EP2851518A1 - Modules d'une turbomachine - Google Patents

Modules d'une turbomachine Download PDF

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Publication number
EP2851518A1
EP2851518A1 EP14185872.0A EP14185872A EP2851518A1 EP 2851518 A1 EP2851518 A1 EP 2851518A1 EP 14185872 A EP14185872 A EP 14185872A EP 2851518 A1 EP2851518 A1 EP 2851518A1
Authority
EP
European Patent Office
Prior art keywords
component
segment
component segment
overlapping
elements
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
EP14185872.0A
Other languages
German (de)
English (en)
Other versions
EP2851518B1 (fr
Inventor
Thomas Hess
Manfred Feldmann
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 AG
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 AG filed Critical MTU Aero Engines AG
Publication of EP2851518A1 publication Critical patent/EP2851518A1/fr
Application granted granted Critical
Publication of EP2851518B1 publication Critical patent/EP2851518B1/fr
Not-in-force 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a component system of a turbomachine, in particular an aircraft turbine.
  • the invention further relates to a method for mounting such a component system and a turbomachine with such a component system.
  • a component system of an aircraft turbine which comprises a plurality of component segments each formed as a shroud segments, which are arranged in a housing annularly around a rotor of the aircraft turbine.
  • Each component segment includes two opposing abutment surfaces which, when assembled, abut an associated abutment surface of the respective adjoining component segment.
  • sealing plates are inserted into grooves provided for the individual abutment surfaces for sealing the segmental joints.
  • component segments with simple joints or abutment surfaces and seal the shocks by mounting a circumferential sealing plate on these component segments.
  • component segments are used with permanently attached sealing plates, wherein the sealing plates rest on the respective adjacent component segment or are taken in grooves or brackets.
  • the sealing effect is strongly influenced by the different tolerance chains, so that only a comparatively poor sealing of the segment joints can be achieved.
  • the use of individual sealing sheets leads to a high assembly and disassembly effort and thus to correspondingly high manufacturing and repair costs.
  • Object of the present invention is to provide a component system of the type mentioned, which allows an improved seal and beyond is simpler and less expensive to install.
  • Another object of the invention is to provide a method of assembling such a component system as well as a turbomachine having such a component system.
  • a first aspect of the invention relates to a component system which allows for improved sealing and moreover is simpler and more cost-effective to assemble, in that at least the first component segment and the second component segment for sealing a gap between the abutting surfaces together comprise at least three overlapping elements. It is further provided that each overlap element overlaps in abutting abutting surfaces with the respective other component segment in the radial direction, that at least two of the overlapping elements are formed on the first component segment, that at least one of the overlapping elements is formed on the second component segment and that the overlap element of the second component segment is arranged in abutting abutting surfaces in the axial direction between the overlapping elements of the first component segment.
  • component segments which adjoin one another in the assembled state, each comprise overlapping elements which overlap in the assembled state with the respective other component segment.
  • This segment seal is integrated into the component segments in such a way that at least three overlapping elements are provided per joint or abutting surface pair, at least two of the overlapping elements being attached to the first component segment, ie on the first bank, and at least one of the overlapping elements on the second component segment, that is is formed on the second bank and also between the two overlapping elements of the first component segment.
  • the component system according to the invention has only two such component segments, which complement each other to form a ring.
  • the component system three, four, five, six has seven, eight, nine, ten or more component segments, which are provided in the above manner with overlapping elements.
  • all the component segments of the component system complement each other in the mounted state to form a ring whose center axis preferably runs coaxially to the axis of the rotor of the turbomachine.
  • the alternate arrangement and coverage of the overlap elements has the advantage that the leakage gaps between the abutment surfaces of the component segments are determined at least substantially only by the component segments themselves, but not by other components.
  • the tolerance chain for the individual leakage gaps can be greatly reduced in this way. Due to the alternating arrangement of the overlapping elements can also be achieved that the component elements fix each other and not need to be fixed by additional housing receptacles or the like. This allows a further reduction of the tolerance chain and thus an improved gap seal.
  • At least one of the overlap elements is integrally formed on the relevant component segment and / or is connected by a material fit to the relevant component segment.
  • the overlapping element concerned may be fastened to the relevant component segment by welding, soldering and / or gluing, for example.
  • the two overlapping elements of the first component segment are formed on opposite outer regions of the first component segment and / or that the overlapping element of the second component segment is formed in the axially central region of the second component segment.
  • the overlapping elements jointly at least abdicht the gap between the abutment surfaces in abutting abutting surfaces.
  • the overlapping elements in the assembled state of the component segments together at least substantially cover the impact gap, whereby a particularly high sealing effect is achieved.
  • the overlapping elements if they are mounted at different radial distances or planes, are arranged above or below each other at least in regions. In this way, a kind of labyrinth seal can be generated, whereby a particularly high sealing effect can be achieved.
  • At least one of the overlapping elements is hook-shaped and / or rectangular in cross-section and / or trough-shaped and / or V-shaped and / or U-shaped.
  • the overlapping elements are basically not limited in their shape, a hook-shaped configuration of at least one of the overlapping elements can be used to construct a kind of clip connection between the component segments in a structurally simple manner. After assembly, an undesired relative movement of adjacent component segments in the circumferential direction is thus avoided particularly reliably.
  • at least one of the overlapping elements may be formed rectangular, V-shaped and / or U-shaped, which in addition to a falloptim convinced segment seal additionally increased mechanical stability and protection against unwanted relative movements of the component segments against each other can be ensured.
  • a mechanically particularly stable connection of the component segments is made possible in a further embodiment of the invention in that the first component segment and / or the second Component segment comprises at least one overlap region which is complementary to the associated overlap element of the respective other component segment.
  • the overlapping element of the second component segment has a larger surface area and / or a greater axial extent than the overlapping elements of the first component segment, a particularly good segmental sealing is achieved.
  • first component segment and / or the second component segment is designed as a guide ring segment and / or as a turbine ring segment.
  • advantages of the component system according to the invention for said turbine elements can be realized, in which a reliable sealing of the abutting surfaces between the individual component segments and a simple assembly and disassembly is of particularly high importance.
  • a geometrically particularly exact production with simultaneously low production costs is achieved in a further embodiment of the invention in that at least one of the component segments is produced generatively. It can furthermore be provided that two, several or all component segments of the component system are or are produced generatively.
  • a second aspect of the invention relates to a method for mounting a component system according to the first aspect of the invention in a turbomachine, in which at least the first component segment and the second component segment of the component system are joined such that the abutment surface of the first component segment and the abutment surface of the second component segment abut each other in that the at least two overlapping elements of the first component segment overlap in the radial direction with the second component segment, that the at least one overlapping element of the second component segment overlaps in the radial direction with the first component segment, and in that the overlapping element of the second component segment extends axially between the two overlap elements of the first component segment Component segment is arranged.
  • the at least two component segments are pushed toward one another, so that the overlapping elements come to lie alternately on the respective other component segment in the aforementioned manner.
  • the component system can basically be mounted inside a housing of the turbomachinery or outside be mounted and then mounted in the composite in the housing or installed.
  • a disassembly for example for maintenance, repair or overhaul purposes can accordingly be made in the reverse order or by pulling the component segments in the circumferential direction.
  • a third aspect of the invention relates to a turbomachine, in particular an aircraft engine, which comprises a component system which is designed according to the first aspect of the invention and / or is mounted by means of a method according to the second aspect of the invention.
  • Fig. 1 shows a schematic perspective view of a component system 10 according to a first embodiment of the invention.
  • the component system 10 comprises a plurality of component segments, of which only a first component segment 12a and a second component segment 12b are shown in fragmentary form.
  • the component system 10 is designed as a guide vane of an aircraft turbine (not shown) and comprises further component segments, not shown, which are formed analogously to the component segments 12a, 12b shown and complement each other to form a ring.
  • the component segments are arranged for mounting annularly about an axis of a rotor of the aircraft engine, so that in each case an abutment surface 14a of the first component segment 12a and an abutment surface 14b of the second component segment 12b abut each other.
  • the abutment surfaces 14a, 14b are respectively provided on the narrow sides of the component segments 12a, 12b.
  • the opposing abutment surfaces of the individual component segments 12a, 12b which are not shown, can in principle be identical or complementary to the abutment surfaces 14a, 14b, in order to ensure a mutually secure assembly of all component segments. For assembly all component segments are pushed towards each other in the circumferential direction until their respective abutment surfaces abut each other or abut each other.
  • the component segments 12a, 12b have a total of three overlap elements 16a-c for each abutment surface pairing. It can be seen that the overlapping elements 16a-c in the abutting abutting surfaces 14a, 14b overlap with the respective other component segment 12a, 12b in the radial direction, so that the component segments 12a, 12b only in the circumferential direction, but not in the axial or radial direction relative to each other can be moved.
  • the overlapping element 16a according to arrow Ia is on the associated, complementarily formed overlap region 18a to lie
  • the overlap element 16b comes to lie according to arrow Ib on the associated, complementarily formed overlap region 18b
  • the overlap element 16c comes according to arrow Ic on the associated, complementary formed Overlap area 18c to lie.
  • all the overlapping elements 16a-c are integrally formed with the respective component segment 12a, 12b. This can be achieved in a particularly simple and cost-effective manner, for example by generative production of the component segments 12a, 12b. Furthermore, it is off Fig.
  • the individual overlap element 16b formed in the middle of the second component segment 12b and accordingly in the assembled state between the respective outer overlap elements 16a, 16c of the first component segment 12b is arranged.
  • the second, opposing overlap element 16b has a larger surface area and a greater axial extent than the outer overlap elements 16a, 16c of the first component segment 12a, is formed in another radially outermost plane than the overlap elements 16a, 16c, and a has different geometry than the overlap elements 16a, 16c.
  • the overlapping elements 16a, 16c are cuboid or rectangular in cross-section, while the overlapping element 16b is formed in a trough-shaped or approximately V-shaped cross-section.
  • the segment seal is integrated into the component segments 12a, 12b in such a way that at least three overlap elements 16a-c are provided per joint surface pair, of which two overlap elements 16a, 16c are mounted on the first bank (component segment 12a), while the further overlap element 16b is mounted on the second bank (component segment 12b) and between the two other overlap elements 16a, 16c, so that in the mounted state an alternately overlap results.
  • the leakage gaps are determined only by the component segments themselves, since they are fixed to each other and need not be fixed by housing receivers or the like.
  • the tolerance chain for the leakage gap can thus be reduced.
  • no loose or separate parts are required for the seal. It may in principle be provided that the first component segment 12a and / or the second component segment 12b have one or more further overlap elements.
  • Fig. 2 shows a partially transparent schematic perspective view of the component system 10 according to a second embodiment of the invention.
  • the component system 10 also includes a plurality of component segments, of which only a first component segment 12a and a second component segment 12b are shown in fragmentary form. It can be seen that the component segments 12a, 12b, the first, in the present case V-shaped overlapping element 16a and the second overlapping element 16b have different geometries compared to the preceding embodiment, while the overlapping element 16c is also rectangular in cross-section or rectangular in cross-section.
  • the overlap elements 16a and 16c not integrally formed, but materially connected, for example by welding, soldering or gluing, with the component segment 12a.
  • the second overlapping element 16b can be connected to the component segment 12b by material engagement, for example by welding, soldering or gluing.
  • the component segments 12a, 12b at their radial inner sides sealing elements 20a, 20b which may be formed, for example, as honeycomb seals for turbine blades.
  • the basic principle of the component system 10 with the alternate overlapping of the overlapping elements 16a-c corresponds to that of the preceding embodiment, so that during assembly or during joining of the component segments 12a, 12b according to the arrows IIa-c, a corresponding overlap and segment sealing occurs.
  • deviating geometries of the overlapping elements 16a-c are also conceivable in principle.
  • at least one of the overlapping elements 16a-c may be hook-shaped, so that the component segments 12a, 12b latch when pushed together in the manner of a clip connection and are fixed relative to one another.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14185872.0A 2013-09-23 2014-09-23 Modules d'une turbomachine Not-in-force EP2851518B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013219024.7A DE102013219024A1 (de) 2013-09-23 2013-09-23 Bauteilsystem einer Turbomaschine

Publications (2)

Publication Number Publication Date
EP2851518A1 true EP2851518A1 (fr) 2015-03-25
EP2851518B1 EP2851518B1 (fr) 2019-04-03

Family

ID=51609951

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14185872.0A Not-in-force EP2851518B1 (fr) 2013-09-23 2014-09-23 Modules d'une turbomachine

Country Status (4)

Country Link
US (1) US10047618B2 (fr)
EP (1) EP2851518B1 (fr)
DE (1) DE102013219024A1 (fr)
ES (1) ES2724903T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3363994A1 (fr) * 2017-02-17 2018-08-22 MTU Aero Engines GmbH Agencement d'étanchéité pour une turbine à gaz
WO2019109197A1 (fr) * 2017-12-04 2019-06-13 贵州智慧能源科技有限公司 Carter de turbine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10202857B2 (en) * 2015-02-06 2019-02-12 United Technologies Corporation Vane stages
EP3228826B1 (fr) 2016-04-05 2021-03-17 MTU Aero Engines GmbH Agencement de segments d'étanchéité ayant un connecteur, moteur à turbine à gaz et procédé de fabrication associé
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
DE102021100071A1 (de) 2021-01-05 2022-07-07 Doosan Heavy Industries & Construction Co., Ltd. Gasturbine-Ringanordnung, die Ringsegmente mit integrierter Verbindungsdichtung umfasst
DE102022205646A1 (de) 2022-06-02 2023-12-07 Siemens Energy Global GmbH & Co. KG Dichtungsring mit überlappenden Dichtungsteilen und Rotoranordnung mit einem solchen

Citations (6)

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Publication number Priority date Publication date Assignee Title
FR2521217A1 (fr) * 1982-02-08 1983-08-12 Jehier Sa Perfectionnements aux anneaux isolants pour carters de turbines
EP1013788A1 (fr) 1998-12-22 2000-06-28 General Electric Company Réparation des anneaux de cerclage à haute pression de turbine
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
US6504127B1 (en) * 1999-09-30 2003-01-07 National Research Council Of Canada Laser consolidation methodology and apparatus for manufacturing precise structures
DE102011054654A1 (de) * 2010-10-22 2012-04-26 General Electric Company Dichtungsvorrichtung

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US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
FR2685381B1 (fr) * 1991-12-18 1994-02-11 Snecma Carter de turbine delimitant une veine d'ecoulement annulaire de gaz divisee par des bras radiaux.
US5218816A (en) * 1992-01-28 1993-06-15 General Electric Company Seal exit flow discourager
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US7484936B2 (en) * 2005-09-26 2009-02-03 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US8784041B2 (en) * 2011-08-31 2014-07-22 Pratt & Whitney Canada Corp. Turbine shroud segment with integrated seal

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2521217A1 (fr) * 1982-02-08 1983-08-12 Jehier Sa Perfectionnements aux anneaux isolants pour carters de turbines
EP1013788A1 (fr) 1998-12-22 2000-06-28 General Electric Company Réparation des anneaux de cerclage à haute pression de turbine
US6504127B1 (en) * 1999-09-30 2003-01-07 National Research Council Of Canada Laser consolidation methodology and apparatus for manufacturing precise structures
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
DE102011054654A1 (de) * 2010-10-22 2012-04-26 General Electric Company Dichtungsvorrichtung

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3363994A1 (fr) * 2017-02-17 2018-08-22 MTU Aero Engines GmbH Agencement d'étanchéité pour une turbine à gaz
US10655490B2 (en) 2017-02-17 2020-05-19 MTU Aero Engines AG Seal arrangement for a gas turbine
WO2019109197A1 (fr) * 2017-12-04 2019-06-13 贵州智慧能源科技有限公司 Carter de turbine

Also Published As

Publication number Publication date
DE102013219024A1 (de) 2015-04-09
US10047618B2 (en) 2018-08-14
EP2851518B1 (fr) 2019-04-03
US20150086331A1 (en) 2015-03-26
ES2724903T3 (es) 2019-09-17

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