EP1714006A1 - Systeme amortisseur pour aubes directrices - Google Patents

Systeme amortisseur pour aubes directrices

Info

Publication number
EP1714006A1
EP1714006A1 EP05714933A EP05714933A EP1714006A1 EP 1714006 A1 EP1714006 A1 EP 1714006A1 EP 05714933 A EP05714933 A EP 05714933A EP 05714933 A EP05714933 A EP 05714933A EP 1714006 A1 EP1714006 A1 EP 1714006A1
Authority
EP
European Patent Office
Prior art keywords
guide vanes
damping arrangement
designed
leaf spring
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.)
Granted
Application number
EP05714933A
Other languages
German (de)
English (en)
Other versions
EP1714006B1 (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 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 EP1714006A1 publication Critical patent/EP1714006A1/fr
Application granted granted Critical
Publication of EP1714006B1 publication Critical patent/EP1714006B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 blades, in particular for guide blades of a gas turbine or an aircraft engine, according to the preamble of claim 1.
  • Gas turbines consist of several assemblies, for example a fan, a combustion chamber, preferably several compressors and several turbines.
  • the preferably several turbines are, in particular, a high-pressure turbine and a low-pressure turbine, and the several compressors are in particular a high-pressure compressor and a low-pressure compressor.
  • a plurality of guide vane rings are positioned one behind the other in a turbine and a compressor of a gas turbine in the axial direction or in the flow direction of the gas turbine, each guide vane ring having a plurality of guide vanes which are arranged distributed over the circumference.
  • a rotor blade ring which has a plurality of rotor blades, is positioned between each two adjacent guide vane rings. The rotor blades are assigned to a rotor and rotate together with the rotor with respect to a fixed housing and also the guide vanes of the guide vane rings, which are also designed to be stationary.
  • the guide vanes of compressors of a gas turbine are subject to high stressing vibrations during their operation, so that the guide vanes must be damped to avoid damage to them.
  • C-shaped springs are used which have a relatively large radial height. This increases the radial dimension of the gas turbine.
  • the manufacture of the spring elements known from the prior art is comparatively complex, and due to the bending processes required in the manufacture thereof, they are also subject to tolerances. Overall, this is a disadvantage.
  • the present invention is based on the problem of creating a novel damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine.
  • This problem is solved by a damping arrangement according to claim 1.
  • the or each spring element is designed as a leaf spring, the or each spring element designed as a leaf spring having a small radial extension.
  • leaf springs as spring elements.
  • the leaf springs are clamped between the inner shroud of the guide vanes and the or each seal carrier. This results in a significant reduction in the radial installation space required for damping and thus a significant reduction in the radial dimensions of the gas turbine.
  • Such spring elements designed as leaf springs are inexpensive to manufacture and less tolerant than the C-shaped spring elements used in the prior art for damping.
  • the or each spring element designed as a leaf spring is preferably clamped between the inner shroud of the guide vanes and the or each seal carrier, the leaf spring resting with a central contact area on the or each seal carrier and with two lateral contact areas on the inner cover band of the guide vanes. It is also possible for the leaf spring to bear on the inner shroud of the guide vanes with the central contact area and on the or each seal carrier with the two lateral contact areas.
  • the or each spring element designed as a leaf spring has a plurality of leaf spring sections separated by slots, such a leaf spring section being associated with each inner shroud of each guide vane and abutting the same.
  • FIG. 1 shows a damping arrangement for guide vanes of a gas turbine, namely an aircraft engine, according to the prior art
  • Fig. 2 shows a damping arrangement for guide blades of a gas turbine, namely an aircraft engine, in the sense of the present invention in an exploded view; and Fig. 3 shows a detail of the damping arrangement of Fig. 2 in the area of the inner shroud of a guide vane in the assembled state.
  • FIG. 1 shows a section of a compressor 10 of a gas turbine 11 in the region of two guide vane rings 12 and three moving blade rings 13. In the axial direction or in the direction of flow (arrow 14), alternating guide vane rings 12 and moving vane rings 13 are arranged.
  • Each of the guide vane rings 12 is formed from a plurality of guide vanes 15 spaced apart from one another in the circumferential direction.
  • the guide vanes 15 of the guide vane rings 12 are fastened 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 shroud 19.
  • At least one seal carrier 20 for sealing elements 21 is fastened to the inner shrouds 19 of the guide vanes 15.
  • the sealing elements 21 are designed as honeycomb seals which interact with sealing fins 23 assigned to rotor disks 22.
  • this spring element 25 is designed as an egg-shaped spring, which causes a relatively large radial height in the area of the inner shroud 19.
  • the radial overall height in the area of the inner shroud 19 and the seal carrier 20 is visualized in FIG. 1 by a double arrow 26.
  • Such a large radial height in the area of the inner shroud causes a radial height of the entire gas turbine. This is a disadvantage.
  • the C-shaped spring elements known from the prior art are subject to tolerances and therefore inaccurate.
  • FIG. 2 shows an exploded view of the damping arrangement
  • FIG. 3 shows a cross section in the region of the inner shroud of a guide vane through the damping arrangement according to the invention.
  • FIG. 2 shows a section of a guide vane ring 27 in the region of four guide vanes 28.
  • a radially outer end 29 of the guide vanes 28 is not used to fasten the latter to one in FIG. 2 illustrated housing of the gas turbine.
  • a seal carrier 32 for sealing elements 33 can be fastened to the inner shroud 31 of the four guide vanes 28.
  • the spring element 34 designed as a leaf spring 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 the overall radial height of the gas turbine is reduced.
  • the spring element 34 is clamped between the inner shrouds 31 of the guide vanes 28 and the seal carrier 32 in such a way that the spring element 34 has a central bearing area 36 on the seal carrier 32 and with two lateral bearing areas 37 and 38 bears against the inner cover band 31 or is in contact. Accordingly, forces to be damped and caused by vibrations act on the spring element 34 in the sense of the arrows drawn in FIG. 3. It should be noted that the abbreviation F in FIG. 3 stands for force and thus force.
  • the spring element 34 can also be clamped exactly the other way round between the inner shrouds 31 of the guide vanes 28 and the seal carrier 32, in such a way that the spring element 34 with the central Au position region 36 on the inner shroud 31 and with the two lateral bearing areas 37 and 38 abuts the seal carrier 32.
  • the spring element 34 designed as a leaf spring has a plurality of, in the exemplary embodiment shown four, leaf spring sections 39 which are separated from one another by slots 40.
  • Such a leaf spring section 39 is accordingly positioned in the region of each inner shroud 31 of each guide vane 38.
  • Each guide vane 28 is accordingly individually damped in the area of the respective inner shroud 31.
  • the individual leaf spring sections 39 are separated from one another by two slots 40, each of the two slots 40 extending into the spring element 34 from a different side.
  • the slots 40 which run into the spring element 34 from different sides and which separate two adjacent leaf spring separate cuts 39, end at a distance from each other, so that between these two slots 40, a connecting web between two leaf spring sections 39 remains.
  • the sealing arrangement according to the invention also has 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 run laterally in cross-section next to or each spring element 34 designed as a leaf spring.
  • the securing elements 41 are guided in corresponding recesses 42 and 43 within the inner shroud 31 and the seal carrier 32.
  • the spring element 34 has angled sections 44, which serve as securing tabs and fix the securing elements 41 in their position.
  • a structurally particularly advantageous damping arrangement for the guide vanes of a gas turbine is provided.
  • the low radial height and the simple manufacture of the spring elements are particularly advantageous.
  • the spring elements are designed as a simple, flat sheet metal part. There is therefore no need to bend 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 shroud 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)

Abstract

L'invention concerne un système amortisseur pour aubes directrices, notamment pour aubes directrices de turbine à gaz ou de groupe motopropulseur. Pour ce qui est du système amortisseur, les aubes directrices (28) d'une grille d'aubes directrices ou d'une couronne d'aubes directrices (27) sont fixées sur un boîtier, par des leurs extrémités situées à l'extérieur (29) dans le sens radial. Les extrémités situées à l'intérieur (30) dans le sens radial, des aubes directrices (28), forment une bande de recouvrement intérieure (31). Au moins un support de garniture d'étanchéité (32) est fixé sur la bande de recouvrement intérieure (31) des aubes directrices (28). Au moins un élément à effet ressort (34) est disposé entre la bande de recouvrement intérieure (31) des aubes directrices (28) et le ou chaque support de garniture d'étanchéité (32). Selon l'invention, le ou chaque élément à effet ressort (34) se présente sous forme de ressort à lame.
EP05714933.8A 2004-02-11 2005-02-04 Systeme amortisseur pour aubes directrices Ceased 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 true EP1714006A1 (fr) 2006-10-25
EP1714006B1 EP1714006B1 (fr) 2014-01-15

Family

ID=34801875

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05714933.8A Ceased 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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EP1798378B1 (fr) * 2005-12-19 2010-06-09 Rolls-Royce Plc Disposition de montage d'une aube directrice de turbine à gaz
US7481618B2 (en) 2005-12-21 2009-01-27 Rolls-Royce Plc Mounting arrangement
JP4918263B2 (ja) * 2006-01-27 2012-04-18 三菱重工業株式会社 軸流圧縮機の静翼環
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US8616842B2 (en) * 2009-03-30 2013-12-31 Airius Ip Holdings, Llc Columnar air moving devices, systems and method
DE102008032661A1 (de) * 2008-07-10 2010-01-14 Mtu Aero Engines Gmbh Strömungsmaschine
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WO2012174155A1 (fr) 2011-06-15 2012-12-20 Airius Ip Holdings, Llc Dispositifs, systèmes et procédés de déplacement d'air en colonne
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USD698916S1 (en) 2012-05-15 2014-02-04 Airius Ip Holdings, Llc Air moving device
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WO2015050739A1 (fr) * 2013-10-03 2015-04-09 United Technologies Corporation Système de joint d'étanchéité pour pale comprenant un élément d'étanchéité à positionnement positif par ressort dans le sens axial
US10024531B2 (en) 2013-12-19 2018-07-17 Airius Ip Holdings, Llc Columnar air moving devices, systems and methods
US9702576B2 (en) 2013-12-19 2017-07-11 Airius Ip Holdings, Llc Columnar air moving devices, systems and methods
WO2015187856A1 (fr) 2014-06-06 2015-12-10 Airius Ip Holdings, Llc Dispositifs, systèmes et procédés de déplacement d'air en colonne
US9976431B2 (en) * 2014-07-22 2018-05-22 United Technologies Corporation Mid-turbine frame and gas turbine engine including same
US10392951B2 (en) 2014-10-02 2019-08-27 United Technologies Corporation Vane assembly with trapped segmented vane structures
USD805176S1 (en) 2016-05-06 2017-12-12 Airius Ip Holdings, Llc Air moving device
USD820967S1 (en) 2016-05-06 2018-06-19 Airius Ip Holdings Llc Air moving device
US10487852B2 (en) 2016-06-24 2019-11-26 Airius Ip Holdings, Llc Air moving device
EP3315728B1 (fr) * 2016-10-26 2022-01-12 MTU Aero Engines AG Palier amorti d'aube directrice
BE1024935B1 (fr) * 2017-01-26 2018-08-27 Safran Aero Boosters S.A. Compresseur avec virole interne segmentee pour turbomachine axiale
USD886275S1 (en) 2017-01-26 2020-06-02 Airius Ip Holdings, Llc Air moving device
USD885550S1 (en) 2017-07-31 2020-05-26 Airius Ip Holdings, Llc Air moving device
WO2019147219A1 (fr) * 2018-01-23 2019-08-01 Siemens Aktiengesellschaft Coulissement sur des segments de couvercle de carénage pour aubes de stator de compresseur de turbine à gaz
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Also Published As

Publication number Publication date
US8105016B2 (en) 2012-01-31
US20080019836A1 (en) 2008-01-24
CA2555578A1 (fr) 2005-08-25
DE102004006706A1 (de) 2005-08-25
EP1714006B1 (fr) 2014-01-15
WO2005078242A1 (fr) 2005-08-25

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