11 in FIG Fig. 1 and 2 have a rectangular cross-sectional area. It should be noted at this point that the honeycomb seals can of course also have a hexagonal cross-sectional profile.
  • honeycomb seal cells 11 of the honeycomb seal 10 are bounded by a plurality of walls. For the purposes of the present invention is to be distinguished between such walls which extend transversely or longitudinally to the direction of rotation of a rotor.
  • the direction of rotation of a non-illustrated rotor is in Fig. 1 and 2 illustrated with an arrow 12.
  • Walls of the honeycomb sealing cells 11 extending transversely to the direction of rotation 12 are identified by the reference numeral 13
  • walls of the honeycomb sealing cells 11 running longitudinally or parallel to the direction of rotation 12 are identified by the reference numeral 14.
  • Fig. 1 can be removed, extend according to the prior art, the transverse to the direction of rotation 12 of the rotor walls 13 of the honeycomb sealing cells 11 exactly in the radial direction, so that the same in the axial direction of the Fig. 1 are aligned perpendicular to the direction of rotation 12 of the rotor.
  • the walls 13 running transversely to the direction of rotation of the rotor form a resistance for the rotor 12, since walls 13 formed in this way are relatively stiff and can only slightly deform, if at all. When rubbing the rotor in the same direction transverse to the direction of rotation walls 13, these are therefore removed and thus damaged.
  • the honeycomb seal 15 of 3 and 4 shows a honeycomb seal 15 of a further seal arrangement according to the prior art in different representations or viewing directions, the viewing directions of 3 and 4 the views of the Fig. 1 and 2 correspond.
  • the honeycomb seal 15 of 3 and 4 consists of several honeycomb sealing cells 16, wherein the honeycomb sealing cells 16 have a rectangular contour in cross section.
  • the honeycomb cells 16 are in turn bounded by several walls, which are aligned optimally relative to the direction of rotation (arrow 17) of a rotor.
  • the transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set obliquely so that a rotor facing edge 20 is offset from the rotor facing away from the edge 21 in the direction of rotation of the rotor, which means that the edge facing the rotor 20th is positioned in the direction of rotation 17 to the front or downstream of the edge 21 facing away from the rotor.
  • the offset edges 20 and 21 of the transverse to the direction of rotation 17 of the rotor walls 18 are shown as parallel lines. The edges 20, 21 of the walls 18 thus run straight.
  • the production of such precise, obliquely employed honeycomb cells is complex.
  • FIGS. 5 and 6 show two embodiments of inventive honeycomb seals or sealing arrangements.
  • Fig. 5 differs from the known version of the 3 and 4 in that in the honeycomb seal 22 of the Fig. 5 the rotor-facing edges 20 of the transverse to the direction of rotation 17 of the rotor walls 18 are not rectilinear, but rather are curved or curved. The curvature runs in the direction of rotation 17 of the rotor. The edges facing away from the rotor 21 of the transverse to the direction of rotation of the rotor walls 18, however, are rectilinear.
  • Fig. 6 shows a further embodiment of a honeycomb seal 23 according to the invention, wherein in the honeycomb seal 23 according to Fig. 6 in addition to the transverse to the direction of rotation 17 of the rotor walls 18 extending in the direction of rotation of the rotor walls 19 of the honeycomb sealing cells 16 are inclined.
  • the edges thereof offset from each other so that a rotor facing edge 24 of the walls 19 is offset from a rotor 25 facing away from the edge, wherein in the embodiment of Fig. 6 the rotor facing edge 24 is curved and facing away from the rotor edge 25 is rectilinear.
  • the flexibility of the honeycomb sealing cells 16 or the walls 18, 19 of the honeycomb sealing cells 16 can be optimized once again.
  • the embodiments shown have in common that at least the transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set radially obliquely in the direction of rotation of the rotor.
  • the edges 20, 21 extend on the one hand straight, on the other curved. In this way, a good elastic and plastic deformability of the walls of the honeycomb seal cells is made possible, without damaging or removing the walls of the honeycomb seal cells when the rotor or rotor-side sealing fins are rubbed into the honeycomb seal. The stress of the honeycomb seal can thus be reduced, thereby increasing the life of the same.
  • the sealing arrangement according to the invention serves, in particular, for sealing a radial gap between radially inner ends of guide vanes and a rotor.
  • the honeycomb seals are then assigned to the radially inner ends of the guide vanes or corresponding inner end tapes of the guide vanes, the sealing fins associated with the rotor interacting with the honeycomb seal. It is also possible to seal a gap between the radially outer ends of the rotating blades and a fixed housing with such a sealing arrangement.
  • the use of the sealing arrangement in the compressor area or turbine area of a gas turbine, in particular of 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)

Claims (5)

  1. Garniture d'étanchéité, en particulier pour une turbine à gaz telle qu'un réacteur d'avion, pour combler un interstice entre un rotor et un stator, en particulier pour combler un interstice entre des extrémités radialement intérieures d'aubes fixes et un rotor et/ou un interstice entre des extrémités radialement extérieures d'aubes rotatives et un carter fixe, où un joint alvéolaire (15) comprenant plusieurs cellules (16) de joint alvéolaire est affecté au stator, où les cellules (16) de joint alvéolaire sont séparées les unes des autres par des cloisons (18, 19), et où au moins les cloisons (18) des cellules (16) de joint alvéolaire s'étendant transversalement à la direction de rotation (17) du rotor sont inclinées de manière à décaler en direction de rotation (17) des bords (20) desdites cloisons (18) opposés au rotor relativement à des bords (21) desdites cloisons (18) éloignés du rotor, caractérisée en ce que les bords (21) desdites cloisons (18) éloignés du rotor s'étendent en ligne droite, et en ce que les bords (20) desdites cloisons (18) opposés au rotor sont courbés ou cintrés, la courbure desdites cloisons (18) s'étendant dans la direction de rotation (17) du rotor.
  2. Garniture d'étanchéité selon la revendication 1,
    caractérisée en ce que
    les cloisons (19) des cellules (16) de joint alvéolaire s'étendant dans la direction de rotation (17) du rotor sont également inclinées, en plus des cloisons (18) des cellules (16) de joint alvéolaire s'étendant transversalement à la direction de rotation (17) du rotor.
  3. Garniture d'étanchéité selon la revendication 2,
    caractérisée en ce que
    les bords (24) desdites cloisons (19) opposés au rotor sont décalés relativement à des bords (25) desdites cloisons (19) éloignés du rotor.
  4. Garniture d'étanchéité selon la revendication 3,
    caractérisée en ce que
    les bords (25) desdites cloisons (19) éloignés du rotor s'étendent en ligne droite.
  5. Garniture d'étanchéité selon la revendication 4,
    caractérisée en ce que
    les bords (24) desdites cloisons (19) opposés au rotor sont courbés ou cintrés.
EP05706719A 2004-01-31 2005-01-28 Ensemble d' étanchéité Expired - Fee Related EP1711689B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004004915A DE102004004915A1 (de) 2004-01-31 2004-01-31 Dichtungsanordnung
PCT/DE2005/000131 WO2005073518A1 (fr) 2004-01-31 2005-01-28 Ensemble d'étanchéité

Publications (2)

Publication Number Publication Date
EP1711689A1 EP1711689A1 (fr) 2006-10-18
EP1711689B1 true EP1711689B1 (fr) 2009-04-22

Family

ID=34801375

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05706719A Expired - Fee Related EP1711689B1 (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)

Families Citing this family (4)

* 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
DE102012200883B4 (de) 2012-01-23 2015-12-03 MTU Aero Engines AG Strömungsmaschinen-Dichtungsanordnung
WO2017095926A1 (fr) 2015-12-01 2017-06-08 Saint-Gobain Performance Plastics Corporation Joints annulaires
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

Family Cites Families (5)

* 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
US4477089A (en) * 1982-07-26 1984-10-16 Avco Corporation Honeycomb seal for turbine engines
US5520508A (en) * 1994-12-05 1996-05-28 United Technologies Corporation Compressor endwall treatment

Also Published As

Publication number Publication date
EP1711689A1 (fr) 2006-10-18
US20070273103A1 (en) 2007-11-29
WO2005073518A1 (fr) 2005-08-11
DE102004004915A1 (de) 2005-08-18
DE502005007136D1 (de) 2009-06-04

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