EP1149985A2 - Structure de virole métallique - Google Patents

Structure de virole métallique Download PDF

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Publication number
EP1149985A2
EP1149985A2 EP01110386A EP01110386A EP1149985A2 EP 1149985 A2 EP1149985 A2 EP 1149985A2 EP 01110386 A EP01110386 A EP 01110386A EP 01110386 A EP01110386 A EP 01110386A EP 1149985 A2 EP1149985 A2 EP 1149985A2
Authority
EP
European Patent Office
Prior art keywords
wall
hollow chamber
housing structure
segmented
chamber structure
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.)
Granted
Application number
EP01110386A
Other languages
German (de)
English (en)
Other versions
EP1149985A3 (fr
EP1149985B1 (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
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 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 housing structure in metal construction for the rotor blade area axial flow through compressor and turbine stages, according to the generic term of claim 1.
  • the housing structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. The mostly hot working gas should generally only be applied to the inner wall of the structure; leakage losses through the structure should be minimized. In non-steady-state operation, it is advantageous if the changes in dimensions of the housing structure, in particular thermally induced, are matched in time and size to those of the bladed rotor.
  • EP-B-0 728 258 relates to a cover band element of a turbine which, together with segments of the same type, forms the inner wall and part of the connecting structure to the outer wall of a wall structure.
  • the segments In order to prevent the segments from getting into the blade tip raceway in places, they are connected to the outer area of the housing structure via a special hook-like geometry on the front and rear edges, which in some cases allow radial movement outwards. Since the inner contour often deviates from the circular shape with a tendency to form polygons, it is difficult to maintain a defined gap. The sealing of the segments with gaps and play is also structurally complex.
  • EP-B-0 781 371 deals with an arrangement for the dynamic control of the blade tip play in gas turbines.
  • the inner wall of the housing structure consists of radially outwardly movable, circumferentially overlapping, arc-shaped curved segments, the movement of which is limited radially inwardly by a circumferential housing structure holding its front and rear edges on one side in the manner of a hook.
  • the segments are prestressed radially inwards against the stop by mechanical spring elements or by gas pressure.
  • the rotor blades have wedge-shaped surfaces on the tip side, which generate a dynamic gas cushion during rapid rotation, the pressure of which should keep the wall segments at a defined, small distance from the blade tips.
  • EP-B-0 616 113 relates to a gas turbine and a method for assembling a seal in this gas turbine. From this patent, it is known, inter alia, to use metallic honeycombs as inlet linings for labyrinth seals.
  • honeycombs are soldered on one side to a flat, metallic support, usually in a closed, ring-shaped geometry, with their openings facing cutting-like, ring-shaped sealing tips.
  • the deformation behavior of the ductile, thin, upright honeycomb walls accelerates any running-in process that may be necessary and protects the sealing tips.
  • the open structure with a large number of chambers increases the sealing effect through flow deflection and swirling.
  • Sandwich-like lightweight structures are preferably used in aircraft and boat construction, in which a relatively thick, light core with a high void volume, e.g. a honeycomb core, is connected and covered on both sides with thin, high-strength, closed walls.
  • the walls When such a structure is bent, the walls become primarily open Loaded in tension or pressure in their plane, the core transfers the forces from wall to wall, especially thrust forces.
  • the walls are preferably made of fiber composite, glued to the core and at least comparable in terms of their thickness and mechanical properties.
  • the object of the invention in it, a housing structure in metal construction for the blade area of 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.
  • connection structure arranged between the segmented inner wall and the closed, load-bearing outer wall and their integral integration.
  • the connecting structure is designed as a filigree, light, hollow chamber structure that occupies practically the entire cavity between the inner and outer walls - for example as a honeycomb structure - and is connected to one or both walls by soldering.
  • the "quasi-flat" connection of the walls makes it possible to impress the shape accuracy of the load-bearing outer wall in all operating states of the segmented inner wall. Warping or "polygonizing" of the inner contour can be avoided in this way.
  • the solder joint Due to its "flat character", the solder joint is optimal in terms of mechanical strength and durability and has no negative influence on the material structure.
  • the filigree connection structure is elastic enough to allow thermal expansion / contraction of the inner wall segments in the circumferential direction without critical constraining forces.
  • the connection structure has a thermally insulating effect, which is due to its high void volume and can also be influenced by the selection of its material.Thus, the inner wall takes on the usually high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for its mechanical properties . 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 of the inner wall is 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 is easily deformable or removable 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 recesses 19 extend upstream 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 may 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)
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
DE10020673 2000-04-27
DE10020673A DE10020673C2 (de) 2000-04-27 2000-04-27 Ringstruktur in Metallbauweise

Publications (3)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2362432B (en) * 2000-05-19 2004-06-09 Rolls Royce Plc Tip treatment bars in a gas turbine engine
WO2008011864A1 (fr) * 2006-07-26 2008-01-31 Mtu Aero Engines Gmbh Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation
EP2050931A2 (fr) * 2007-10-16 2009-04-22 United Technologies Corporation Systèmes et procédés impliquant des joints abradables étanches à l'air
EP2728124A1 (fr) * 2012-10-30 2014-05-07 MTU Aero Engines GmbH Anneau de turbine et turbomachine
WO2014207054A1 (fr) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Turbine à gaz et bouclier thermique pour une turbine à gaz
US10760527B2 (en) 2009-08-17 2020-09-01 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
US11125101B2 (en) 2017-07-04 2021-09-21 MTU Aero Engines AG Turbomachine sealing ring

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0206136D0 (en) * 2002-03-15 2002-04-24 Rolls Royce Plc Improvements in or relating to cellular materials
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
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
EP2075416B1 (fr) * 2007-12-27 2011-05-18 Techspace Aero Procédé de fabrication d'un élément de turbomachine et dispositif ainsi obtenu
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
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
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0728258B1 (fr) 1993-11-08 1998-06-03 United Technologies Corporation Segment d'anneau de renforcement de turbine
EP0616113B1 (fr) 1993-03-01 1998-07-01 General Electric Company Turbine à gaz et procédé pour monter une garniture d'échantéité dans cette turbine à gaz
EP0781371B1 (fr) 1994-08-31 1998-12-23 United Technologies Corporation Procede de commande dynamique du jeu d'extremites

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US3425665A (en) * 1966-02-24 1969-02-04 Curtiss Wright Corp Gas turbine rotor blade shroud
US3728039A (en) * 1966-11-02 1973-04-17 Gen Electric Fluid cooled porous stator structure
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
GB2095749B (en) * 1981-03-25 1984-12-12 Rolls Royce Gas turbine engine having improved resistance for foreign object ingestion damage
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
JP2820655B2 (ja) * 1995-04-28 1998-11-05 三菱重工業株式会社 セグメント型ハニカムろう付法及びハニカムろう付け用治具
US5951892A (en) * 1996-12-10 1999-09-14 Chromalloy Gas Turbine Corporation Method of making an abradable seal by laser cutting
JPH1113404A (ja) * 1997-06-25 1999-01-19 Mitsubishi Heavy Ind Ltd 動翼の翼端シール機構

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0616113B1 (fr) 1993-03-01 1998-07-01 General Electric Company Turbine à gaz et procédé pour monter une garniture d'échantéité dans cette turbine à gaz
EP0728258B1 (fr) 1993-11-08 1998-06-03 United Technologies Corporation Segment d'anneau de renforcement de turbine
EP0781371B1 (fr) 1994-08-31 1998-12-23 United Technologies Corporation Procede de commande dynamique du jeu d'extremites

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2362432B (en) * 2000-05-19 2004-06-09 Rolls Royce Plc Tip treatment bars in a gas turbine engine
WO2008011864A1 (fr) * 2006-07-26 2008-01-31 Mtu Aero Engines Gmbh Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation
US8092148B2 (en) 2006-07-26 2012-01-10 Mtu Aero Engines Gmbh Gas turbine having a peripheral ring segment including a recirculation channel
EP2050931A2 (fr) * 2007-10-16 2009-04-22 United Technologies Corporation Systèmes et procédés impliquant des joints abradables étanches à l'air
EP2050931A3 (fr) * 2007-10-16 2009-12-02 United Technologies Corporation Systèmes et procédés impliquant des joints abradables étanches à l'air
US10760527B2 (en) 2009-08-17 2020-09-01 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
EP2728124A1 (fr) * 2012-10-30 2014-05-07 MTU Aero Engines GmbH Anneau de turbine et turbomachine
US9963993B2 (en) 2012-10-30 2018-05-08 MTU Aero Engines AG Turbine ring and turbomachine
WO2014207054A1 (fr) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Turbine à gaz et bouclier thermique pour une turbine à gaz
US11125101B2 (en) 2017-07-04 2021-09-21 MTU Aero Engines AG Turbomachine sealing ring

Also Published As

Publication number Publication date
JP4572042B2 (ja) 2010-10-27
DE10020673A1 (de) 2001-10-31
DE50104737D1 (de) 2005-01-13
DE10020673C2 (de) 2002-06-27
US6537020B2 (en) 2003-03-25
US20010048876A1 (en) 2001-12-06
JP2002004806A (ja) 2002-01-09
EP1149985A3 (fr) 2003-09-17
EP1149985B1 (fr) 2004-12-08
ATE284480T1 (de) 2004-12-15

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