EP1215363B1 - Aube refroidie pour turbine à gaz - Google Patents

Aube refroidie pour turbine à gaz Download PDF

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Publication number
EP1215363B1
EP1215363B1 EP01128573A EP01128573A EP1215363B1 EP 1215363 B1 EP1215363 B1 EP 1215363B1 EP 01128573 A EP01128573 A EP 01128573A EP 01128573 A EP01128573 A EP 01128573A EP 1215363 B1 EP1215363 B1 EP 1215363B1
Authority
EP
European Patent Office
Prior art keywords
cover plate
gas turbine
turbine blade
cooled gas
shroud
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.)
Expired - Lifetime
Application number
EP01128573A
Other languages
German (de)
English (en)
Other versions
EP1215363A3 (fr
EP1215363A2 (fr
Inventor
Alexander Dr. Beeck
Reinhard Fried
Markus Oehl
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 EP1215363A2 publication Critical patent/EP1215363A2/fr
Publication of EP1215363A3 publication Critical patent/EP1215363A3/fr
Application granted granted Critical
Publication of EP1215363B1 publication Critical patent/EP1215363B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/187—Convection cooling
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/191—Two-dimensional machined; miscellaneous perforated

Definitions

  • the invention relates to a cooled gas turbine blade with a Shroud in which a cooling channel system is provided, which is radially to Gas turbine blade is completed with a cover plate.
  • the heat-exposed plant components can be increased by providing appropriate cooling duct systems through targeted supply of Cooling air actively cooled.
  • Gas turbine blades are present in a manner known per se, regardless of whether they are to guide or moving blades, usually from a blade root and an airfoil, which is usually projected radially from a shroud.
  • the im Inside a gas turbine blade provided cooling system is usually from a plurality of individual cooling channels extending radially from the sides of the blade root extend through the entire turbine blade to the shroud.
  • Within the shroud cooling duct areas are provided in which the cooling air and Deflection flow guide structures are provided to the cooling effect within to improve the shroud.
  • the cooling channels producing casting core present turbine blade especially in the area of the shroud large openings, although a subsequent insertion of the aforementioned flow guide structures,
  • a baffle-cooling plate but allow, it is gas-tight seal.
  • Closure plate or so-called cover plate usually with the shroud the gas turbine blade is connected by means of high temperature soldering.
  • Fig. 2a to 2c is a known connection between a cover plate. 6 and the shroud 2 of a turbine blade.
  • Fig. 2a is a perspective view of a turbine blade with an airfoil 1 and a shroud 2 shown.
  • the shroud 2 has two each with a groove contour. 3 trained side edges 4 and 5, along which a cover plate. 6 is inserted positively.
  • the cross section along the section line S1 is shown in FIG. 2b.
  • the groove contour 3 partially covers the in the shroud. 2 inserted cover plate 5, in addition to the positive connection between the groove contour 3 and the cover plate 6 is fixed by a solder joint 7. From the Cross-sectional view according to FIG. 2b are those between the cover plate 6 and the cover band 2 enclosed cooling channels K to remove through the cooling air by not shown in the further cooling system within the Gas turbine blade is passed.
  • the invention is based on the object, a cooled gas turbine blade with a shroud, in which a cooling channel system is provided, which is radially to the Gas turbine blade is completed with a cover plate to train such that the cover plate is provided with the shroud in a secure manner and at the above-mentioned total loss of the cover plate are excluded can. Furthermore, leakage losses occur when cracks occur in the joint connection between the cover plate and the shroud to minimize crucial. The too appropriate measures should thereby only a small design effort by which the manufacturing cost of cooled gas turbine blades not or only slightly more expensive.
  • a cooled gas turbine blade according to the preamble of Claim 1 formed such that the cover plate has a peripheral edge, along the entire extent of the cover plate with the shroud of Gas turbine blade a continuous form joint or a variety locally Limited form compounds received.
  • an inventively designed shroud looks at the shape and size of the peripheral edge of the cover plate adapted receiving contour in Meaning of a box frame, in which the cover plate radially to the full extent can be inserted.
  • the receiving contour preferably has one stepped cross-section, comparable to that of a picture frame in which a Picture can be pasted on the back.
  • the step-shaped cross-section of Receiving contour in this case has a radially or obliquely radially first and one axially oriented second step surface, the so-called contact surface, on the the cover plate can be placed with its entire peripheral edge.
  • the Direction data radially or axially refer to conventional Directional information, in conjunction with an axial flowed rotor assembly usually used within a gas turbine plant.
  • a joining agent preferably soldering material
  • the solder material is selected such that the Solders after the soldering and / or heat treatment process no or only has a low ductility, so is brittle.
  • solder material inherent brittleness occur at the beginning of the first commissioning of the gas turbine blades due to thermally induced Deformations cracks within the solder seam, which turn out to be "zigzag” shaped form extending fracture lines or surfaces and the soldering seam completely push through. Surprisingly, it is precisely these training Fracture surfaces that guarantee a secure fit and also to a BiegeHarsstage solder joint between cover plate and shroud contribute.
  • the forming within the solder seam hair tear basically a Cooling air leakage is limited by the cooling air from that of the cover plate Cooling air system within the gas turbine blade can escape to the outside, but this cooling air loss is negligible and does not matter further.
  • form on the surfaces of the crack within the solder seam Oxidation layers on the one hand able to reduce the crack gap and in addition, for a play-free fit of the cover plate within the through Lötnaht predetermined positive connection despite prevailing large Ensure vibrations during operation of the gas turbine.
  • this provides the first, preferably radially oriented step surface of the receiving contour within the shroud a circumferential mounting groove in front, in the at least half the outer contour of a Snap ring can engage, which surrounds the cover plate in a suitable form.
  • One Inserting the cover plate in the receiving contour of the shroud is done by mechanical constriction of the circlip following correspondingly have within the mounting groove in the shroud spread out and thus a positive connection between shroud and cover plate guaranteed.
  • rod-shaped holding means to create a Positive connection between cover plate and shroud can be used by passing them through suitable holes in the cover plate and the Shroud to be inserted.
  • the rod-like holding means can tangential or radial running between cover plate and shroud in corresponding mounting holes are inserted. While being on this Do not cover the top plate along its entire peripheral edge continuous positive connection with the shroud has, as it is in a circumferential solder joint is the case, but is also in this way for a secure fit of the cover plate provided in the shroud.
  • Fig. 1a shows a perspective top view of a gas turbine blade with a Shroud 2, which at its radially oriented upper side a rectangular Recess 10 provides, in which the cover plate 6 radially from above completely is inserted. Between the cover plate 6 and the shroud 2 is a solder seam. 7 introduced, which completely surrounds the peripheral contour of the cover plate 6.
  • Fig.1b is a cross section through an arbitrary position transverse to the receiving contour shown within the shroud 2.
  • the receiving contour of the shroud 2 has a first obliquely radially directed first step surface 11 and one axially oriented second step surface, the so-called support surface 12.
  • the step depth the receiving contour is preferably just chosen so that the surface of the Cover plate 6 is flush with the surface of the shroud 2.
  • a Intermediate gap 13 is provided, which is at least chosen so large that a simple Inserting the cover plate 6 in the receiving contour of the shroud 2, due to a existing installation play 16 is possible.
  • the between the cover plate 6 and the shroud 2 located intermediate gap 13 is subsequently with solder 14th completely filled and soldered, the solder 14 has the lowest possible Has ductility or high brittle hardness after the soldering process.
  • FIG. 3a shows such a crack 15, which consists of two Zigzag-shaped, directly opposite fracture surfaces composed. Since the crack course takes a statistical course and thus along the fracture surfaces has fracture surface portions which are inclined to the Radial direction of the gas turbine blade and thus to the at the Gas turbine blade attacking centrifugal forces are inclined, wearing an intimate Gearing between the cover plate 6 and the shroud along the Lötnaht thereto in that the cover plate 6 can not come off the shroud 2. Furthermore allows the loose multi-pronged form-fitting connection a stress-free seat the cover plate 6 within the shroud, whereby the cover plate 6 lower mechanical stresses as well as vibrations is exposed.
  • Fig. 3b shows a joining variant using an additional Closure strip 16, which is soldered on both sides by two solder seams 7, 7 '.
  • the Closure strip 16 is made of a high temperature resistant material, which has a much higher ductility than the material itself, so that the Closure strip 16 to a vibration damping of the cover plate 6 within contributes the shroud 2.
  • FIG. 4a the insertion process of the cover plate 6 is shown in the receiving contour of the shroud 2.
  • An installation play 16 present between the cover strip 2 and the cover plate 6 ensures unimpeded radial insertion of the cover plate 6 into the cover strip 2.
  • FIG. 4b shows the insertion of a closure piece 17 as a function of a mechanical holding means 18 , which is integrally formed as a molded part in the intermediate gap 13 is inserted.
  • the closure piece 1 7 has a sufficiently high ductility and high temperature resistance, so that it is able to transfer the forces occurring between the cover plate 6 and the shroud 2 harmless.
  • Fig. 4c a force distribution between the cover plate 6, the closure piece 17 and the shroud 2 is shown.
  • Fig. 5a, b and c are different embodiments of Positive connection between the cover plate 6 and the shroud. 2 shown.
  • Fig. 5a is a radially directed gap between shroud 2 and Cover plate 6 filled with solder material.
  • Fig. 5b shows an obliquely radially inclined soldering gap.
  • Fig. 5c the intermediate gap between the cover plate 6 and Shroud 2 radially formed and only in the upper region is a wedge-shaped solder joint 7 introduced. This surpasses this Shroud 2, the cover plate 6 a little, so that a dreieickförmiger solder wedge. 7 can form between shroud 2 and cover plate 6.
  • a Set crack course which is approximately 45 ° relative to the radial direction and thus to a stable positive connection between the cover plate 6 and the Shroud 2 leads.
  • Fig. 6 shows For this purpose, a corresponding connection cross section between cover plate 6 and Shroud 2. Between the shroud 2 and the cover plate 6 is a snap ring 18th introduced on both sides partially in the peripheral edge of the cover plate 6 and in the shroud 2 protrudes.
  • a snap ring 18 rod-shaped molded body can be provided by lateral mounting openings within the cover strip and the cover plate can be introduced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (12)

  1. Aube de turbine à gaz refroidie comprenant une virole (2), dans laquelle un système de canal de refroidissement (K) est prévu, lequel est fermé radialement à l'aube de turbine à gaz avec une plaque de recouvrement (6),
    caractérisée en ce que la plaque de recouvrement (6) présente un bord périphérique le long de toute l'étendue duquel la plaque de recouvrement (6) réalise avec la virole (2) une liaison par coopération de forme continue ou une pluralité de liaisons par coopération de forme limitées localement.
  2. Aube de turbine à gaz refroidie selon la revendication 1,
    caractérisée en ce que la pluralité de liaisons par coopération de forme limitées localement est répartie uniformément le long du bord périphérique.
  3. Aube de turbine à gaz refroidie selon la revendication 1 ou 2,
    caractérisée en ce que la virole (2) présente un contour de réception adapté suivant la forme et la taille du bord périphérique de la plaque de recouvrement (6), avec une section transversale étagée, qui comprend une première surface étagée (11) orientée radialement ou obliquement radialement et une deuxième surface étagée (12) orientée axialement, que l'on appelle la surface d'appui, sur laquelle la plaque de recouvrement (6) peut être placée radialement, et
    en ce que dans la région entre la première surface étagée (11) et le bord périphérique de la plaque de recouvrement (6) on monte un moyen de fixation qui garantit la liaison par coopération de forme.
  4. Aube de turbine à gaz refroidie selon la revendication 3,
    caractérisée en ce que l'on prévoit une fente intermédiaire (13) entre la première surface étagée (11) et la plaque de recouvrement (6) insérée dans le contour de réception.
  5. Aube de turbine à gaz refroidie selon la revendication 4,
    caractérisée en ce que la première surface étagée (11) et le bord périphérique sont réalisés de manière rectiligne et la fente intermédiaire (13) présente une largeur de fente substantiellement constante, et
    en ce que la fente intermédiaire (13) est orientée radialement ou obliquement radialement par rapport à la direction longitudinale de l'aube de turbine à gaz.
  6. Aube de turbine à gaz refroidie selon l'une quelconque des revendications 3 à 5,
    caractérisée en ce que le moyen de fixation est un moyen de joint qui est monté dans la région entre la première surface étagée (11) et le bord périphérique de la plaque de recouvrement (6) et qui réalise une liaison par joint intime à chaque fois avec la première surface étagée (11) et le bord périphérique, et
    en ce qu'à l'intérieur du moyen de joint le long de l'étendue des deux liaisons par joint, au moins une surface de rupture (15) traversant complètement le moyen de joint est prévue, avec des portions de surface de rupture s'étendant obliquement par rapport à la direction radiale.
  7. Aube de turbine à gaz refroidie selon la revendication 6,
    caractérisée en ce que le moyen de joint est un matériau de brasage (7) qui ne possède aucune ductilité ou une très faible ductilité.
  8. Aube de turbine à gaz refroidie selon l'une quelconque des revendications 3 à 6, caractérisée en ce que la première surface étagée (11) est dimensionnée de telle sorte qu'elle dépasse de la plaque de recouvrement (6) insérée dans le contour de réception, en ce que le moyen de joint est prévu au moins au-dessus de la plaque de recouvrement (6) entre la plaque de recouvrement (6) et la première surface étagée (11) dépassant de la plaque de recouvrement (6), et en ce que la surface de rupture (15) traverse obliquement radialement le moyen de joint.
  9. Aube de turbine à gaz refroidie selon la revendication 8,
    caractérisée en ce que la surface de rupture (15) s'étend dans une plage angulaire d'environ 45° par rapport à la plaque de recouvrement (6).
  10. Aube de turbine à gaz refroidie selon la revendication 3,
    caractérisée en ce que le bord périphérique de la plaque de recouvrement (6) présente un contour de fixation s'étendant le long du bord périphérique, dans lequel on peut monter un moyen de fixation mécanique (18), et
    en ce qu'un contour de fixation correspondant au contour de fixation de la plaque de recouvrement (6) est prévu le long de la première surface étagée (11), dans lequel débouche par engagement positif le moyen de fixation mécanique (18) dans l'état assemblé de la plaque de recouvrement (6) à l'intérieur du contour de réception.
  11. Aube de turbine à gaz refroidie selon la revendication 10,
    caractérisée en ce que le moyen de fixation mécanique (18) est une espèce de jonc, qui est prévu à l'intérieur du contour de fixation de la plaque de recouvrement (6).
  12. Aube de turbine à gaz refroidie selon la revendication 10,
    caractérisée en ce que le moyen de fixation mécanique (18) se compose d'une pluralité de corps moulés réalisés en forme de barre, qui peuvent être montés à travers des ouvertures de montage latérales à l'intérieur de la virole entre le bord périphérique de la plaque de recouvrement et la première surface étagée dans le contour de fixation.
EP01128573A 2000-12-16 2001-11-30 Aube refroidie pour turbine à gaz Expired - Lifetime EP1215363B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10062907 2000-12-16
DE10062907 2000-12-16

Publications (3)

Publication Number Publication Date
EP1215363A2 EP1215363A2 (fr) 2002-06-19
EP1215363A3 EP1215363A3 (fr) 2004-01-02
EP1215363B1 true EP1215363B1 (fr) 2005-10-05

Family

ID=7667527

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01128573A Expired - Lifetime EP1215363B1 (fr) 2000-12-16 2001-11-30 Aube refroidie pour turbine à gaz
EP01128572A Expired - Lifetime EP1215364B1 (fr) 2000-12-16 2001-11-30 Dispositif de refroidissement d'une virole d'aube dans une turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01128572A Expired - Lifetime EP1215364B1 (fr) 2000-12-16 2001-11-30 Dispositif de refroidissement d'une virole d'aube dans une turbine à gaz

Country Status (4)

Country Link
US (2) US6589011B2 (fr)
EP (2) EP1215363B1 (fr)
JP (1) JP2002201907A (fr)
DE (4) DE10131073A1 (fr)

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EP1503330B1 (fr) 2002-05-09 2010-06-02 Sony Corporation Procede pour identifier un modele biologique, detecteur de modele biologique, procede et dispositif pour etablir un certificat biologique
EP1789654B1 (fr) 2004-09-16 2017-08-23 General Electric Technology GmbH Pale de turbomachine a couronne a refroidissement fluidique
US20070048122A1 (en) * 2005-08-30 2007-03-01 United Technologies Corporation Debris-filtering technique for gas turbine engine component air cooling system
US20110110772A1 (en) * 2009-11-11 2011-05-12 Arrell Douglas J Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same
US9133724B2 (en) * 2012-01-09 2015-09-15 General Electric Company Turbomachine component including a cover plate
US9567857B2 (en) 2013-03-08 2017-02-14 Rolls-Royce North American Technologies, Inc. Turbine split ring retention and anti-rotation method
US10590785B2 (en) * 2014-09-09 2020-03-17 United Technologies Corporation Beveled coverplate
DE102017208680A1 (de) 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Verfahren zum Befestigen eines Kühlbleches an einer Turbinenschaufel
US10370300B2 (en) * 2017-10-31 2019-08-06 General Electric Company Additively manufactured turbine shroud segment
US11156102B2 (en) * 2018-03-19 2021-10-26 General Electric Company Blade having a tip cooling cavity and method of making same
CN114405715B (zh) * 2021-12-28 2023-08-18 东方电气集团东方汽轮机有限公司 一种燃气轮机空心叶片喷涂用装夹工装

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Also Published As

Publication number Publication date
EP1215363A3 (fr) 2004-01-02
EP1215364B1 (fr) 2005-08-03
JP2002201907A (ja) 2002-07-19
US20020127103A1 (en) 2002-09-12
DE50106966D1 (de) 2005-09-08
EP1215363A2 (fr) 2002-06-19
US20020136635A1 (en) 2002-09-26
DE50107607D1 (de) 2006-02-16
US6589011B2 (en) 2003-07-08
DE10131370A1 (de) 2002-06-20
EP1215364A3 (fr) 2004-01-02
EP1215364A2 (fr) 2002-06-19
US6682304B2 (en) 2004-01-27
DE10131073A1 (de) 2002-06-20

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