EP1714006B1 - Systeme amortisseur pour aubes directrices - Google Patents

Systeme amortisseur pour aubes directrices Download PDF

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Publication number
EP1714006B1
EP1714006B1 EP05714933.8A EP05714933A EP1714006B1 EP 1714006 B1 EP1714006 B1 EP 1714006B1 EP 05714933 A EP05714933 A EP 05714933A EP 1714006 B1 EP1714006 B1 EP 1714006B1
Authority
EP
European Patent Office
Prior art keywords
guide vanes
spring
damping arrangement
inner shroud
spring element
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
EP05714933.8A
Other languages
German (de)
English (en)
Other versions
EP1714006A1 (fr
Inventor
Carsten Butz
Werner Humhauser
Patrick Wackers
Walter Waschka
Moritz Wirth
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 EP1714006A1 publication Critical patent/EP1714006A1/fr
Application granted granted Critical
Publication of EP1714006B1 publication Critical patent/EP1714006B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2240/00—Components
    • F05D2240/70—Slinger plates or washers
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a damping arrangement for guide vanes, in particular for guide vanes of 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 guide vanes of compressors of a gas turbine are subjected during operation of the same highly stressful vibrations, so that the guide vanes must be damped to avoid damage.
  • a spring element is disposed in a cavity between the inner shroud of the vanes and a seal carrier.
  • C-shaped springs are used, which have a relatively large radial height. This increases the radial dimension of the gas turbine.
  • the production of the known from the prior art spring elements is relatively expensive, and by the bending processes required in the preparation of the same are also subject to tolerances. This is disadvantageous overall.
  • the document EP 1 441 108 A2 relates to a damping arrangement for guide vanes with a spring element formed as a leaf spring with slots.
  • the spring element has a multiply curved or bent cross-section which leads to a relatively large radial Requires space and can only be produced with a considerable manufacturing effort, eg by rolling or pressing, as well as with considerable shape tolerances.
  • the arrangement of the slots in the leaf spring interior with circumferentially uninterrupted leaf spring edges leads to a limited adaptability to adjacent component surfaces, such as the êtendeckb selected the vanes.
  • the present invention is based on the problem of creating a production-technically simple and functionally precise suspension arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine.
  • the or each spring element is designed as a special leaf spring, wherein the or each spring element designed as a leaf spring has a particularly small radial extent.
  • Each spring element has a plurality of leaf spring sections separated from each other by pairs of opposite sides extending into the spring element and leaving an inner connecting web, and forms a simple, flat sheet metal part in the expanded and thus antspannzen state.
  • leaf springs are clamped between the inner shroud of the vanes and the or each seal carrier. This results in a significant reduction of the radial space required for damping and thus a significant reduction of the radial dulling of the gas turbine.
  • Such designed as a leaf springs spring elements are inexpensive to produce and less subject to tolerances than the C-shaped or otherwise curved Federelenente used for damping according to the prior art.
  • the or each formed as a leaf spring spring element between the inner shroud of the guide vanes and the or each seal carrier is clamped, wherein the leaf spring rests with a central bearing area on the or each seal carrier and with two lateral bearing areas on the inner shroud of the vanes. It is also possible that the leaf spring rests with the central bearing area on the inner cover band of the guide vanes and with the two lateral bearing areas on the or each seal carrier.
  • the leaf spring sections are dimensioned so that each inner shroud of each vane each associated with such a leaf spring portion and bears against the same.
  • Fig. 1 shows a section of a compressor 10 of a gas turbine 11 in the region of two Leitschaufelkränzen 12 and three blade rings 13. In the axial direction or in the direction of flow (arrow 14) alternately vane rings 12 and blade rings 13 are arranged.
  • Each of the vane rings 12 is formed from a plurality of circumferentially spaced vanes 15.
  • the vanes 15 of the vane rings 12 are fixed with a radially outer end 16 to a housing 17 of the compressor 10.
  • the guide vanes 17 of the guide vane rings 12 form an inner cover tape 19.
  • At least one seal carrier 20 for sealing elements 21 is fastened to the inner cover strips 19 of the guide vanes 15.
  • the sealing elements 21 are designed as honeycomb seals which cooperate with rotor discs 22 associated sealing fins 23.
  • this spring element 25 is designed as a C-shaped spring, which causes a relatively large radial height in the region of the inner cover strip 19.
  • the radial height in the region of the inner cover strip 19 and the seal carrier 20 is in Fig. 1 visualized by a double arrow 26.
  • Such a large radial height in the region of the inner cover band causes a large radial height of the entire gas turbine. This is a disadvantage.
  • C-shaped spring elements are tolerant and thus inaccurate.
  • Fig. 2 an exploded view of the damping arrangement
  • Fig. 3 shows a cross section in the region of the inner cover strip of a guide vane by the damping arrangement according to the invention.
  • Fig. 2 shows a section of a vane ring 27 in the region of four vanes 28.
  • a radially outer end 29 of the vanes 28 serves to attach the same to a in Fig. 2 Not illustrated housing of the gas turbine.
  • a seal carrier 32 for sealing elements 33 can be fastened.
  • At least one spring element 34 designed as a leaf spring between the inner shroud 31 of the guide vanes 28 and the seal carrier 33 for damping the guide vanes 28 in the region of the inner shrouds 31.
  • Fig. 3 is designed as a leaf spring spring element 34 is positioned in a cavity 35 between the inner shroud 31 and the seal carrier 32. Due to the small radial extent of the spring element 34 designed as a leaf spring, the cavity 35 can also be designed with a low radial height, so that overall the radial height of the gas turbine is reduced.
  • the spring element 34 can be clamped exactly the other way between the inner end bands 31 of the guide vanes 28 and the seal carrier 32, such that the spring element 34 with the central support region 36 on the inner shroud 31 and the two lateral Support areas 37 and 38 rests against the seal carrier 32.
  • Fig. 2 has designed as a leaf spring spring element 34 has a plurality of, in the illustrated embodiment, four, leaf spring portions 39 which are separated by slots 40 from each other. Accordingly, such a leaf spring section 39 is positioned in the region of each inner cover strip 31 of each guide blade 38. Each vane 28 is therefore individually attenuated in the region of the respective inner cover 31.
  • the individual leaf spring portions 39 are separated from each other by two slots 40, wherein each of the two slots 40 extends from a different side into the spring element 34 inside.
  • the extending from different sides in the spring element 34 slots 40, which two adjacent leaf spring sections 39 separate from each other, end at a distance from each other, so that between these two slots 40, a connecting web between two leaf spring portions 39 remains.
  • the seal assembly according to the invention further comprises securing elements 41 which extend in the circumferential direction and are arranged between the inner shrouds 31 of the guide vanes 28 and the seal carrier 33.
  • the securing elements 41 are designed as securing wires and extend in cross-section laterally next to the or each leaf spring designed as a spring element 34.
  • the securing elements 41 are guided in corresponding recesses 42 and 43 within the inner cover strip 31 and the seal carrier 32.
  • the spring element 34 has angled portions 44, which serve as securing tabs and fix the securing elements 41 in their position.
  • a structurally particularly advantageous damping arrangement is provided for the guide vanes of a gas turbine.
  • Particularly advantageous are the low radial height and ease of manufacture of the spring elements.
  • the spring elements When removed and thus relaxed state, the spring elements are designed as a simple, flat sheet metal part. Therefore, no bending operations are required in the manufacture of the or each spring element.
  • the spring forces or the deformation of the or each spring element are determined inter alia by the contour of the inner cover strip of the guide vanes and by the contour of the or each seal carrier.

Landscapes

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

Claims (11)

  1. Ensemble amortisseur pour aubes directrices, en particulier pour aubes directrices d'une turbine à gaz ou d'un groupe motopropulseur d'avion, les aubes directrices (28) d'une grille d'aubes directrices ou d'une couronne d'aubes directrices (27) étant fixées au niveau d'un carter par des extrémités situées radialement à l'extérieur (29), des extrémités situées radialement à l'intérieur (30) des aubes directrices (28) formant une bande de recouvrement intérieure (31), au moins un support de garniture d'étanchéité (32) étant fixé au niveau de la bande de recouvrement intérieure (31) des aubes directrices (28), au moins un élément formant ressort (34) étant disposé entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32), l'élément ou chaque élément formant ressort (34) étant réalisé sous la forme d'un ressort à lames doté d'entailles (40),
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames présente plusieurs segments de ressort à lames (39) séparés les uns des autres de manière fonctionnelle par des entailles (40) s'étendant par paire à l'intérieur de l'élément formant ressort (34) en partant de côtés opposés et laissant une entretoise de liaison intérieure et forme, à l'état démonté et donc détendu, une pièce de tôle simple, plane.
  2. Ensemble amortisseur selon la revendication 1,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames est disposé dans un espace creux (35) présentant une faible hauteur radiale entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32).
  3. Ensemble amortisseur selon la revendication 1 ou 2,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames est serré entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32).
  4. Ensemble amortisseur selon la revendication 3,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames est serré entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture (32) de telle manière que ledit élément formant ressort repose par une zone d'appui (36) médiane contre le ou chaque support de garniture d'étanchéité (32) et par deux zones d'appui (37, 38) latérales contre la bande de recouvrement intérieure (31) des aubes directrices (28).
  5. Ensemble amortisseur selon la revendication 3,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames est serré entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32) de telle manière que ledit élément formant ressort repose par une zone d'appui (36) médiane contre la bande de recouvrement intérieure (31) des aubes directrices (28) et par deux zones d'appui (37, 38) latérales contre le ou chaque support d'étanchéité (32).
  6. Ensemble amortisseur selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce
    qu'au moins un élément de sécurité (41) est disposé entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32) en plus de l'élément ou chaque élément formant ressort (34).
  7. Ensemble amortisseur selon la revendication 6,
    caractérisé en ce
    que l'élément ou chaque élément de sécurité (41) s'étend dans la direction périphérique, de manière latérale, à côté de l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames.
  8. Ensemble amortisseur selon la revendication 7,
    caractérisé en ce
    que l'élément ou chaque élément de sécurité (41) est réalisé sous la forme d'un fil de sécurité.
  9. Ensemble amortisseur selon l'une quelconque des revendications 5 à 8,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames présente au moins un segment (44) coudé, qui fait office de bride de sécurité pour un élément de sécurité (41).
  10. Ensemble amortisseur selon l'une quelconque des revendications 1 à 9,
    caractérisé en ce
    que l'élément ou chaque élément formant ressort (34) réalisé sous la forme d'un ressort à lames présente une faible extension radiale.
  11. Ensemble amortisseur selon l'une quelconque des revendications 1 à 10,
    caractérisé en ce
    que les segments de ressort à lames (39) présentent des dimensions telles que respectivement un segment de ressort à lames (39) de ce type est associé à chaque bande de recouvrement intérieure (31) de toute aube directrice (28).
EP05714933.8A 2004-02-11 2005-02-04 Systeme amortisseur pour aubes directrices Expired - Fee Related EP1714006B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004006706A DE102004006706A1 (de) 2004-02-11 2004-02-11 Dämpfungsanordnung für Leifschaufeln
PCT/DE2005/000182 WO2005078242A1 (fr) 2004-02-11 2005-02-04 Systeme amortisseur pour aubes directrices

Publications (2)

Publication Number Publication Date
EP1714006A1 EP1714006A1 (fr) 2006-10-25
EP1714006B1 true EP1714006B1 (fr) 2014-01-15

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ID=34801875

Family Applications (1)

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EP05714933.8A Expired - Fee Related EP1714006B1 (fr) 2004-02-11 2005-02-04 Systeme amortisseur pour aubes directrices

Country Status (5)

Country Link
US (1) US8105016B2 (fr)
EP (1) EP1714006B1 (fr)
CA (1) CA2555578A1 (fr)
DE (1) DE102004006706A1 (fr)
WO (1) WO2005078242A1 (fr)

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EP1714006A1 (fr) 2006-10-25
US8105016B2 (en) 2012-01-31
DE102004006706A1 (de) 2005-08-25
WO2005078242A1 (fr) 2005-08-25
CA2555578A1 (fr) 2005-08-25
US20080019836A1 (en) 2008-01-24

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