EP2401477A2 - Procédé de fixation ou de fabrication d' un anneau de renfort fermé pour un rotor d'un étage de turbine et rotor de turbine - Google Patents

Procédé de fixation ou de fabrication d' un anneau de renfort fermé pour un rotor d'un étage de turbine et rotor de turbine

Info

Publication number
EP2401477A2
EP2401477A2 EP10702677A EP10702677A EP2401477A2 EP 2401477 A2 EP2401477 A2 EP 2401477A2 EP 10702677 A EP10702677 A EP 10702677A EP 10702677 A EP10702677 A EP 10702677A EP 2401477 A2 EP2401477 A2 EP 2401477A2
Authority
EP
European Patent Office
Prior art keywords
blades
shroud
turbine
fiber
fiber material
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Withdrawn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
EP10702677A
Other languages
German (de)
English (en)
Inventor
Christoph Ebert
Detlef Haje
Albert Langkamp
Markus Mantei
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2401477A2 publication Critical patent/EP2401477A2/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Withdrawn legal-status Critical Current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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/33—Shrouds which are part of or which are rotating with the rotor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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

Definitions

  • the present invention relates to a plurality of methods for attaching or producing a closed shroud to the front-side free ends of side-by-side arranged blades of a rotor blading of a turbine stage of a turbine. Furthermore, the invention relates to a rotor blading of a turbine stage for a turbine, comprising a plurality of side by side arranged blades.
  • the rotor blading of a turbine stage of a turbine has a plurality of airfoils.
  • the rotor blading When operating a turbine, in particular a steam turbine, the rotor blading is exposed to high forces.
  • the last stage of a condensing steam turbine is in the design of the turbine usually the limiting component respect.
  • the use of running blading or blade leaves made of a composite material, such as a fiber composite material, in particular a carbon fiber reinforced composite material has an advantageous effect due to the significantly lower mass of such trained run blading or blade blades. That is, the use of Faserverbundenlaufbeschaufelschier advantageous by the significantly better strength / mass ratio.
  • the last stage of a blading of a turbine in particular a condensing steam turbine, is usually carried out with free-standing airfoils.
  • the blades are stabilized with coupling elements which are arranged between the blades.
  • the object of the invention is to produce a shroud for a large blade blading of a turbine stage of a turbine or to attach this to a large blade blading a turbine stage of a turbine to increase the efficiency of a blading or a turbine stage of a turbine and the vibrations of the blades of the Laufbe - to dampen blade.
  • This object is achieved by a method for attaching or producing a closed shroud on the / the free ends of side by side angeord- Neten blades of a blade blading a turbine stage of a turbine having the features of independent claim 1, by a method according to the independent claim 9, by a method according to independent claim 10 and by a blading of a turbine stage for a turbine with the features according to independent claim 20 solved. Further features and details of the invention will become apparent from the dependent claims, the description and the drawings.
  • the object is achieved by a method for attaching a closed shroud to the free end (s) of juxtaposed blades of a turbine blade turbine runner, the method being characterized in that US Pat Ribbon is wound from a fiber material on the front free ends of the blades, that a matrix material in the
  • Fiber material of the wound tape is infiltrated and the resulting fiber composite is cured.
  • the blade tips are referred to as front free ends of the blades.
  • Adjacent blades preferably have the same distance from one another.
  • the blades of the Laufbeschaufe- ment can be made of steel or titanium.
  • the blades of the rotor blading are preferably formed from a fiber composite material, since this material, in contrast to blades made of steel or titanium, by the improved strength / mass ratio advantageous effect.
  • Fiber composites are materials comprising at least two components, namely a fiber material and a matrix material. The matrix material surrounds the fiber material. Due to the mutual interactions of the two components better or higher quality properties can be achieved in a fiber composite material than in each of the two individual components.
  • a band of a fiber material is first wound on the frontal free ends of the blades. This can be done by a Rotation of the rotor blading about an axis take place.
  • the rotor blading is attached to a rotor which is rotated.
  • the fibrous material band is advantageously wound up on a roll. This roll is preferably also rotatable, for example, on a winding machine stored for winding the fiber material band on the front ends of the blades.
  • the fiber material band can be wound differently tight on the front ends of the blades.
  • a matrix material is infiltrated into the fiber material of the wound band.
  • the infiltration of the matrix material into the fiber material results in the so-called fiber composite material.
  • After a curing process creates a solid shroud, which is fixedly disposed at the front ends of the blades. By varying the strip length of the fiber material strip, the shroud thickness can be selectively varied and adapted to the respective boundary conditions of a turbine.
  • the matrix material is infiltrated in liquid form into the fiber material of the wound strip. Curing means that the liquid matrix material solidifies after it has spread evenly throughout the fiber material. This can be done with the aid of an annealing process. By appropriate heating of the resulting composite cures, so that a stable, tight-fitting shroud of a fiber composite material is formed.
  • Such a shroud made of a fiber composite dampens the vibrations of the blades during operation of the rotor blading very well and makes it possible that the turbine blades of the turbine blade thinner and thus aerodynamically be designed nen cheaper than vibration stability reasons was previously possible.
  • large running blading as in the final stage of a condensation steam turbine, can be achieved by attaching such a shroud in its oscillations. be damped. The centrifugal forces that occur during rotation of the rotor blading can be reduced by such a shroud, compared to an attached steel shroud.
  • fiber material different types of fibers can be used.
  • a band of glass fibers, ceramic fibers, nylon fibers or aramid fibers can be used.
  • the band is particularly preferably formed from carbon fibers.
  • Carbon fibers, also known as carbon fibers, are characterized by high strength, a high modulus of elasticity, and so on
  • a fiber composite material with high specific stiffnesses and strengths is produced.
  • the fibers of the fiber material are bonded to the matrix material by adhesive or cohesive forces.
  • a plastic in particular a resin
  • a thermoset or a thermoplastic is infiltrated into the fiber material of the wound tape.
  • the matrix material is infiltrated by negative pressure in the fiber material.
  • a mold or a housing can be placed around the wound fiber material, which seals it airtight.
  • a negative pressure can be generated by suitable tools in the sealed area.
  • the matrix material is introduced into the sealed area, so that it mixes evenly with the fiber material due to the negative pressure. Due to the negative pressure, the matrix material can be better mixed with the fiber material, in particular with the carbon fibers.
  • the liquid matrix material flows into the cavities between the fibers of the fiber material.
  • a form or a channel-shaped housing can already be applied to the sides of the blades during winding of the fiber material band, so that the fiber material band can be centered on the frontal free ends of the blades.
  • the mold may have two disk or annular elements which are positively applied to the longitudinal sides of the airfoils. These stand at the free ends of the blades, i. at the blade tips, something on both sides, so that they form a channel into which the fiber material band can be inserted during winding. This ensures a centering of the fiber material strip during winding.
  • the turbine blade leaves each have a trough at their front-side free ends. point, in which the fiber material tape is inserted during winding. That is, the fiber material band is inserted into the wells, also referred to as bed, at the front ends of the blades to better be positioned at the ends or centered. The fiber material band is thereby automatically centered during winding in the troughs at the frontal free ends of the blades, so that lateral slipping of the fiber material band is prevented at the front ends of the blades.
  • the advantage here is that the wound fiber material band is held laterally by the walls or legs of the wells, in particular during operation of the rotor blading.
  • the trough or the bed at the frontal free end of an airfoil is advantageously produced directly in the production of the airfoil.
  • the fiber material band is covered with a film airtight when subsequently a negative pressure in the covered area is generated and if after reaching a determinable negative pressure of the matrix material in the acted upon with negative pressure Area is introduced for infiltration in the fiber material.
  • the film is applied radially circumferentially at the front-side free ends of the blades, so that the wound fiber material band is sealed airtight.
  • the film is advantageously applied to the edges of the wells of the blades.
  • the film may also be formed as a dimensionally stable housing.
  • the fiber material band is already provided with the matrix material during winding onto the frontal free ends of the blades.
  • the matrix material is already mixed with the fiber material during the winding of the fiber material strip onto the front ends of the blade blades.
  • the fact that the fiber material band is wound in many layers around the ends of the blades is already in every position of the matrix material. Since the fibers impregnated with the matrix material are wound under pretension, excess matrix material is pressed outward. By a subsequent processing, for example by over-rotation of the blading, the extruded matrix material is removed.
  • the matrix material can bond very evenly with the fibers of the fiber material band.
  • further liquid matrix material can be filtered into the sealed area so that sufficient matrix material surrounds the fiber material band.
  • sealing tips are attached to the resulting shroud made of fiber composite material. These can be subsequently attached to the resulting shroud. Thus, grooves can subsequently be screwed in on the outer side of the shroud, to which the sealing tips, in particular in the form of a sealing tip strip, are fastened. the.
  • the sealing tips can also be introduced or generated during the infiltration of the matrix material into the fiber material.
  • the sealing tips can be made of plastic, in particular of a resin, but also of metal or another favorable material.
  • the sealing tips may comprise thermoplastic or thermosetting plastic. The sealing tips are later over-turned and, if necessary, after a tempering process for dimensional stability.
  • the resulting shroud made of a fiber composite material damps vibrations of the blades and thus the rotor blades and thus gives the potential, for example, make the blades much thinner, as from Schwingungsstabili- ity reasons so far, especially for larger Laufbeschaufelept possible.
  • Additional coupling elements, such as coupling wires, between the blades can be dispensed with, which in turn increases the efficiency of the stage of a turbine.
  • an excitability of vibrations is reduced by the stiffening of all blades.
  • the object is achieved by a method for attaching / forming a closed shroud to the front-side free end. solved by the juxtaposed blades of a blade blading a turbine stage of a turbine, the method being characterized in that a closed ring of a fiber composite material by a Aufschrumpfrind is mounted on the front ends of the blades. That is, the closed ring of a fiber composite material can be shrunk on the one hand on the front ends of the blades of the rotor blading.
  • This method utilizes the property that materials expand or contract when a certain temperature is reached.
  • the shroud and the blades are not made to fit, but either the shroud slightly too small or the blades made slightly too large, so that they can not be connected together at normal temperature.
  • the shroud shrinks and thereby presses on the ends of the airfoils and remains so firmly connected to it.
  • the turbine blades can be cooled or heated depending on the material, so that they shrink somewhat. The airfoils expand when cooled or heated to the ambient temperature again so that they press against the wound up shroud.
  • the diameter of the shroud can be increased somewhat by cooling the shroud of carbon fiber reinforced composite material.
  • the running blading can be slightly reduced by a corresponding temperature control, so that the cover strip can be pushed on more easily.
  • the object is achieved by a method for attaching / producing a closed Senen shroud at the front-side free ends of side by side arranged blades of a rotor blade blading of a turbine stage of a turbine solved, in which a closed ring of a fiber composite material, in particular of a carbon fiber reinforced composite material, is glued to the front ends of the blades.
  • the surface of the front ends of the blades can be irradiated and / or specially activated.
  • the tips of the airfoils and / or the inside of the shroud are activated by means of plasma spraying, mechanical roughening and / or coating.
  • the closed ring is arranged on free ends of the turbine blade blades that run inclined relative to the axis of rotation of the turbine blade. That is, the free ends of the turbine airfoils are advantageously inclined to the longitudinal axes of the turbine airfoils and to the plane in which the turbine airfoils are disposed. The inclination allows a better mounting of the ring. In particular, the vapor pressure is used to force the ring onto the blade tips.
  • the closed ring in the attachment of the ring according to the second or third aspect of the invention already on sealing tips.
  • the sealing tips must not be subsequently arranged on the resulting shroud.
  • the sealing tips are preferably made of resin, in particular of a thermoplastic or of a duroplastic, or of metal.
  • the sealing tips can be over-tightened for dimensional stability.
  • the sealing tips can be used after a tempering process for be overdriven.
  • the shroud ring is positioned on a suitable lathe and turned to measure.
  • the play of the sealing tips to a stator surrounding the turbine blade can preferably be adjusted by material abrasion on the stator and / or at the sealing tips.
  • the sealing tips and the stator touch each other for a short time.
  • This intermediate layer serves as a damper between the blades and the shroud. That is, the intermediate layer dampens the vibrations of the blades. These can be vibrated individually or together.
  • the intermediate layer which is preferably formed of a rubber, vibrations of individual airfoils, but also vibrations of several airfoils can be damped.
  • the intermediate layer is preferably formed as a closed elastic ring, which can be raised by spreading on the frontal free ends.
  • the damping of the vibrations of an airfoil or a plurality of airfoils is due to the friction of the front ends of the airfoils and the intermediate layer as well as the applied to the intermediate layer shroud and the intermediate layer.
  • the shroud can be applied to the intermediate layer according to one of the previously described methods.
  • the front-side free ends of the blades each have a trough, in the bottom region of the intermediate layer is introduced.
  • the intermediate layer allows, to a certain extent, unwinding of the airfoils.
  • the intermediate layer may be formed of various materials. Conceivable metals, plastics or fiber materials.
  • a circumferential or interrupted circumferential damping intermediate layer of an elastic material, in particular of a rubber, between the front-side free ends of the blades and the cover sheet is arranged.
  • the damping layer can also be applied in sections, for example with sections for each individual blade or for a plurality of blades. The sections may be further configured to achieve a positive fit with the airfoil tips, for example in the form of "shoes" that engage the ends of the airfoils.
  • the object is achieved by a rotor blading of a turbine stage for a turbine, comprising a plurality of adjacently arranged airfoils, wherein at the front free ends of the bladed blades a closed shroud of a fiber composite material is arranged.
  • a trough for receiving the shroud is provided at the front ends of the blades.
  • the shroud of the blade blading was advantageously attached by a method according to one of the first three aspects to the front ends of the blades.
  • the blades are preferably made of a fiber composite material and in particular of a carbon fiber reinforced plastic.
  • the shroud of a fiber composite material which in particular comprises fibers of carbon, arranged.
  • the so-called blade tips which preferably have a trough, the shroud of fiber composite material is attached.
  • the shroud attenuates during operation of the turbine, ie upon rotation of the bladed rotor, occurring vibrations of the rotor blading.
  • the additionally provided shroud makes it possible, for example, for the blades to be designed to be thinner and more aerodynamically more optimal than would otherwise be possible for reasons of vibration stability.
  • On additional coupling elements for damping can be dispensed with such Laufbeschaufelept, which in turn increases the efficiency of the turbine.
  • an excitability of vibrations is reduced by the stiffening of the entire rotor blading and thus the turbine stage.
  • Figure 1 is a blade tip with trough for receiving a shroud
  • FIG. 2 shows a blade tip rotated by 90 ° in comparison to FIG. 1;
  • FIG. 3 shows a blade tip with shroud and sealing tips
  • FIG. 4 shows a blade tip with sealing tips rotated by 90 ° in comparison with FIG. 3;
  • Figure 5 is a blade tip with oblique frontal
  • FIG. 6 shows a blade tip with an oblique frontal
  • FIG. 7 shows a plan view of a few airfoils and a shroud arranged on the airfoils.
  • FIG. 1 shows the free end or the blade tip of an airfoil 3.
  • the airfoil 3 has a T-shaped end. In this illustration, the airfoil 3 is viewed transversely to the flow direction of the steam within a turbine.
  • the frontal free end 2 of the airfoil 3 is arranged perpendicular to the longitudinal axis 8 of the airfoil 3 in this embodiment.
  • the blade 3 has a trough 4 for receiving a shroud 1, not shown.
  • the trough 4 can be designed in various ways.
  • the trough 4 can have a rectilinearly shaped bottom and legs arranged perpendicular to the bottom, whose free ends are formed by an edge 6 in each case.
  • the trough 4 may have curved transitions between the bottom and the legs as shown in FIG. The bottom, but also the legs of the trough 4 can be roughened.
  • Fig. 1 shows a
  • Figs. 3 and 4 correspond in their views to Figs. 1 and 2, except that at the front end free end 2 of the airfoil 3, the shroud 1 is attached.
  • the shroud 1 and the rotor blading are preferably both made of a fiber composite material, which in particular has carbon fibers.
  • the shroud 1 is in the trough 4 a. From the shroud 1, the sealing tips 5 protrude.
  • the shroud 1 is positively and non-positively in the trough 4 a.
  • the shroud 1 has been produced in the trough 4 by a method according to the first aspect of the invention.
  • the shroud 1 is preferably formed flat with the edges 6 of the trough 4.
  • the sealing tips 5 are used to seal the stator of a turbine surrounding the rotor blades.
  • the sealing tips 5 may have a plurality of sealing tip bands.
  • FIG. 5 shows a blade tip of an airfoil 3 without shroud 1.
  • the front end 2 of the airfoil 3 is arranged obliquely to the longitudinal axis of the airfoil 3.
  • the frontal free end 2 of the airfoil 3 is inclined to the direction of vapor flow 7.
  • a shroud 1 is advantageously applied to an airfoil 3, as shown in Fig. 5, a prefabricated shroud 1 is advantageously applied. This can be done for example by shrinking or sticking the shroud 1.
  • the prefabricated shroud 1 preferably has a side surface which corresponds to the inclination of the frontal free end 2 of the airfoil 3.
  • a well-damping intermediate layer is introduced between the frontal free end 2 of the airfoil 3 and the applied shroud 1.
  • This is preferably formed of a rubber.
  • the sealing tips 5 can be inserted into the trough 4 according to FIG. 1 or produced in the infiltration process of the matrix material in a wound into the trough 4 band of a fiber material. Alternatively, the sealing tips 5 may already be prefabricated in the finished shroud.
  • the sealing tips 5 are made of plastic, resin, CFRP, thermoplastic or another favorable material.
  • the sealing tips 5 are over-revved in hindsight and after any annealing process for dimensional stability. It is also possible to perform the sealing tips 5 so that by touching briefly with the Stator sets the game on its own. On the other hand, it is also possible to use steel sealing tips 5 in the shroud 1.
  • FIG. 7 shows a plan view of four blades 3 and a shroud 1 arranged on the blades 3.
  • the shroud 1 is applied to the free end of the blades 3.
  • the width of the shroud 1 may vary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne en particulier un procédé pour le montage ou la confection d'un anneau de renfort fermé (1) sur les extrémités frontales libres (2) de pales d'aubes (3) disposées côte à côte d'un aubage mobile d'un étage de turbine. Selon l'invention, on enroule une bande en matériau fibreux sur les extrémités frontales libres (2) des pales d'aubes (3), on infiltre un matériau de matrice dans le matériau fibreux de la bande enroulée et on fait durcir le matériau composite fibreux ainsi obtenu. L'invention concerne également deux autres procédés pour le montage et la confection d'un anneau de renfort fermé (1) sur les extrémités frontales libres (2) de pales d'aubes (3) disposées côte à côte d'un aubage mobile d'un étage de turbine, ainsi qu'un aubage mobile pour une turbine, cet aubage comprenant une pluralité de pales d'aubes (3) disposées côte à côte qui sont constituées d'un matériau composite fibreux.
EP10702677A 2009-02-25 2010-02-04 Procédé de fixation ou de fabrication d' un anneau de renfort fermé pour un rotor d'un étage de turbine et rotor de turbine Withdrawn EP2401477A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200910010613 DE102009010613A1 (de) 2009-02-25 2009-02-25 Verfahren zum Anbringen bzw. Herstellen eines geschlossenen Deckbandes für eine Laufbeschaufelung einer Turbinenstufe sowie Laufbeschaufelung einer Turbinenstufe für eine Turbine
PCT/EP2010/051366 WO2010097277A2 (fr) 2009-02-25 2010-02-04 Procédé pour monter ou confectionner un anneau de renfort fermé pour un aubage mobile d'un étage de turbine et aubage mobile d'un étage de turbine pour une turbine

Publications (1)

Publication Number Publication Date
EP2401477A2 true EP2401477A2 (fr) 2012-01-04

Family

ID=42371723

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10702677A Withdrawn EP2401477A2 (fr) 2009-02-25 2010-02-04 Procédé de fixation ou de fabrication d' un anneau de renfort fermé pour un rotor d'un étage de turbine et rotor de turbine

Country Status (3)

Country Link
EP (1) EP2401477A2 (fr)
DE (1) DE102009010613A1 (fr)
WO (1) WO2010097277A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009036018A1 (de) * 2009-08-04 2011-02-17 Siemens Aktiengesellschaft Thermoplastendstufenschaufel
US9151166B2 (en) * 2010-06-07 2015-10-06 Rolls-Royce North American Technologies, Inc. Composite gas turbine engine component
EP2431571B1 (fr) * 2010-09-16 2013-06-05 Techspace Aero S.A. Assemblage d'un aube et d'un support composite par scellage

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GB835177A (en) * 1957-06-14 1960-05-18 Burton Albert Avery Vibration damping shroud for gas turbine engines
US3501090A (en) * 1968-01-29 1970-03-17 Gen Electric Composite bladed rotors
US3977728A (en) * 1974-12-30 1976-08-31 General Electric Company Wheel
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
GB2161110B (en) * 1984-07-07 1988-03-23 Rolls Royce An annular bladed member having an integral shroud and a method of manufacture thereof
US6223524B1 (en) * 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
DE10304529B3 (de) * 2003-02-04 2004-05-27 E & T Energietechnik Gmbh Axialturbine, insbesondere Dampf- oder Gasturbine
GB2427658B (en) * 2005-06-30 2007-08-22 Rolls Royce Plc Organic matrix composite integrally bladed rotor
EP1788197A1 (fr) * 2005-11-21 2007-05-23 Siemens Aktiengesellschaft Aube de turbine pour turbine à vapeur
DE102006025883A1 (de) * 2006-06-02 2007-12-06 Mtu Aero Engines Gmbh Gasturbinenrotor

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Title
See references of WO2010097277A3 *

Also Published As

Publication number Publication date
DE102009010613A1 (de) 2010-09-02
WO2010097277A3 (fr) 2011-06-23
WO2010097277A2 (fr) 2010-09-02

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