EP2344722A2 - Groupe d'aubes avec pied de montage axial décalé - Google Patents

Groupe d'aubes avec pied de montage axial décalé

Info

Publication number
EP2344722A2
EP2344722A2 EP09771688A EP09771688A EP2344722A2 EP 2344722 A2 EP2344722 A2 EP 2344722A2 EP 09771688 A EP09771688 A EP 09771688A EP 09771688 A EP09771688 A EP 09771688A EP 2344722 A2 EP2344722 A2 EP 2344722A2
Authority
EP
European Patent Office
Prior art keywords
blade
blades
rotor
stage according
cluster
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.)
Withdrawn
Application number
EP09771688A
Other languages
German (de)
English (en)
Inventor
Frank Stiehler
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 EP2344722A2 publication Critical patent/EP2344722A2/fr
Withdrawn legal-status Critical Current

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • 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

Definitions

  • the present invention relates to a blade cluster according to the preamble of patent claim 1.
  • Turbine stages which are built for turbines with higher loads, but also compressor stages are generally equipped with individual blades, which are each hung on a profiled foot in a disc with grooves and fixed therein.
  • the blade of a turbomachine is known, which is mounted on a rotor or stator via an axially aligned dovetail foot in the form of a Christmas tree.
  • the rotor in the form of a disc on its radial peripheral surface on a number of axially extending grooves forming a plurality of radially spaced undercuts in the direction of groove bottom in the above-mentioned form.
  • the foot consists of a fir-tree-shaped projection on which a number of circumferentially facing undercuts are formed, such that the foot in the axial direction of the rotor can be inserted into the groove and fixed therein.
  • a partial solution to the above-mentioned problem is provided by the rotors of compressor and turbine stages, which are constructed in accordance with the design principle of a BLISK. are built.
  • Basis of a BLISK is preferably a forged disc, from the outer contour, for example, by machining the blade profiles are worked out. That is, the disc and the blades are made of one part.
  • Blade clusters are according to the invention integral components consisting of at least two blades, which are equipped with a common (single) blade attachment for mounting the cluster on the rotor or stator.
  • a particularly high power transmission is ensured by the blade attachment is designed as an axially extending dovetail joint with at least one undercut (on each flank). This type of connection can be produced with high precision and can be mounted inexpensively.
  • the dovetail connection is decentralized between the
  • Blades preferably arranged offset in the circumferential direction. This allows the airfoil loads to be split into each instead of a centralized merge Dovetail contact surface are introduced, so that reduce the resulting high Kerblasten. This makes it possible to make the dovetail connection less massive, or to transmit higher forces. It has proved to be particularly favorable with respect to the introduction of force when the offset in the circumferential direction is about half a blade pitch.
  • the groove or the recess of the dovetail connection is formed on the side of the blade cluster and the foot or the projection on the side of the rotor or stator. This reduces the weight of the cluster and thus the load on the connection.
  • Fig. 1 shows the radially outer peripheral portion of a turbine or compressor disk mounted thereon blade cluster according to a preferred embodiment of the invention
  • Fig. 2 shows the blade cluster in unmounted state.
  • a blade cluster 1 of a turbine or compressor stage consists of a pair of blades 2 which are connected at their radially inner ends to a single common blade root 3.
  • the radially outer ends are coupled to one another via a flat band 4 (referred to in the trade as "plainshroud").
  • the blade cluster 1 comprising the projecting components is of an integral design, for example by friction welding or inductive high frequency pressure welding and more preferably in one piece.
  • the blade root 3 consists of a base plate 5, at the radial top of the two radially inner blade ends are attached and at the radial bottom of a foot base 6 is formed, such that the base plate 5 is a strip-shaped overhang forms with respect to the base 6.
  • a groove 7 is worked out, which extends continuously in respect to the blade row axial direction of the step.
  • the groove 7 is made in the shape of a dovetail and thus forms an undercut on each groove flank.
  • the groove 7 is not centrally located centrally between the two blades 2 and the inner blade ends, but in the present case by about half a pitch in the circumferential direction, namely in accordance with the Fig. 1 in the force direction of the Blades 2 arranged offset.
  • a disk (rotor) 8 of the stage is shown in sections. Accordingly, the disc 8 is axially expanded at its radially outer periphery to form a so-called Filletinterface 9, on the radial outer side a number of spring-like strips 10 are formed integrally with the disc 8 in the axial direction of the step.
  • the springs 10 are equally spaced circumferentially.
  • the springs 10 have a dovetail shape in their cross-section and thus form the counterpart to the grooves 7 on the side of the blade cluster 1.
  • the dimensioning of the grooves 7 and springs 10 is selected such that when they are brought together a press connection is produced.
  • the blade feet 3 are pushed onto the disc-side springs 10 in the axial direction, until at the respective end faces a burr-free transition between disc 8 and 3 foot is formed.
  • the individual blade clusters 1 are assembled into a complete blade ring.
  • a blade cluster 1 can also have more than two blades, for example three blades.
  • the shape of the blade root 3 is not limited to a simple dovetail but may also, as is known in the art, be formed like a fir tree with a plurality of undercut edges per flank.

Landscapes

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

Abstract

La présente invention concerne un étage d'une turbine ou d'un compresseur, avec une pluralité d'aubes qui sont montées sur un rotor et/ou un stator de l'étage. Selon l'invention, les aubes sont réunies en un certain nombre de groupes d'aubes formés d'une seule pièce, composés chacun d'au moins deux aubes et dotés d'une unique fixation commune pour le montage du groupe sur le rotor ou le stator.
EP09771688A 2008-11-13 2009-11-07 Groupe d'aubes avec pied de montage axial décalé Withdrawn EP2344722A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008057190A DE102008057190A1 (de) 2008-11-13 2008-11-13 Schaufelcluster mit versetztem axialem Montagefuß
PCT/DE2009/001579 WO2010054632A2 (fr) 2008-11-13 2009-11-07 Groupe d'aubes avec pied de montage axial décalé

Publications (1)

Publication Number Publication Date
EP2344722A2 true EP2344722A2 (fr) 2011-07-20

Family

ID=42105017

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09771688A Withdrawn EP2344722A2 (fr) 2008-11-13 2009-11-07 Groupe d'aubes avec pied de montage axial décalé

Country Status (4)

Country Link
US (1) US20110200440A1 (fr)
EP (1) EP2344722A2 (fr)
DE (1) DE102008057190A1 (fr)
WO (1) WO2010054632A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2695704B1 (fr) * 2012-08-09 2015-02-25 MTU Aero Engines GmbH Procédé de fabrication d'un segment de couronne d'aubes en TiAl pour une turbine à gaz ainsi que segment de couronne d'aubes correspondant
EP2730745B1 (fr) 2012-11-09 2017-08-30 MTU Aero Engines AG Agencement d'aubes pour une turbomachine
US9677405B2 (en) 2013-03-05 2017-06-13 Rolls-Royce Corporation Composite gas turbine engine blade having multiple airfoils
US20170002659A1 (en) * 2015-07-01 2017-01-05 United Technologies Corporation Tip shrouded high aspect ratio compressor stage
US10934859B2 (en) * 2018-08-24 2021-03-02 Rolls-Royce North American Technologies Inc. Turbine blade comprising ceramic matrix composite materials
WO2020099184A1 (fr) * 2018-11-15 2020-05-22 Rolls-Royce Deutschland Ltd & Co Kg Procédé de fabrication d'un composant pour une turbomachine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE679926C (de) * 1935-12-21 1939-08-17 Gustav Koehler Dipl Ing Befestigung von radial beaufschlagten Doppelschaufeln
US2221685A (en) * 1939-01-18 1940-11-12 Gen Electric Elastic fluid turbine bucket unit
US2277484A (en) * 1939-04-15 1942-03-24 Westinghouse Electric & Mfg Co Turbine blade construction
CH305819A (de) * 1951-02-26 1955-03-15 Power Jets Res & Dev Ltd Verfahren zur Herstellung eines Schaufelrotors einer Turbomaschine und nach diesem Verfahren hergestellter Schaufelrotor.
CH335695A (de) * 1955-12-06 1959-01-31 Bbc Brown Boveri & Cie Fuss zur Befestigung von Schaufeln in Läufern von Turbomaschinen
GB1217275A (en) * 1968-05-31 1970-12-31 Rolls Royce Gas turbine engine axial flow multi-stage compressor
US3902820A (en) * 1973-07-02 1975-09-02 Westinghouse Electric Corp Fluid cooled turbine rotor blade
JPH0988506A (ja) * 1995-09-21 1997-03-31 Ngk Insulators Ltd ハイブリッド型ガスタービン動翼用のブレード及びタービンディスク並びにこれらからなるハイブリッド型ガスタービン動翼
DE19858702B4 (de) 1998-12-18 2004-07-01 Mtu Aero Engines Gmbh Verfahren zum Verbinden von Schaufelteilen einer Gasturbine, sowie Schaufel und Rotor für eine Gasturbine
FR2851285B1 (fr) * 2003-02-13 2007-03-16 Snecma Moteurs Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine
GB2401655A (en) * 2003-05-15 2004-11-17 Rolls Royce Plc A rotor blade arrangement
DE10337868A1 (de) * 2003-08-18 2005-03-17 Mtu Aero Engines Gmbh Rotor für eine Gasturbine sowie Gasturbine
EP1834067B1 (fr) * 2004-12-01 2008-11-26 United Technologies Corporation Ensemble de pales de soufflante pour moteur a turbine de bout et procede de montage

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines

Also Published As

Publication number Publication date
WO2010054632A3 (fr) 2010-12-29
US20110200440A1 (en) 2011-08-18
WO2010054632A2 (fr) 2010-05-20
DE102008057190A1 (de) 2010-05-20

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