EP1747349B1 - Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise - Google Patents

Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise Download PDF

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Publication number
EP1747349B1
EP1747349B1 EP05747436A EP05747436A EP1747349B1 EP 1747349 B1 EP1747349 B1 EP 1747349B1 EP 05747436 A EP05747436 A EP 05747436A EP 05747436 A EP05747436 A EP 05747436A EP 1747349 B1 EP1747349 B1 EP 1747349B1
Authority
EP
European Patent Office
Prior art keywords
sealing strip
blade
thickness
shroud
shroud 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.)
Not-in-force
Application number
EP05747436A
Other languages
German (de)
English (en)
Other versions
EP1747349A1 (fr
Inventor
Andreas Bögli
Alexander Mahler
James George Ritchie
Slawomir Slowik
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1747349A1 publication Critical patent/EP1747349A1/fr
Application granted granted Critical
Publication of EP1747349B1 publication Critical patent/EP1747349B1/fr
Not-in-force 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
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2230/10—Manufacture by removing 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to a turbomachine blade according to the preamble of claim 1. It further relates to a method for producing a turbomachine blade according to the invention.
  • Blades of turbomachinery with Schaufeldeckbändem are well known in the art.
  • Shovel cover strips are used on the one hand to mechanically couple the blade tip areas of adjacent blades together, resulting in a greater rigidity of the blade assembly and thus a higher natural vibration frequency.
  • sealing tapes in turbomachinery blading also serve to reduce leaks at the blade tips.
  • the shrouds preferably continue to wear sealing strips, which cooperate with a mating surface, and with this form a non-contact seal, such as a labyrinth seal.
  • the mating surface is often a so-called honeycomb structure (“honeycomb”) or other touch-tolerant system.
  • the circumferential bucket cover strips usually consist of individual segments, which are each cast on the tip of a blade with.
  • a shroud element increased stress on the blade root and the blade due to the centrifugal forces of the shroud element.
  • the shroud elements are generally not stored centrally of the blade tip. This results in addition to a bending load for the blade and a "tilting", that is, a one-sided lifting, the shroud element. It has also been shown that even with balanced shroud elements due to the centrifugal force during operation, plastic deformations and thus "tipping" can occur.
  • Out US-A-5,290,144 is a Strömungsmaschinenschaufel, with a built-in circumferential direction and a built-in radial direction, comprising a blade root, an airfoil, and a shroud element, wherein on the shroud element, which is arranged at the head end of the airfoil, arranged in the circumferential direction radial sealing strip, the thickness of which varies in the circumferential direction such that the sealing strip has a first thickness at the position of the airfoil.
  • the thickness of the sealing strip in the areas seen in the installation circumferential direction outside areas is less than the first thickness.
  • an inflow-side and a downstream-side sealing strip is provided.
  • a turbomachine blade of the type mentioned is to be specified so that the unbalanced loads are reduced and / or avoided by the centrifugal force load of the shroud element, which can result in a lifting of a shroud element.
  • the core of the invention is thus, the shroud element, which is arranged with respect to the skeleton line of the airfoil in particular circumferentially-asymmetrically at the head end of the airfoil, to be designed such that the thickness of the sealing strip varies in the circumferential direction.
  • the thickness of the sealing strip has a lower value in the areas located outside in the installation circumferential direction than in the middle area, which lies in the region of the blade leaf.
  • the plastic deformation under centrifugal load is thus reduced or completely stopped.
  • the reduced mass of the shroud element reduces on the one hand the total centrifugal load on the blade root; on the other hand is reduced by the reduced moment of inertia of the shroud element with respect to the airfoil skeleton line under centrifugal force due to the asymmetry of the shroud element initiated bending moment at the transition from the shroud element to the blade.
  • a one-sided lifting or "tilting" of the shroud element is thereby reduced.
  • the variation of the thickness of the sealing strip is carried out such that the moment of inertia of the shroud element is balanced with respect to the airfoil skeleton line.
  • the invention can be realized very easily on existing turbomachinery blades by the sealing strip machined, for example by milling, grinding, or eroding, is reworked.
  • the invention can be realized in existing turbomachinery without having to redesign the tools for the production of turbomachinery blades.
  • an inflow-side sealing strip is arranged on the shroud element, which is adjacent to the airfoil leading edge, and a downstream sealing strip, which is adjacent to the airfoil trailing edge, wherein only the thickness of the upstream side sealing strip varies.
  • the sealing strip in the region of the airfoil has a greater thickness than in the outer circumferential direction seen in the installation circumferential direction.
  • the area of reduced thickness of the sealing strip is, for example, 20% to 70% of the extent of the sealing strip in recessed circumferential direction.
  • turbomachine blade For producing a turbomachine blade according to the invention, this can already be produced on the one hand during prototyping, that is to say, for example, during casting, with an outgoing sealing strip with a thickness varying in the circumferential direction. In the complete redesign of a turbomachine blade this way is readily feasible.
  • Another possibility for producing a turbomachine blade according to the invention is to machine an existing turbomachine blade and to reduce the thickness of the outlet-side sealing strip in the regions lying outwards in the circumferential direction. This reduction is achieved, for example, by machining, wherein the machining of the mass of the sealing strip is preferably reduced by 10% to 50% of the original mass. The mass reduction also helps to reduce the centrifugal force load on the blade root.
  • the post-processing of an existing blade makes it possible to implement the invention, in particular in existing constructions. Furthermore, already in use blades can be modified in the context of regular maintenance according to the invention.
  • FIG. 1 Shovels of a turbomachine
  • FIG. 2 a single turbomachine blade according to the prior art
  • FIG. 3 a single turbomachine blade according to the prior art in a plan view
  • FIG. 4 a turbomachine blade according to the invention.
  • FIG. 5 a turbomachine blade according to the invention in a plan view.
  • FIG. 1 is a section of the running blading of a turbine according to the prior art shown.
  • the head regions of two adjacently arranged blades 1 are shown.
  • Each of the rotor blades 1 comprises a vane root (not illustrated) which is readily familiar to the person skilled in the art and comprises a fastening device with which the rotor blade is fastened in the rotor of a gas turbine group or steam turbine.
  • Each of the blades has a built-in circumferential direction represented by the rotational revolution speed U and a built-in radial direction facing the blade root from the blade root.
  • a blade comprises an airfoil 11 with an airfoil leading edge 12 and an airfoil trailing edge 13.
  • the blade grid formed by the blades is flowed through by a hot gas flow from the blade blade leading edge to the blade trailing edge.
  • the illustrated running blading has a so-called blade cover strip, which the blade row as Ring surrounds. Due to the arrangement of the shroud, leaks at the blade tips are reduced. Further, the shroud causes mechanical coupling of the blades to the blade tips, such that the vibration mode of the blade is the vibration mode of a package vibration in which a plurality of blades vibrate in phase. This results in a greater rigidity of the blading and in a relation to the vibrations of a single blade significantly increased natural vibration frequency.
  • the shroud is formed by shroud elements 14, which are arranged at the head of each blade.
  • shroud elements 14 On the shroud elements 14 extending in the circumferential direction radial sealing strips, namely an inflow-side sealing strip 15 and a downstream sealing strip 16, respectively.
  • the sealing strips form a non-contact labyrinth seal in a manner known per se with the housing parts opposite to them in the installed state.
  • the shroud elements are mounted on the blades 11, as it were. In the installation position, the circumferential end faces of the shroud elements of two adjacent blades abut each other, and form a substantially gas-tight unit, such that no hot gas can flow outward from the flow channels of the blade grid.
  • the illustrated blades move in the direction of the arrow labeled U.
  • the blades, and in particular the shroud elements are loaded by centrifugal forces acting radially outward, ie in the direction of the blade head.
  • the centrifugal forces acting on the shroud elements must be absorbed in the airfoils. Due to the complex, influenced by centrifugal forces and thermal deformations, stress states occur under unfavorable circumstances to local plastic deformation at the transition from the shroud element to the blade.
  • the shroud element On the pressure side, the shroud element is thereby moved radially outwards by the amount ⁇ .
  • FIG. 2 shows a perspective view of the blade head region of the blade 1;
  • FIG. 3 shows a plan view of the blade.
  • the turbomachine blade has a built-in radial direction R and a built-in circumferential direction U.
  • the airfoil skeleton line is designated 17.
  • the airfoil skeleton line may be considered as a virtual axis of the tilting movement previously described. On the suction side of the blade and on the pressure side of the blade, the moment of inertia of the shroud element with respect to this virtual axis are different.
  • the thickness of the upstream side sealing strip in the circumferential direction U outer lying areas 21 and 22 is reduced relative to a central region.
  • the moment of inertia of the shroud element is reduced. This means that the bending moments caused by the centrifugal force during operation and thus the deformation are reduced.
  • the reduction is carried out in such a way that, at least in the area on the inflow side, the shroud element is balanced with respect to the airfoil skeleton line.
  • the areas 21 and 22 reduced thickness of the sealing strip extended over 20% to 70% of the extent of the sealing strip in the circumferential direction, that is, the sum L1 + L2 is between 20% and 70% of the total extension L. Due to the reduction in the mass of the shroud element the plastic deformation at the transition to the blade is at least reduced.
  • Such a geometry of the sealing strip 15 can on the one hand be produced directly during prototyping, for example during casting or sintering of the turbomachine blade. It can also be produced by a forming process such as forging.
  • the turbomachine blade according to the invention as described in US Pat FIGS. 4 and 5 is shown, from a flow machine blade with constant thickness of the sealing strip, as in the FIGS. 2 and 3 is produced by the sealing strip 15 machined, that is, for example, by milling, grinding, or eroding, is processed.
  • the sealing strip 15 machined that is, for example, by milling, grinding, or eroding
  • the sealing strip 15 machined that is, for example, by milling, grinding, or eroding
  • This manufacturing process proves to be particularly efficient when the blades of existing machines according to the invention are to be modified. It is then not necessary to make new tools for the production of the blade, but it is only an additional machining step necessary.
  • This method is also particularly suitable for reworking blades already in use during overhaul and / or maintenance measures according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)
  • Auxiliary Methods And Devices For Loading And Unloading (AREA)

Claims (7)

  1. Aube de turbomachine, comprenant une direction périphérique de montage (U) et une direction radiale de montage (R), comprenant une base d'aube, une pale d'aube (11) et un élément d'anneau de renforcement (14), dans laquelle, sur l'élément d'anneau de renforcement qui est disposé à l'extrémité côté tête de la pale d'aube, est disposée une baguette d'étanchéité radiale (15,16) s'étendant dans la direction périphérique, dont l'épaisseur varie dans la direction périphérique de telle sorte que la baguette d'étanchéité présente au niveau de la position de la pale d'aube une première épaisseur et que l'épaisseur de la baguette d'étanchéité dans les régions (22, 21) situées à l'extérieur, vu dans la direction périphérique de montage, soit inférieure à la première épaisseur, une baguette d'étanchéité (15) du côté de l'attaque et une baguette d'étanchéité (16) du côté de fuite étant prévues, caractérisée en ce que seule l'épaisseur de la baguette d'étanchéité (15) du côté de l'attaque varie.
  2. Aube de turbomachine selon la revendication 1, caractérisée en ce qu'une première région de la baguette d'étanchéité (15) du côté de l'attaque présente une première épaisseur, une deuxième région présente une épaisseur réduite, et en ce que la région d'épaisseur réduite (L1, L2) de la baguette d'étanchéité (15) du côté de l'attaque représente 20 % à 70 % de l'étendue (L) de la baguette d'étanchéité dans la direction périphérique.
  3. Procédé de fabrication d'une aube de turbomachine selon l'une quelconque des revendications précédentes, caractérisé en ce que seule l'épaisseur de la baguette d'étanchéité (15) du côté de l'attaque est réduite au moins en partie.
  4. Procédé selon la revendication 3, caractérisé en ce que la réduction de l'épaisseur est réalisée par un usinage par enlèvement de copeaux.
  5. Procédé selon l'une quelconque des revendications 3 ou 4, caractérisé en ce que l'épaisseur de la baguette d'étanchéité (15) du côté de l'attaque est réduite au niveau des régions (21, 22) situées à l'extérieur dans la direction périphérique.
  6. Procédé selon l'une quelconque des revendications 4 ou 5, caractérisé en ce que l'on usine entre 20 % et 70 % de l'étendue périphérique de la baguette d'étanchéité (15) du côté de l'attaque.
  7. Procédé selon l'une quelconque des revendications 3 à 6, caractérisé en ce que l'on utilise une aube avec une baguette d'étanchéité (15) du côté de l'attaque dont l'épaisseur est constante avant la réduction dans la direction périphérique de montage.
EP05747436A 2004-05-19 2005-05-13 Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise Not-in-force EP1747349B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004025321A DE102004025321A1 (de) 2004-05-19 2004-05-19 Strömungsmaschinenschaufel
PCT/EP2005/052198 WO2005113941A1 (fr) 2004-05-19 2005-05-13 Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise

Publications (2)

Publication Number Publication Date
EP1747349A1 EP1747349A1 (fr) 2007-01-31
EP1747349B1 true EP1747349B1 (fr) 2008-11-12

Family

ID=34969025

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05747436A Not-in-force EP1747349B1 (fr) 2004-05-19 2005-05-13 Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise

Country Status (5)

Country Link
US (1) US7326033B2 (fr)
EP (1) EP1747349B1 (fr)
AT (1) ATE414214T1 (fr)
DE (2) DE102004025321A1 (fr)
WO (1) WO2005113941A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060280610A1 (en) * 2005-06-13 2006-12-14 Heyward John P Turbine blade and method of fabricating same
EP1840333A1 (fr) 2006-03-31 2007-10-03 ALSTOM Technology Ltd Aube de turbine ayant des portions de bande de renforcement
US20090097979A1 (en) * 2007-07-31 2009-04-16 Omer Duane Erdmann Rotor blade
US8257035B2 (en) * 2007-12-05 2012-09-04 Siemens Energy, Inc. Turbine vane for a gas turbine engine
DE102008008894A1 (de) * 2008-02-13 2009-08-20 Man Turbo Ag Verfahren zur Herstellung eines Bauteiles für eine thermische Maschine
DE102008061800A1 (de) 2008-12-11 2010-06-17 Rolls-Royce Deutschland Ltd & Co Kg Segmentierte Dichtlippen für Labyrinthdichtungsringe
TWI510189B (zh) * 2009-06-19 2015-12-01 Lilly Co Eli 殺外寄生蟲之方法及調配物
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
DE102013224199A1 (de) 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
FR3077093B1 (fr) * 2018-01-19 2020-07-03 Safran Aircraft Engines Aube equilibree d'une roue mobile d'une turbomachine
CN113486512B (zh) * 2021-07-05 2022-05-10 哈尔滨工程大学 一种功能梯度变厚度叶片模型的颤振分析方法

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US2278041A (en) * 1939-10-23 1942-03-31 Allis Chalmers Mfg Co Turbine blade shroud
US4878810A (en) * 1988-05-20 1989-11-07 Westinghouse Electric Corp. Turbine blades having alternating resonant frequencies
US5048183A (en) * 1988-08-26 1991-09-17 Solar Turbines Incorporated Method of making and repairing turbine blades
US5083903A (en) * 1990-07-31 1992-01-28 General Electric Company Shroud insert for turbomachinery blade
DE59202211D1 (de) * 1991-08-08 1995-06-22 Asea Brown Boveri Deckblatt für axialdurchströmte Turbine.
EP0536575B1 (fr) 1991-10-08 1995-04-05 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
DE19904229A1 (de) * 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel
JP2001055902A (ja) * 1999-08-18 2001-02-27 Toshiba Corp タービン動翼
FR2825411B1 (fr) 2001-05-31 2003-09-19 Snecma Moteurs Aube de turbine avec lechette d'etancheite
DE50304325D1 (de) * 2002-04-16 2006-09-07 Alstom Technology Ltd Laufschaufel für eine Turbomaschine

Also Published As

Publication number Publication date
ATE414214T1 (de) 2008-11-15
EP1747349A1 (fr) 2007-01-31
DE502005005956D1 (de) 2008-12-24
WO2005113941A1 (fr) 2005-12-01
US20070104570A1 (en) 2007-05-10
US7326033B2 (en) 2008-02-05
DE102004025321A1 (de) 2005-12-08

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