WO2010026005A1 - Aube de turbine à fréquence propre adaptée au moyen d'un élément rapporté - Google Patents

Aube de turbine à fréquence propre adaptée au moyen d'un élément rapporté Download PDF

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Publication number
WO2010026005A1
WO2010026005A1 PCT/EP2009/059954 EP2009059954W WO2010026005A1 WO 2010026005 A1 WO2010026005 A1 WO 2010026005A1 EP 2009059954 W EP2009059954 W EP 2009059954W WO 2010026005 A1 WO2010026005 A1 WO 2010026005A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine blade
airfoil
turbine
natural frequency
Prior art date
Application number
PCT/EP2009/059954
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2010026005A1 publication Critical patent/WO2010026005A1/fr

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods

Definitions

  • the invention relates to a turbine blade for a gas turbine, with a platform and an airfoil arranged transversely thereon, comprising a pressure-side blade leaf wall and a suction-side blade leaf wall, which
  • Blade blade walls at least partially define a arranged in the interior of the airfoil cavity. Furthermore, the invention relates to a method of manufacturing a turbine blade with a hollow airfoil.
  • turbine blades are subject to vibrational excitation during operation in a gas turbine engine.
  • the vibration excitation occurs due to the rotation of the rotor to which the turbine blades are attached.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. Therefore, care is taken in the development of the turbine blade that the finished Turbi ⁇ nenraisingschaufel total meets the requirements relating to the natural resonance. In the manufacturing process of the turbine blade is therefore seen ⁇ to review every turbine blade on their oscillations ⁇ transfer properties. If the turbine blade does not meet the predetermined frequency values at natural frequency, this is to be discarded or manipulated by suitable measures such that it is then suitable for operation and meets the requirements of the natural frequency.
  • Vibration property are not intended for use in the gas turbine to feed yet use, for example, from EP 1 439 281 A2 known to provide or introduce a recess on the blade of the turbine blade end face, whereby the mass of the turbine blade are reduced at its free, schwmgfahigen end can.
  • the vibration characteristic is positively influenced.
  • Their natural frequency can be shifted to greater natural frequencies by removing the mass, in particular at its outer end.
  • EP 1 217 171 A2 a method of manufacturing a turbine blade is known in which a rib inside the airfoil is added only due to insufficient vibration characteristics of a finished turbine blade to change the natural frequency of the turbine blade.
  • GB 2 106 996 A shows only a partial attachment of a baffle insert, so that it exerts a dampening function when vibrations of the airfoil occur.
  • the object of the invention is to provide a turbine blade and the specification of a method for producing turbine blades, the natural frequency of which corresponds to the requirements for use within a stationary gas turbine.
  • the object directed to the turbine blade is solved by a turbine blade according to the features of claim 1.
  • the object directed to the method is achieved by a method for producing a turbine blade according to the features of claim 5.
  • the invention is based on the finding that a turbine blade for a gas turbine can be adapted with regard to its natural frequency and rigidity, without its outer contour having to be changed.
  • the change in the natural frequency of the turbine blade or the change in the rigidity of the blade can be done in a simple manner by at least one means is provided in at least one cavity of the blade of the turbine blade, the arrangement of which mainly the change of the natural frequency or the change in stiffness of the airfoil serves.
  • the invention thus resists the idea that the internal structure of a turbine blade is dictated solely by the outer aerodynamic contour of the airfoil and solely by cooling requirements typically associated with a turbine blade.
  • the invention proposes additional means in the cavity of a turbine engine. To provide a bucket, which serve mainly or solely to change the natural frequency of the turbine blade - by changing the center of gravity of the blade and / or its stiffness - compared to an identical turbine blade, but without this inventive means.
  • the invention is thus of particular advantage for turbine blades which have already been used in gas turbines and are therefore operationally stressed. Often, it is precisely these turbine blades that will continue to be used after a gas turbine upgrade (upgrade), although there is increased demand on the turbine blades for their natural frequency due to the changed operating conditions of the gas turbine as a result of the upgrade.
  • the invention now provides methods and means for adapting the turbine blade operated to operation to the new operating conditions independently of any possible additional refurbishment, in which case the changes take place only in the interior, that is to say in the cavity of the blade, without damaging the blade Aerodynamics of the relevant turbine blade - based on the hot air flowing around the blade to change. It is therefore proposed that, after producing a turbine blade with a high airfoil, an insert member is mounted in its cavity, the arrangement of the insert member mainly or exclusively of changing the natural frequency of the turbine blade.
  • the turbine rotor blades to be newly produced for an upgraded gas turbine can be manufactured by means of the still existing tool, in particular the casting apparatus in which the relevant turbine rotor blade is cast.
  • the casting apparatus in particular its slider which predetermines the outer shape of the turbine blade, can then continue to be used unchanged.
  • a new Casting core can be used for a casting apparatus for producing a turbine blade, wherein the casting core has successive sections which have a constant cross-section or a continuously varying cross-section along its extension, wherein the
  • Cast core between two such sections has a further section with compared to substantially reduced cross-section.
  • the turbine blade can also be manufactured in one production step.
  • the agent in question is designed as an insert component which is manufactured separately from the airfoil and which is fastened in its cavity after production of the airfoil.
  • the agent in question may also be an integral part of the airfoil, so that this is produced directly with the production of the airfoil of the turbine blade. This is the case, for example, if at least the blade of the turbine blade, or even the entire turbine blade is produced by a casting process.
  • the airfoil is divided by means of at least one rib into a plurality of cavities, which rib extends in each case from the suction-side airfoil wall to the pressure-side airfoil wall and at the same time from a foot region of the turbine blade to an airfoil tip region.
  • the invention can thus be used in particular for turbine blades are, the pure or approximately rectilinear Kuhlkanale ⁇ has, which extend from a foot portion of the turbine blade ⁇ blade to a blade tip area and are separated by a rib arranged in the interior of the blade leaf.
  • such turbine blades are provided on the blade tip side with an opening in the order of the cross section of the cavity arranged behind, so that sufficient accessibility to the respective cavities is present, in which the agent is to be arranged and fixed.
  • the means or the insert component is designed as a partition wall disposed approximately parallel to the platform of the turbine blade, in which at least one opening is formed.
  • the partition wall is thus substantially perpendicular, if present, oriented to the rib.
  • at least one opening is provided in the dividing wall.
  • this can be changed in its contour, for example by means of a machining method, in order to bring about a further change in the natural frequency of the turbine blade.
  • the opening can be drilled further. This makes it possible to further adapt the frequency characteristic of the turbine blade even after the attachment component has been fastened.
  • a correspondingly formed casting core can be used in a casting apparatus for producing a turbine blade.
  • Such cast ⁇ core is substantially stabformig formed with a plurality of successive sections which ckung have along their Tilere- either a constant cross section or a continuously changing cross-section, wherein the casting core between two such sections a further section with substantially reduced as compared to Has cross-section through which the relevant means, in particular the dividing wall, can be formed.
  • the Gusskernabites with significantly reduced cross-section has a maximum of a cross-sectional area of 90% of the cross-sectional area of the immediately adjacent to him section with constant cross-section or with continuously changing cross-section.
  • the cross-sectional area should be chosen as small as possible so that the opening formed by it and arranged in the dividing wall can be reworked.
  • the transition between the further section and the immediately adjacent section with constant cross-section or with continuously changing cross-section may be step-like.
  • two or more of these further sections of substantially reduced cross-section may be present on the casting core.
  • Each section of the casting core having a substantially reduced cross-section is arranged on the casting core in such a way that it is manufactured at a casting core made with this casting core
  • Turbine bucket leaves a partition wall, which is in the cavity of a blade of the turbine blade - that is arranged in the interior - and not at the blade tip.
  • Erfmdungsgetake to be provided means, which is preferably designed as a partition, mainly or solely the change in the natural frequency of Serving turbine blade. This is achieved by significantly changing the rigidity of the airfoil and / or the center of gravity of the airfoil by the insert component as compared to an identical turbine blade without insert component.
  • means should not be understood to mean turbulators which, arranged on the inner side surfaces of the airfoil walls, are intended mainly to swirl the cooling air flowing along the seldom walls.
  • impact-cooling inserts which, for example, can be arranged inside the turbine blade, in order to allow impact padding of the blade blade walls.
  • ribs located inside the airfoil do not fall underneath.
  • the agents according to the invention are used, at least primarily, if not solely for the purpose of modifying the
  • At least as many means are provided that a change in the preferably first natural frequency of the turbine blade of at least 5 Hz, more preferably at least 10 Hz - based on an identical turbine blade without the inventive means - can be brought about.
  • FIG. 1 shows a longitudinal section through a turbine blade 10 according to the invention, which has a foot region 12, a hot gas platform 14 and an aerodynamically curved blade 16 extending transversely thereon along a main blade axis.
  • the airfoil 16 includes a pressure-side airfoil wall 18 (FIG. 2) and a suction-side airfoil wall 20, which extend from a common front edge 22 to a common trailing edge 29.
  • the airfoil 16 is substantially hollow latest available ⁇ det, wherein in FIG 1, three cavities 24, 26, 28 are shown. The cavities 24, 26 are separated by a first rib 32 and the two cavities 26, 28 are separated by a second rib 34.
  • the turbine runner 10 it is possible for the turbine runner 10 to be more than three or less than three
  • Hollow spaces 24, 26, 28 and accordingly more or fewer ribs 32, 34 has.
  • the ribs 32, 34 extend from the suction-side blade wall 20 to the pressure-side blade wall 18 and at the same time from the foot region 12 of the turbine runner 10 to the blade tip region 30.
  • the cavities 24, 26, 28 are considered to be straight from the root region 12 to a tip-side region 30 extending Kuhlkanale formed by which a fuß season zugeschreibtes Kuhlsch, for example Kuhlluft, is strombar, which can escape shovel blade tip side.
  • means 38 formed as insert components 36 may be subsequently fixed after casting of the turbine blade 10.
  • the insert members 36 are formed as a partition wall and serve to change the natural frequency of the turbine blade 10 and / or the change in the rigidity of the airfoil 16 without having another essential function. Impact chill patches, rib-like turbulators or even dimples do not fall under the concept of the means according to the invention.
  • the replacement components 36 each have a central one Opening 40, through which the cavities 24, 26, 28 can flow through ⁇ flowing coolant.
  • insert member 36 is formed as a partition, this can be positioned by the blade tip-side, wide opening 40 of the cavities 24, 26, 28 in the interior of the blade 16 and the ribs 32, 34 and the mecanicfla ⁇ surfaces of the suction-side blade wall 20 and be angelotet or welded to the inner surface of the pressure-side blade wall 18.
  • a casting core 50 according to the invention shown in FIG. 3 is required, which is substantially rod-shaped and has a plurality of successive sections 52, 54, 56, 68.
  • Each of these sections 52, 54, 56, 58 has along its extent a constant cross-section or at least only slightly continuously changing cross-section, wherein the casting core 50 between two such sections 52, 54, 56, 58 another section 60 with in Compared to having significantly reduced cross-section.
  • the cross-sectional area of the reduced cross section 60 amounts to a maximum of 90% of the cross-sectional area of the sections 52, 54, 56, 58 with a constant cross section or with a continuously decreasing cross section.
  • the transition between the cut 52, 54 and portion 60 is effected in each case by means of a stage, three From ⁇ sections 60 are provided with a reduced cross-section in the example illustrated further. There may also be more or fewer sections 60 of reduced cross-section. If another section 60 has a particularly small cross-sectional area, this further increases the strength, in which case the remaining separating web 36 can be easily changed if necessary.
  • the casting core 50 is designed such that the sections 52, 54, 56, 58 of reduced cross section lie in such a position that these partitions leave behind 36, which in the interior of the cavity 24, 26, 28 of a blade 16 of the Turbine blade 10 arranged to cause a particularly large increase in rigidity.
  • the invention provides a turbine blade 10 for a gas turbine, which is a hollow airfoil
  • the invention provides a method by means of which, after the manufacture of the blade 16, an insert component 36 is fastened in its cavity 24, 26, 28, the arrangement of which mainly serves to change the natural frequency of the turbine blade 10. If a further change in the frequency characteristic of the turbine blade 10 is required after installation of the fitting 36, for example, the diameter of the opening 40 in the separating web 36 can be increased, for example, by drilling. It is only necessary to ensure that the concomitant reduction in the mass of the turbine blade does not cause too great a change in the rigidity of the blade 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Abstract

L'invention concerne une aube de turbine (10) destinée à une turbine à gaz, présentant une pale (16) creuse dans laquelle au moins un moyen (38) est disposé pour que l'aube de turbine (10) puisse être adaptée à de nouvelles conditions de service, ce moyen (38) servant principalement à modifier la fréquence propre de l'aube de turbine (10). L'invention concerne également un procédé selon lequel, après la fabrication de la pale (16), un élément rapporté (36) est fixé dans la cavité (24, 26, 28) de la pale (16), l'agencement de cet élément servant principalement à modifier la fréquence propre de l'aube de turbine (10).
PCT/EP2009/059954 2008-09-05 2009-07-31 Aube de turbine à fréquence propre adaptée au moyen d'un élément rapporté WO2010026005A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP08015726.6 2008-09-05
EP08015726A EP2161411A1 (fr) 2008-09-05 2008-09-05 Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion

Publications (1)

Publication Number Publication Date
WO2010026005A1 true WO2010026005A1 (fr) 2010-03-11

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Application Number Title Priority Date Filing Date
PCT/EP2009/059954 WO2010026005A1 (fr) 2008-09-05 2009-07-31 Aube de turbine à fréquence propre adaptée au moyen d'un élément rapporté

Country Status (2)

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EP (1) EP2161411A1 (fr)
WO (1) WO2010026005A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9670797B2 (en) 2012-09-28 2017-06-06 United Technologies Corporation Modulated turbine vane cooling
EP2725193B1 (fr) 2012-10-24 2015-07-29 MTU Aero Engines AG Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.
EP2792434A1 (fr) * 2013-04-19 2014-10-22 Alstom Technology Ltd Procédé de fabrication d'un composant ayant une structure d'amortissement
US20160199954A1 (en) * 2013-09-09 2016-07-14 Siemens Aktiengesellschaft Combustion chamber for a gas turbine, and tool and method for producing cooling ducts in a gas turbine component
GB2518379A (en) * 2013-09-19 2015-03-25 Rolls Royce Deutschland Aerofoil cooling system and method
CN112177681B (zh) * 2020-09-21 2022-03-15 西北工业大学 一种适用于涡轮叶片内部冷却的分形间断肋结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19839592A1 (de) * 1998-08-31 2000-03-02 Asea Brown Boveri Strömungsmaschine mit gekühlter Rotorwelle
EP1217172A2 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Procédé pour réduire la variance de la consommation d' agent réfrigerant aux composants d' une turbomachine
EP1217171A2 (fr) 2000-12-22 2002-06-26 General Electric Company Nervure pour influencer la fréquence propre d'une aube de turbine
DE10348413A1 (de) * 2002-10-15 2004-06-24 General Electric Company Verfahren zum Erzeugen einer Wirbelströmung auf der Innenseite von Löchern in einem Gegenstand und dazugehörige Gegenstände
EP1439281A2 (fr) 2003-01-18 2004-07-21 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz
EP1510653A2 (fr) 2003-07-29 2005-03-02 Siemens Aktiengesellschaft Aube de turbine refroidie

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2106996A (en) * 1981-09-30 1983-04-20 Rolls Royce Cooled rotor aerofoil blade for a gas turbine engine
US7588421B2 (en) * 2006-03-31 2009-09-15 General Electric Company Methods and apparatus for mechanical retainment of non-metallic fillers in pockets

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19839592A1 (de) * 1998-08-31 2000-03-02 Asea Brown Boveri Strömungsmaschine mit gekühlter Rotorwelle
EP1217172A2 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Procédé pour réduire la variance de la consommation d' agent réfrigerant aux composants d' une turbomachine
EP1217171A2 (fr) 2000-12-22 2002-06-26 General Electric Company Nervure pour influencer la fréquence propre d'une aube de turbine
DE10348413A1 (de) * 2002-10-15 2004-06-24 General Electric Company Verfahren zum Erzeugen einer Wirbelströmung auf der Innenseite von Löchern in einem Gegenstand und dazugehörige Gegenstände
EP1439281A2 (fr) 2003-01-18 2004-07-21 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz
EP1510653A2 (fr) 2003-07-29 2005-03-02 Siemens Aktiengesellschaft Aube de turbine refroidie

Also Published As

Publication number Publication date
EP2161411A1 (fr) 2010-03-10

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