EP1149985B1 - Structure de virole métallique - Google Patents

Structure de virole métallique Download PDF

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Publication number
EP1149985B1
EP1149985B1 EP01110386A EP01110386A EP1149985B1 EP 1149985 B1 EP1149985 B1 EP 1149985B1 EP 01110386 A EP01110386 A EP 01110386A EP 01110386 A EP01110386 A EP 01110386A EP 1149985 B1 EP1149985 B1 EP 1149985B1
Authority
EP
European Patent Office
Prior art keywords
wall
hollow chamber
segmented
chamber structure
structure according
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
EP01110386A
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German (de)
English (en)
Other versions
EP1149985A3 (fr
EP1149985A2 (fr
Inventor
Werner Humhauser
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
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Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1149985A2 publication Critical patent/EP1149985A2/fr
Publication of EP1149985A3 publication Critical patent/EP1149985A3/fr
Application granted granted Critical
Publication of EP1149985B1 publication Critical patent/EP1149985B1/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
    • 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
    • F01D11/122—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 erodable or abradable material

Definitions

  • the invention relates to a ring structure in metal construction for the blade area axial flow through compressor and turbine stages, according to the generic term of claim 1.
  • the wall structure should initially be sufficiently dimensionally stable and be geometrically accurate. Thermal and mechanical influences should affect the geometry change as little as possible. With the mostly hot working gas, i.w. only the inside of the structure must be acted on, leakage losses through the structure are to be minimized. In transient operation, it is advantageous if the particular thermally induced dimensional changes in the wall structure in terms of time and size those of the bladed rotor are aligned. Because there are mechanical contacts between the blade tips and the wall structure under special loads can hardly be avoided, the inside of the wall structure should at least blade tip deformable / resilient or abradable.
  • EP-B-0 728 258 relates to a shroud element of a turbine, which together with similar segments the inner wall and part of the connecting structure to the outer wall of a wall structure. Due to temperature differences between Inside and cooled outside of the segments in operation and as a result of different material behavior of the base material and one as a rule The existing coating tends to change the curvature of the segments. To prevent the segments from getting into the blade tip raceway they have a special, hook-like geometry on the front and Trailing edge connected to the outer area of the housing structure, which radial outward movement in places. Because the inner contour often deviates from the circular shape with a tendency to form polygons, is a defined one Difficult to keep gaps. The sealing of the segments with gaps and play is constructively also complex.
  • EP-B-0 781 371 deals with an arrangement for dynamic control of the Blade tip play in gas turbines.
  • the inner wall of the housing structure is there from radially outward-moving, circular arc-shaped overlapping in the circumferential direction curved segments whose movement radially inwards through one of their Front and rear edge hook-like, surrounding housing structure on one side is limited.
  • the segments are made by mechanical spring elements or by Gas pressure biased radially inwards against the stop.
  • the blades have wedge surfaces on the tip side, which, when rotating faster, a dynamic gas cushion generate, the pressure of the wall segments at a defined, small distance should stick to the blade tips.
  • the holding structure of the segments is exposed to the working gas and thus possibly subjected to high thermal loads, whereby they also contain a considerable amount of heat leads to the outer wall of the structure.
  • EP-B-0 616 113 relates to a gas turbine and a method for assembling one Seal in this gas turbine. From this patent, it is i.a. known, metallic Honeycombs to be used as inlet coverings for labyrinth seals.
  • the honeycomb are soldered on one side to a flat, metallic carrier, usually in ring-shaped closed geometry, its openings being cutting-like, ring-shaped Sealing tips are facing.
  • the deformation behavior of the ductile, thin, Upright honeycomb walls accelerate any necessary running-in process and protects the sealing tips.
  • the open structure with a variety of Chambers increase the sealing effect through flow deflection and swirling.
  • Sandwich-like lightweight structures are preferred in aircraft and boat construction uses a relatively thick, light core with a high empty volume, e.g. a honeycomb core, with thin, high-strength, closed on both sides Walls connected and covered
  • a relatively thick, light core with a high empty volume e.g. a honeycomb core
  • thin, high-strength closed on both sides Walls connected and covered
  • the walls are preferred in Fiber composite construction, glued to the core and in terms of its thickness and mechanical properties at least comparable.
  • DE-A-15 51 183 relates to composite sealing components for gas turbine engines. Such components are also used in specialist circles as jacket rings or liners referred to and are arranged around blade rings, in particular with the function of the blade tip seal. With regard to easy assembly and unimpeded thermal expansion, the liners are mostly segmented and left unchanged arranged by expansion joints.
  • the sealing components according to this published specification are in sandwich construction with a metallic honeycomb core and with these metallic walls / sheets covering on both sides, hence the expression "Composed”.
  • the inner, abradable wall (layer 58 ') can on the Angled edges of the sealing component up to the outer wall (rear layer 50 ') and connected to the latter by soldering (60) (see page 9 from the eighth last line).
  • the sealing components form either curved segments, such as shown in the figures, or complete rings (see page 10, lines 1 to 6).
  • the outer and inner walls are inevitably interrupted, i.e. segmented, in the second case none of the walls is segmented.
  • the Indicates a direct soldering of the outer and inner wall in the edge area there is no evidence of the type of connection between the walls and the Honeycomb core.
  • the outer wall is with flanges (52,53) so that they can be hung on the engine housing (11).
  • the outer wall (rear layer) of each sealing component is therefore not a housing wall.
  • the design of the core layer is limited to honeycomb material.
  • the object of the invention is based on the cited prior art in it, a ring structure in metal construction for the blade area from axial flow through compressor and turbine stages, which are characterized by a high Dimensional and shape accuracy under changing operating conditions and temperatures, high mechanical load bearing capacity, good thermal insulation as well as a minimal working fluid leakage due to the structure and through particularly small, little changing gaps to the blade tips enables a high level of efficiency or a high level of load.
  • the invention is thus in the combination of a segmented inner wall, one closed, formed by a housing wall, supporting outer wall, one connecting structure arranged between the walls and from their material connection See integration by soldering.
  • the connection structure is in itself known as filigree, light, practically the entire cavity between Hollow chamber structure occupying inner and outer wall - for example as a honeycomb structure - and connected to one or both walls by soldering. Due to the "quasi-flat" connection of the walls, it is possible to achieve dimensional accuracy the load-bearing outer wall in all operating states of the segmented Imprint on the inner wall. A warping or "polygonizing" of the inner contour leaves avoid yourself.
  • the solder connection is optimal due to its "flat character" in terms of mechanical strength and durability and has no negative Influence on the material structure.
  • the filigree connection structure elastic enough to accommodate thermal expansions / contractions of the inner wall segments in the circumferential direction without allowing critical constraining forces.
  • the connection structure has a thermally insulating effect, which is due to its high empty volume and can also be influenced by the selection of its material the inner wall assumes the mostly high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for their mechanical Properties is. Of course, the insulation effect is also good for the thermodynamic Efficiency of the machine.
  • the filigree connection structure is practically impermeable to gas in the circumferential and axial direction, so that additional sealing measures are not required. The leakage through the few, small expansion joints on the inner wall are of no importance.
  • Preferred embodiments of the housing structure are characterized in the subclaims.
  • the housing structure according to FIG. 1 is part of an axial compressor which runs from left to right to be flowed through on the right.
  • the radially outer part of a guide vane can be seen 21 and a shroud-less blade 20.
  • the outer wall 3 of the Housing structure extends over both blade areas, with the suspension the guide blade 21 in a form-fitting manner, i.e. is conventional.
  • the housing structure according to the invention 1 is on the right in the figure, i.e. in the area of the blade 20, and comprises an inner wall 5, a hollow chamber structure 10 and that of the inner wall 5 opposite part of the outer wall 3, i.e. the right part by Flange.
  • the inner wall 5 is to protect the blade tips when brushing provided with an inlet covering 9.
  • the inner wall 5 including the inlet covering 9 is segmented, i.e. it has several, at least distributed over the circumference predominantly axially extending expansion joints 7 (see Fig. 2).
  • the housing structure 1 represents an integral structure with a material connection of its elements 3, 5 and 10.
  • the hollow chamber structure 10 is with the outer wall 3 and with the inner wall 5 soldered. It is also possible to use one of the hollow chamber structures to manufacture both walls in one piece and then to solder them to the other wall.
  • FIG. 2 shows two different housing structures 1, 2 according to the invention in partial cross section, on the right or left side of a vertical, dash-dotted line in the middle of the drawing.
  • the right housing structure 1 corresponds to that from FIG. 1, an expansion joint 7 running through the inner wall 5 and the inlet covering 9 being evident.
  • the left housing structure 2 initially differs from the right one in that its inner wall 6 consists of a material that can be easily deformed or removed by the blade tips over the entire thickness. This can be a porous metal without or with embedded plastic, graphite or other substances, for example in the form of a sintered structure.
  • the outer wall 4 and the hollow chamber structure 11 have no special features compared to the corresponding positions 3 and 10.
  • the inner wall 6 is provided with geometrically defined openings 8 distributed uniformly over the circumference.
  • recesses 19 interact with the openings 8 and form recirculation chambers for part of the compressor flow in the area of the blade tips.
  • the openings 8 and cutouts 19 extend upstream to in front of the blade entry edges, downstream they end behind the axial center of the blade and in front of the blade exit edges. This is familiar to the person skilled in the art and is therefore not shown separately.
  • the recesses in the hollow chamber structure do not necessarily have to extend radially to the outer wall. It is conceivable to level the partially recessed hollow chamber structure with a filling material, ie to smooth it out in terms of flow technology. It can also be favorable to orient the longitudinal center planes of the openings and cutouts not radially, but rather inclined in the circumferential direction. All of this is clear to the person skilled in the art even without a separate illustration.
  • FIG. 3 shows an example of three different hollow chamber structures 12, 13 and 14 in sections parallel to the inner and outer wall of the housing structure.
  • On the left is a honeycomb structure with equilateral, hexagonal honeycombs, the coherent wall elements 15 of which are geometrically the same size and are at 120 ° angles to one another.
  • the middle structure 13 has rectangular chambers, which are delimited by smaller wall elements 16 and larger wall elements 17 in a rectangular arrangement.
  • the right structure 14 is similar to the left structure 12, but at 14 the hollow chambers have a round - instead of a hexagonal - shape. This results in wall elements 18 with locally different thicknesses.
  • the hollow chamber structure 14 can be produced, for example, by mechanical or electrochemical drilling in an initially thick-walled solid material.
  • the inner or outer wall can be produced in one piece with the hollow chamber structure, the other wall being integrated by soldering.
  • the more delicate structures 12 and 13 are rather manufactured separately from sheet metal strips, expanded metal or the like.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Joining Of Building Structures In Genera (AREA)

Claims (6)

  1. Structure de virole métallique (1, 2) pour la zone d'aubes mobiles d'étages de compresseurs et de turbines traversés axialement, en particulier dans des groupes motopropulseurs de turbines à gaz, comprenant une paroi extérieure (3, 4) de forme annulaire circulaire, une paroi intérieure (5, 6) de forme annulaire circulaire et se trouvant à faible distance radiale par rapport aux extrémités des aubes mobiles, et une structure d'assemblage transmettant les charges, au moins dans le sens radial, entre la paroi intérieure et la paroi extérieure, où une structure à chambres creuses (10, 11, 12, 13, 14) subdivisée de façon multiple - servant de structure d'assemblage - est disposée en s'étendant au moins sur la majeure partie des zones de surface, tournées l'une vers l'autre, de la paroi intérieure et de la paroi extérieure,
    caractérisée
    en ce que la paroi extérieure (3, 4) est une paroi d'enveloppe fermée, mécaniquement stable, de l'étage des compresseurs ou des turbines,
    en ce que la paroi intérieure ( 5, 6), sur sa circonférence, est interrompue - c'est-à-dire segmentée
    à plusieurs reprises par des joints de dilatation (7) s'étendant de façon axiale ou principalement de façon axiale, et
    en ce que la structure à chambres creuses (10, 11, 12, 13, 14) est assemblée par brasage à la paroi intérieure (5, 6) et/ou à la paroi extérieure (3, 4).
  2. Structure de virole selon la revendication 1, caractérisée en ce que la paroi intérieure segmentée (5) est dotée, côté aubes, d'une couche mince se présentant sous la forme d'un revêtement d'entrée (9) pouvant être déformé ou enlevé des extrémités des aubes, mécaniquement, par contact.
  3. Structure de virole selon la revendication 1, caractérisée en ce que la paroi intérieure segmentée (6) est réalisée complètement, c'est-à-dire dans la totalité de sa section de matériau, comme un revêtement d'entrée, de préférence sous la forme d'un corps métallique poreux, avec ou sans inclusions d'une autre matière telle que de la matière plastique ou du carbone.
  4. Structure de virole selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la paroi intérieure segmentée (6), indépendamment des joints de dilatation (7) s'étendant au moins principalement de façon axiale, est dotée de percées (8) géométriquement définies et réparties sur sa circonférence, où la structure à chambres creuses (11), dans la zone des percées (8), est placée en retrait ou évidée (19).
  5. Structure de virole selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la structure à chambres creuses (12) est réalisée comme une structure en nid d'abeilles.
  6. Structure de virole selon l'une quelconque des revendications 1 à 5, caractérisée en ce que la structure à chambres creuses (14), en tant que pièce de structure intégrée de la paroi intérieure (5, 6) ou de la paroi extérieure (3, 4), est produite en procédant par enlèvement, par exemple par fraisage, par perçage ou par enlèvement électrochimique.
EP01110386A 2000-04-27 2001-04-26 Structure de virole métallique Expired - Lifetime EP1149985B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10020673A DE10020673C2 (de) 2000-04-27 2000-04-27 Ringstruktur in Metallbauweise
DE10020673 2000-04-27

Publications (3)

Publication Number Publication Date
EP1149985A2 EP1149985A2 (fr) 2001-10-31
EP1149985A3 EP1149985A3 (fr) 2003-09-17
EP1149985B1 true EP1149985B1 (fr) 2004-12-08

Family

ID=7640124

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01110386A Expired - Lifetime EP1149985B1 (fr) 2000-04-27 2001-04-26 Structure de virole métallique

Country Status (5)

Country Link
US (1) US6537020B2 (fr)
EP (1) EP1149985B1 (fr)
JP (1) JP4572042B2 (fr)
AT (1) ATE284480T1 (fr)
DE (2) DE10020673C2 (fr)

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US6935836B2 (en) * 2002-06-05 2005-08-30 Allison Advanced Development Company Compressor casing with passive tip clearance control and endwall ovalization control
DE102004010236A1 (de) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Ringstruktur in Metallbauweise
DE102006034424A1 (de) * 2006-07-26 2008-01-31 Mtu Aero Engines Gmbh Gasturbine
JP2008180149A (ja) * 2007-01-24 2008-08-07 Mitsubishi Heavy Ind Ltd ガスタービンの翼構造及びガスタービン
US8038388B2 (en) * 2007-03-05 2011-10-18 United Technologies Corporation Abradable component for a gas turbine engine
US8061978B2 (en) * 2007-10-16 2011-11-22 United Technologies Corp. Systems and methods involving abradable air seals
EP2075416B1 (fr) * 2007-12-27 2011-05-18 Techspace Aero Procédé de fabrication d'un élément de turbomachine et dispositif ainsi obtenu
US8739513B2 (en) 2009-08-17 2014-06-03 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
US9062565B2 (en) * 2009-12-31 2015-06-23 Rolls-Royce Corporation Gas turbine engine containment device
JP4916560B2 (ja) * 2010-03-26 2012-04-11 川崎重工業株式会社 ガスタービンエンジンの圧縮機
GB201016335D0 (en) * 2010-09-29 2010-11-10 Rolls Royce Plc Endwall component for a turbine stage of a gas turbine engine
EP2679777A1 (fr) * 2012-06-28 2014-01-01 Alstom Technology Ltd Compresseur pour turbine à gaz et procédé de réparation et/ou modification de la géométrie et/ou l'entretien du dit compresseur
ES2705532T3 (es) 2012-10-30 2019-03-25 MTU Aero Engines AG Anillo de turbina y turbomáquina
DE102013212741A1 (de) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Gasturbine und Hitzeschild für eine Gasturbine
DE202013010937U1 (de) 2013-11-30 2015-03-02 Oerlikon Leybold Vacuum Gmbh Rotorscheibe sowie Rotor für eine Vakuumpumpe
DE102015224160A1 (de) 2015-12-03 2017-06-08 MTU Aero Engines AG Einlaufbelag für eine äußere Luftdichtung einer Strömungsmaschine
US10422348B2 (en) * 2017-01-10 2019-09-24 General Electric Company Unsymmetrical turbofan abradable grind for reduced rub loads
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
DE102018208040A1 (de) * 2018-05-23 2019-11-28 MTU Aero Engines AG Dichtungsträger und Strömungsmaschine
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US11674405B2 (en) 2021-08-30 2023-06-13 General Electric Company Abradable insert with lattice structure

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Also Published As

Publication number Publication date
JP2002004806A (ja) 2002-01-09
DE50104737D1 (de) 2005-01-13
DE10020673C2 (de) 2002-06-27
DE10020673A1 (de) 2001-10-31
EP1149985A3 (fr) 2003-09-17
US6537020B2 (en) 2003-03-25
JP4572042B2 (ja) 2010-10-27
US20010048876A1 (en) 2001-12-06
EP1149985A2 (fr) 2001-10-31
ATE284480T1 (de) 2004-12-15

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