EP2196624A1 - Gas turbine rotor blade - Google Patents

Gas turbine rotor blade Download PDF

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Publication number
EP2196624A1
EP2196624A1 EP09178286A EP09178286A EP2196624A1 EP 2196624 A1 EP2196624 A1 EP 2196624A1 EP 09178286 A EP09178286 A EP 09178286A EP 09178286 A EP09178286 A EP 09178286A EP 2196624 A1 EP2196624 A1 EP 2196624A1
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EP
European Patent Office
Prior art keywords
blade
tie rod
longitudinal direction
root
individual parts
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.)
Granted
Application number
EP09178286A
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German (de)
French (fr)
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EP2196624B1 (en
Inventor
Herbert Brandl
Sven Schofer
Claus Paul Gerdes
Hans-Peter Bossmann
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Ansaldo Energia IP UK Ltd
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Alstom Technology AG
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Publication of EP2196624A1 publication Critical patent/EP2196624A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a blade for a gas turbine according to the preamble of claim 1.
  • Uncooled hollow turbine blades are usually cast from a material. But it is also known ( US B1-6,331,217 ), large rotor blades of a gas turbine from several separately cast blade parts by liquid phase bonding together. Here, either the blade is divided in the blade longitudinal direction (Fig. 3 of the US B1-6,331,217 ) or the entire airfoil is separated from the platform and the blade root manufactured (Fig. 6 of the US B1-6,331,217 ). This leads, especially in the case of large blades, to the fact that, despite the subdivision, large castings for the airfoil have to be produced and positively connected to one another.
  • the object is solved by the entirety of the features of claim 1.
  • Essential to the invention is that the blade is composed of several individual parts, the material of each of which is adapted to the intended use of the item in question, and that each of the individual parts is significantly smaller in size than the composite blade.
  • the invention thus pursues the idea to build a gas turbine blade from several, relatively small items of different materials whose material properties can be adapted to the respective local loads. Due to the possible variation of the materials, a clear optimization potential with respect to the own weight, the manufacturability and the manufacturing costs of the blade is revealed.
  • the idea of the invention is thus to build the gas turbine blade from several individual parts in order to be able to exploit material properties in a targeted way and to avoid any size-related manufacturing problems.
  • a clear separation of functions between the different parts is to be achieved. This is associated with the known and used materials with a relatively high density. This relationship can be represented by the so-called specific density. This is the relation between material strength values and their density.
  • An embodiment of the blade according to the invention is characterized in that the individual parts are at least partially connected by positive locking.
  • Another embodiment of the blade according to the invention is characterized in that the individual parts of the blade comprise a lower blade part and an upper blade part adjoining thereto in the blade longitudinal direction, the blade blade being divided in the blade longitudinal direction onto the lower and upper blade part, the lower blade part the platform and at least includes a portion of the blade root, and the upper blade portion includes the blade tip with.
  • a further embodiment is characterized in that, for receiving the centrifugal forces acting on the upper blade part, a tie rod extending in the longitudinal direction of the blade is arranged in the blade longitudinal direction, that the tie rod engages with its upper end with the lower end of the upper blade part, and that Tie rod with its lower end introduces the tensile forces in the blade root.
  • the tie rod on a foot portion, which forms part of the blade root and with which the tie rod engages behind the lower blade part.
  • an inwardly angled first angle element is arranged on the upper blade part, wherein the tie rod is in engagement with the upper blade part in that it engages behind the first angle element with a second angle element.
  • the tie rod can also consist of several in the blade longitudinal direction arranged in parallel partial anchors, wherein the partial anchors are spaced transversely to the blade longitudinal direction from each other, and wherein the distance of the partial anchors is determined by subsequently usable spacers.
  • Fig. 1 shows a longitudinal section through a (built) blade according to an embodiment of the invention.
  • the blade 10 of the Fig. 1 consists of three separate components, namely an upper blade portion 18, a lower blade portion 17 and a tie rod 16.
  • the blade 10 has an aerodynamically effective airfoil 11 extending in the blade longitudinal direction between a blade tip 15 and a platform 12.
  • the airfoil 11 is divided longitudinally onto the upper blade part 18 and onto the lower blade part 17.
  • a shroud segment 18b is formed at the upper end of the upper blade part 18.
  • an inwardly projecting first angle member 18a is formed, behind which engages the inner tie rod 16 with a mounted at its upper end second angle member 16a and thus holds the upper blade member 18 against the centrifugal forces occurring.
  • the upper blade part 18 is thus loaded only on train.
  • the lower blade part 17 comprises the lower part of the blade 11, the platform 12 a shaft 13 and a part of a blade root 14, which in the shown example, a fir tree-like edge profile (with 3 teeth) has.
  • Another part of the blade root 14 is formed by a foot section 16b, with which the tie rod 16 engages behind the lower blade part 17.
  • the upper blade portion 18 and the lower blade portion 17 must have a significantly higher temperature and creep resistance than the inner tie rod 16.
  • the materials used for the parts 17, 18 on the one hand and the part 16 on the other hand can be correspondingly different. Within the blade height, however, the temperatures vary so strongly that the use of differently adapted materials is also recommended for the two blade parts 17 and 18.
  • Even the tie rod 16 can - as in Fig. 1 indicated by the different hatching - if necessary in the longitudinal direction consist of different materials. But it can also be made of a material throughout.
  • the assembly of an inventive blade can be done in different ways: If the tie rod 16 is not divided in the longitudinal direction in a median plane 19, he can, for example, 90 ° twisted introduced from below into the blade interior and then by a rotation of 90 ° back into engagement with the angle member 18a at the lower end of the upper blade portion 18 are brought.
  • a tie rod 21 divided in the longitudinal direction which comprises two partial anchors 22 and 23 which are mirror-symmetrical to one another, which are spaced apart transversely in the installed state and are kept at a distance by corresponding spacers 24 and 25.
  • the two partial anchors 22, 23 are first inserted without spacers 24, 25 and without transverse spacing in the blade interior until the partial anchors 22, 23 can engage with their upper angle elements 22b, 23b behind the angle elements 18a of the airfoil.
  • the upper (round) spacer 25 from below between the two partial anchors pushed up until he was in Fig. 2 has reached the position shown and the two partial anchors 22, 23 fixed in the hooked position.
  • the lower spacer 24 is inserted between the partial anchors 22, 23 so that they are supported with lower angle elements from the inside on a shoulder on the blade root 14.

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  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The blade (10) has a blade vane (11), a blade tip (15), a blade root (14) and a platform (12) that is formed between the blade tip and the blade root. A tie rod (16), a lower blade part (17) and an upper blade part (18) are made of different materials based on the application, where material properties are adaptable to respective local loads. The dimensions of the tie rod, the upper blade part and the lower blade part are clearly lesser than the dimension of the blade. The tie rod, the upper blade part and the lower blade part are connected together partly by a form closure.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinentechnik. Sie betrifft eine Laufschaufel für eine Gasturbine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbine technology. It relates to a blade for a gas turbine according to the preamble of claim 1.

STAND DER TECHNIKSTATE OF THE ART

Ungekühlte, hohle Turbinenlaufschaufeln werden üblicherweise aus einem Material gegossen. Es ist aber auch bekannt ( US-B1-6,331,217 ), grosse Laufschaufeln einer Gasturbine aus mehreren separat gegossenen Schaufelteilen durch Liquid Phase Bonding zusammenzufügen. Hierbei wird entweder das Schaufelblatt in Schaufellängsrichtung geteilt (Fig. 3 der US-B1-6,331,217 ) oder das gesamte Schaufelblatt wird getrennt von der Plattform und dem Schaufelfuss hergestellt (Fig. 6 der US-B1-6,331,217 ). Dies führt gerade bei grossen Schaufeln dazu, dass trotz der Unterteilung grosse Gussstücke für das Schaufelblatt hergestellt und formschlüssig miteinander verbunden werden müssen.Uncooled hollow turbine blades are usually cast from a material. But it is also known ( US B1-6,331,217 ), large rotor blades of a gas turbine from several separately cast blade parts by liquid phase bonding together. Here, either the blade is divided in the blade longitudinal direction (Fig. 3 of the US B1-6,331,217 ) or the entire airfoil is separated from the platform and the blade root manufactured (Fig. 6 of the US B1-6,331,217 ). This leads, especially in the case of large blades, to the fact that, despite the subdivision, large castings for the airfoil have to be produced and positively connected to one another.

Dasselbe gilt auch für die in der US-A1-2006/0120869 beschriebene Laufschaufel, die im Inneren der Schaufel einen in Längsrichtung durchgehenden Holm (12) aufweist, der im Bereich des Schaufelblattes aussen von einer aerodynamisch wirksamen Hülle (48) umschlossen ist. Eine ähnliches Konzept, bei dem die äussere Hülle mit einer Druckspannung vorgespannt wird, ist aus der US-A-4,473,336 bekannt. Schliesslich ist es aus der US-A-4,563,128 eine vergleichbare Konfiguration bekannt, bei der die äussere Hülle des Schaufelblattes aus einer Keramik besteht.The same applies to the in the US-A1-2006 / 0120869 described blade which has a longitudinally continuous spar inside the blade (12), which is surrounded in the region of the blade outside of an aerodynamically effective sheath (48). A similar concept, in which the outer shell is biased with a compressive stress, is from the US-A-4,473,336 known. Finally, it is from the US-A-4,563,128 a comparable configuration is known in which the outer shell of the airfoil is made of a ceramic.

Mit der Steigerung der Wirkungsgrade und Effizienz von modernen Gasturbinenanlagen werden die Dimensionen der einzelnen Komponenten und somit der Laufschaufeln ebenfalls vergrössert. Dadurch können unter anderem erhebliche gewichtsbedingte Probleme im Einsatz sowie fertigungstechnische Schwierigkeiten beim Giessen grosser Bauteile auftreten.With the increase in efficiency and efficiency of modern gas turbine plants, the dimensions of the individual components and thus of the rotor blades are also increased. As a result, among other things, significant weight-related problems in use and manufacturing difficulties in casting large components can occur.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, eine Gasturbinen-Laufschaufel zu schaffen, die hinsichtlich ihres Gewichts optimiert ist, ohne dabei an Effizienz einzubüssen.It is therefore an object of the invention to provide a gas turbine blade, which is optimized in terms of its weight, without sacrificing efficiency.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wesentlich für die Erfindung ist, dass die Schaufel aus mehreren Einzelteilen zusammengesetzt ist, deren Material jeweils dem Einsatzzweck des betreffenden Einzelteils angepasst ist, und dass jedes der Einzelteile von den Abmessungen her deutlich kleiner ist als die zusammengesetzte Laufschaufel.The object is solved by the entirety of the features of claim 1. Essential to the invention is that the blade is composed of several individual parts, the material of each of which is adapted to the intended use of the item in question, and that each of the individual parts is significantly smaller in size than the composite blade.

Die Erfindung verfolgt damit den Gedanken, eine Gasturbinen-Laufschaufel aus mehreren, vergleichsweise kleinen Einzelteilen verschiedener Materialien zu bauen, deren Materialeigenschaften an die jeweiligen lokalen Belastungen angepasst werden können. Auf Grund der so möglichen Variation der Materialien offenbart sich ein deutliches Optimierungspotential hinsichtlich des Eigengewichtes, der Herstellbarkeit und Herstellkosten der Laufschaufel.The invention thus pursues the idea to build a gas turbine blade from several, relatively small items of different materials whose material properties can be adapted to the respective local loads. Due to the possible variation of the materials, a clear optimization potential with respect to the own weight, the manufacturability and the manufacturing costs of the blade is revealed.

Die Erfindungsidee ist es also, die Gasturbinen-Laufschaufel aus mehreren Einzelteilen zu bauen, um somit gezielt Materialeigenschaften ausnutzen zu können und eventuelle grössenbedingte Herstellungsprobleme zu vermeiden. Eine klare Funktionstrennung der verschiedenen Teile soll erreicht werden. Dies geht mit den bekannten und genutzten Materialien mit einer relativ hohen Dichte einher. Dieser Zusammenhang ist mit der so genannten spezifischen Dichte darstellbar. Dies ist die Relation zwischen Materialfestigkeitswerten und deren Dichte.The idea of the invention is thus to build the gas turbine blade from several individual parts in order to be able to exploit material properties in a targeted way and to avoid any size-related manufacturing problems. A clear separation of functions between the different parts is to be achieved. This is associated with the known and used materials with a relatively high density. This relationship can be represented by the so-called specific density. This is the relation between material strength values and their density.

Dafür können auch Materialien verwendet werden, die eine geringere Dichte aufweisen. Insgesamt können kleinere Bauteile fertigungstechnisch effizienter hergestellt werden, als ein grosses Bauteil. Durch den Zusammenbau der Schaufel aus materialoptimierten Einzelteilen können folgende Vorteile erzielt werden:

  • Kostenreduktion
    • ○ Flexiblere Materialauswahl durch Fertigung mehrerer Einzelteile
    • ○ Effizientere Fertigung (höhere Ausbeute) durch Grössenreduktion der Gussteile
  • Optimierte Materialauswahl
    • ○ Korrosionsbeständige Hülle (u.U. aus Blechmaterial)
    • ○ Zuganker mit hoher spezifischer Festigkeit
  • Gewichtsreduktion durch teilweise Verwendung von Werkstoffen mit niedriger Dichte
  • Der Zuganker kann tiefer in den Rotorkörper greifen (> 3 Zacken am Schaufelfuss oder "long shank")
For this purpose, it is also possible to use materials which have a lower density. Overall, smaller components can be made more efficient in terms of production technology than a large component. By assembling the bucket of material-optimized parts, the following advantages can be achieved:
  • cost reduction
    • ○ More flexible material selection through production of several individual parts
    • ○ More efficient production (higher yield) by reducing the size of castings
  • Optimized material selection
    • ○ Corrosion-resistant casing (possibly made of sheet metal material)
    • ○ Tie rod with high specific strength
  • Weight reduction through partial use of low density materials
  • The tie rod can reach deeper into the rotor body (> 3 points on the blade root or "long shank")

Eine Ausgestaltung der Laufschaufel nach der Erfindung ist dadurch gekennzeichnet, dass die Einzelteile zumindest teilweise durch Formschluss miteinander verbunden sind.An embodiment of the blade according to the invention is characterized in that the individual parts are at least partially connected by positive locking.

Eine andere Ausgestaltung der erfindungsgemässen Schaufel zeichnet sich dadurch aus, dass die Einzelteile der Laufschaufel ein unteres Schaufelteil und ein in Schaufellängsrichtung daran anschliessendes oberes Schaufelteil umfassen, wobei das Schaufelblatt in Schaufellängsrichtung auf das untere und obere Schaufelteil aufgeteilt ist, das untere Schaufelteil die Plattform und zumindest einen Teil des Schaufelfusses mit umfasst, und das obere Schaufelteil die Schaufelspitze mit umfasst. Durch ein solches geteiltes Schaufelblatt kann die Dimension der einzelnen Gussteile massgeblich reduziert werdenAnother embodiment of the blade according to the invention is characterized in that the individual parts of the blade comprise a lower blade part and an upper blade part adjoining thereto in the blade longitudinal direction, the blade blade being divided in the blade longitudinal direction onto the lower and upper blade part, the lower blade part the platform and at least includes a portion of the blade root, and the upper blade portion includes the blade tip with. By such a split airfoil, the dimension of the individual castings can be significantly reduced

Eine weitere Ausgestaltung ist dadurch gekennzeichnet, dass zum Aufnehmen der am oberen Schaufelteil angreifenden Fliehkräfte im Inneren der Laufschaufel ein sich in Schaufellängsrichtung erstreckender Zuganker angeordnet ist, dass der Zuganker mit seinem oberen Ende mit dem unteren Ende des oberen Schaufelteils in Eingriff steht, und dass der Zuganker mit seinem unteren Ende die Zugkräfte in den Schaufelfuss einleitet. Insbesondere weist der Zuganker einen Fussabschnitt auf, der einen Teil des Schaufelfusses bildet und mit dem der Zuganker das untere Schaufelteil hintergreift.A further embodiment is characterized in that, for receiving the centrifugal forces acting on the upper blade part, a tie rod extending in the longitudinal direction of the blade is arranged in the blade longitudinal direction, that the tie rod engages with its upper end with the lower end of the upper blade part, and that Tie rod with its lower end introduces the tensile forces in the blade root. In particular, the tie rod on a foot portion, which forms part of the blade root and with which the tie rod engages behind the lower blade part.

Gemäss einer anderen Ausgestaltung ist am oberen Schaufelteil ein nach innen abgewinkeltes erstes Winkelelement angeordnet, wobei der Zuganker mit dem oberen Schaufelteil dadurch in Eingriff steht, dass er mit einem zweiten Winkelelement hinter das erste Winkelelement greift.According to another embodiment, an inwardly angled first angle element is arranged on the upper blade part, wherein the tie rod is in engagement with the upper blade part in that it engages behind the first angle element with a second angle element.

Der Zuganker kann aber auch aus mehreren in Schaufellängsrichtung parallel angeordneten Teilankern bestehen, wobei die Teilanker quer zur Schaufellängsrichtung voneinander beabstandet sind, und wobei der Abstand der Teilanker durch nachträglich einsetzbare Abstandshalter festgelegt wird.However, the tie rod can also consist of several in the blade longitudinal direction arranged in parallel partial anchors, wherein the partial anchors are spaced transversely to the blade longitudinal direction from each other, and wherein the distance of the partial anchors is determined by subsequently usable spacers.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen

Fig. 1
einen Längschnitt durch eine Laufschaufel gemäss einem Ausführungsbeispiel der Erfindung; und
Fig. 2
den Längsschnitt durch eine zu Fig. 1 alternative Zugankeranordnung.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
a longitudinal section through a blade according to an embodiment of the invention; and
Fig. 2
the longitudinal section through one Fig. 1 alternative tie rod assembly.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

Fig. 1 zeigt einen Längsschnitt durch eine (gebaute) Laufschaufel gemäss einem Ausführungsbeispiel der Erfindung. Die Laufschaufel 10 der Fig. 1 besteht aus drei einzelnen Komponenten, nämlich einem oberen Schaufelteil 18, einem unteren Schaufelteil 17 und einem Zuganker 16. Die Laufschaufel 10 hat ein aerodynamisch wirksames Schaufelblatt 11, das sich in Schaufellängsrichtung zwischen einer Schaufelspitze 15 und einer Plattform 12 erstreckt. Das Schaufelblatt 11 ist in Längsrichtung aufgeteilt auf das obere Schaufelteil 18 und auf das untere Schaufelteil 17. Am oberen Ende des oberen Schaufelteils 18 ist ein Deckbandsegment 18b ausgebildet. Am unteren Ende des oberen Schaufelteils 18 ist ein nach innen vorspringendes erstes Winkelelement 18a angeformt, hinter das der innen liegende Zuganker 16 mit einem an seinem oberen Ende angebrachten zweiten Winkelelement 16a greift und damit das obere Schaufelteil 18 gegen die auftretenden Fliehkräfte hält. Das obere Schaufelteil 18 ist so nur auf Zug belastet. Fig. 1 shows a longitudinal section through a (built) blade according to an embodiment of the invention. The blade 10 of the Fig. 1 consists of three separate components, namely an upper blade portion 18, a lower blade portion 17 and a tie rod 16. The blade 10 has an aerodynamically effective airfoil 11 extending in the blade longitudinal direction between a blade tip 15 and a platform 12. The airfoil 11 is divided longitudinally onto the upper blade part 18 and onto the lower blade part 17. At the upper end of the upper blade part 18, a shroud segment 18b is formed. At the lower end of the upper blade portion 18, an inwardly projecting first angle member 18a is formed, behind which engages the inner tie rod 16 with a mounted at its upper end second angle member 16a and thus holds the upper blade member 18 against the centrifugal forces occurring. The upper blade part 18 is thus loaded only on train.

Das untere Schaufelteil 17 umfasst den unteren Teil des Schaufelblattes 11, die Plattform 12 einen Schaft 13 und einen Teil eines Schaufelfusses 14, der im gezeigten Beispiel ein tannenbaumartiges Randprofil (mit 3 Zacken) aufweist. Ein anderer Teil des Schaufelfusses 14 wird von einem Fussabschnitt 16b gebildet, mit dem der Zuganker 16 das untere Schaufelteil 17 hintergreift.The lower blade part 17 comprises the lower part of the blade 11, the platform 12 a shaft 13 and a part of a blade root 14, which in the shown example, a fir tree-like edge profile (with 3 teeth) has. Another part of the blade root 14 is formed by a foot section 16b, with which the tie rod 16 engages behind the lower blade part 17.

In der in Fig. 1 gezeigten Konfiguration müssen das obere Schaufelteil 18 und das untere Schaufelteil 17 eine deutlich höhere Temperatur- und Kriechbeständigkeit aufweisen als der innen liegende Zuganker 16. Entsprechend unterschiedlich können die verwendeten Materialien der Teile 17, 18 einerseits und des Teils 16 andererseits sein. Innerhalb der Schaufelhöhe variieren die Temperaturen jedoch so stark, dass sich auch für die beiden Schaufelteile 17 und 18 der Einsatz unterschiedlich angepasster Werkstoffe empfiehlt. Selbst der Zuganker 16 kann - wie in Fig. 1 durch die unterschiedliche Schraffur angedeutet ist - bei Bedarf in der Längsrichtung aus unterschiedlichen Werkstoffen bestehen. Er kann aber auch durchgehend aus einem Werkstoff gefertigt sein.In the in Fig. 1 As shown, the upper blade portion 18 and the lower blade portion 17 must have a significantly higher temperature and creep resistance than the inner tie rod 16. The materials used for the parts 17, 18 on the one hand and the part 16 on the other hand can be correspondingly different. Within the blade height, however, the temperatures vary so strongly that the use of differently adapted materials is also recommended for the two blade parts 17 and 18. Even the tie rod 16 can - as in Fig. 1 indicated by the different hatching - if necessary in the longitudinal direction consist of different materials. But it can also be made of a material throughout.

Der Zusammenbau einer erfindungsgemässen Laufschaufel kann auf unterschiedliche Weise erfolgen: Wenn der Zuganker 16 in Längsrichtung nicht in einer Mittelebene 19 geteilt ist, kann er beispielsweise um 90° verdreht von unten in das Schaufelinnere eingeführt und dann durch eine Drehung um 90° zurück in Eingriff mit dem Winkelelement 18a am unteren Ende des oberen Schaufelteils 18 gebracht werden.The assembly of an inventive blade can be done in different ways: If the tie rod 16 is not divided in the longitudinal direction in a median plane 19, he can, for example, 90 ° twisted introduced from below into the blade interior and then by a rotation of 90 ° back into engagement with the angle member 18a at the lower end of the upper blade portion 18 are brought.

Es ist aber auch denkbar, gemäss Fig. 2 bei einer Laufschaufel 20 einen in Längsrichtung geteilten Zuganker 21 vorzusehen, der zwei spiegelsymmetrisch zueinander ausgebildete Teilanker 22 und 23 umfasst, die im eingebauten Zustand in Querrichtung voneinander beabstandet sind und durch entsprechende Abstandshalter 24 und 25 auf Abstand gehalten werden. Beim Zusammenbau der Laufschaufel 20 werden die beiden Teilanker 22, 23 zunächst ohne Abstandshalter 24, 25 und ohne Querabstand in das Schaufelinnere eingeschoben, bis die Teilanker 22, 23 mit ihren oberen Winkelelementen 22b, 23b hinter die Winkelelemente 18a des Schaufelblattes greifen können. Dann wird der obere (runde) Abstandshalter 25 von unten zwischen den beiden Teilankern nach oben geschoben, bis er die in Fig. 2 gezeigte Position erreicht hat und die beiden Teilanker 22, 23 in der eingehakten Stellung fixiert. Schliesslich wird am unteren Ende der untere Abstandshalter 24 zwischen die Teilanker 22, 23 eingeführt, so dass diese sich mit unteren Winkelelementen von innen an einem Absatz am Schaufelfuss 14 abstützen.But it is also conceivable, according to Fig. 2 in the case of a rotor blade 20, a tie rod 21 divided in the longitudinal direction is provided, which comprises two partial anchors 22 and 23 which are mirror-symmetrical to one another, which are spaced apart transversely in the installed state and are kept at a distance by corresponding spacers 24 and 25. When assembling the rotor blade 20, the two partial anchors 22, 23 are first inserted without spacers 24, 25 and without transverse spacing in the blade interior until the partial anchors 22, 23 can engage with their upper angle elements 22b, 23b behind the angle elements 18a of the airfoil. Then, the upper (round) spacer 25 from below between the two partial anchors pushed up until he was in Fig. 2 has reached the position shown and the two partial anchors 22, 23 fixed in the hooked position. Finally, at the lower end, the lower spacer 24 is inserted between the partial anchors 22, 23 so that they are supported with lower angle elements from the inside on a shoulder on the blade root 14.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

10,2010.20
Laufschaufel (Gasturbine)Blade (gas turbine)
1111
Schaufelblattairfoil
1212
Plattformplatform
1313
Schaftshaft
1414
Schaufelfussblade root
1515
Schaufelspitzeblade tip
16,2116.21
Zugankertie rods
16a16a
Winkelelementangle element
16b16b
Fussabschnittfoot section
1717
unterer Schaufelteillower blade part
1818
oberer Schaufelteilupper blade part
18a18a
Winkelelementangle element
18b18b
DeckbandsegmentShroud segment
1919
Mittelebenemidplane
22,2322.23
Teilankerpart anchor
22a,23a22a, 23a
Winkelelement (unten)Angle element (below)
22b,23b22b, 23b
Winkelelement (oben)Angle element (top)
24,2524.25
Abstandshalterspacer

Claims (10)

Laufschaufel (10, 20) für eine Gasturbine, welche Laufschaufel (10, 20) ein Schaufelblatt (11), eine Schaufelspitze (15), einen Schaufelfuss (14) und eine zwischen Schaufelspitze (15) und Schaufelfuss (14) ausgebildete Plattform (12) umfasst und aus mehreren Einzelteilen (16, 17, 18) zusammengesetzt ist, deren Material jeweils dem Einsatzzweck des betreffenden Einzelteils angepasst ist, dadurch gekennzeichnet, dass jedes der Einzelteile (16, 17, 18) von den Abmessungen her deutlich kleiner ist als die zusammengesetzte Laufschaufel (10, 20).Blade (10, 20) for a gas turbine, which blade (10, 20) an airfoil (11), a blade tip (15), a blade root (14) and between the blade tip (15) and blade root (14) formed platform (12 ) and is composed of a plurality of individual parts (16, 17, 18), the material of which is in each case adapted to the intended use of the item in question, characterized in that each of the individual parts (16, 17, 18) is considerably smaller in size than the one composite blade (10, 20). Laufschaufel nach Anspruch 1, dadurch gekennzeichnet, dass die Einzelteile (16, 17, 18) zumindest teilweise durch Formschluss miteinander verbunden sind.Blade according to claim 1, characterized in that the individual parts (16, 17, 18) are at least partially connected to one another by positive locking. Laufschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Einzelteile (16, 17, 18) der Laufschaufel (10, 20) ein unteres Schaufelteil (17) und ein in Schaufellängsrichtung daran anschliessendes oberes Schaufelteil (18) umfassen, wobei das Schaufelblatt (11) in Schaufellängsrichtung auf das untere und obere Schaufelteil (17 bzw. 18) aufgeteilt ist.Blade according to Claim 1 or 2, characterized in that the individual parts (16, 17, 18) of the moving blade (10, 20) comprise a lower blade part (17) and an upper blade part (18) adjoining it in the longitudinal direction of the blade, the blade being ( 11) is divided in the blade longitudinal direction on the lower and upper blade portion (17 and 18). Laufschaufel nach Anspruch 3, dadurch gekennzeichnet, dass das untere Schaufelteil (17) die Plattform (12) und zumindest einen Teil des Schaufelfusses mit umfasst, und dass das obere Schaufelteil (18) die Schaufelspitze (15) mit umfasst.A blade according to claim 3, characterized in that the lower blade part (17) comprises the platform (12) and at least part of the blade root, and in that the upper blade part (18) includes the blade tip (15). Laufschaufel nach Anspruch 3 oder 4, dadurch gekennzeichnet, dass zum Aufnehmen der am oberen Schaufelteil (18) angreifenden Fliehkräfte im Inneren der Laufschaufel (10, 20) ein sich in Schaufellängsrichtung erstreckender Zuganker (16, 21) angeordnet ist, dass der Zuganker (16, 21) mit seinem oberen Ende mit dem unteren Ende des oberen Schaufelteils (18) in Eingriff steht, und dass der Zuganker (16, 21) mit seinem unteren Ende die Zugkräfte in den Schaufelfuss (14) einleitet.A moving blade according to claim 3 or 4, characterized in that for receiving the centrifugal forces acting on the upper blade part (18) inside the moving blade (10, 20) a tie rod (16, 21) extending in the blade longitudinal direction is arranged, that the tie rod (16 , 21) with its upper end with the lower end of the upper blade part (18) is engaged, and that the tie rod (16, 21) with its lower end initiates the tensile forces in the blade root (14). Laufschaufel nach Anspruch 5, dadurch gekennzeichnet, dass der Zuganker (16) einen Fussabschnitt (16b) aufweist, der einen Teil des Schaufelfusses (14) bildet.Blade according to claim 5, characterized in that the tie rod (16) has a foot portion (16b) forming part of the blade root (14). Laufschaufel nach Anspruch 6, dadurch gekennzeichnet, dass der Zuganker (16) mit dem Fussabschnitt (16b) das untere Schaufelteil (17) hintergreift.Blade according to claim 6, characterized in that the tie rod (16) engages behind the lower blade part (17) with the foot section (16b). Laufschaufel nach einem der Ansprüche 5 bis 7, dadurch gekennzeichnet, dass am oberen Schaufelteil (18) ein nach innen abgewinkeltes erstes Winkelelement (18a) angeordnet ist, und dass der Zuganker (14, 21) mit dem oberen Schaufelteil (18) dadurch in Eingriff steht, dass er mit einem zweiten Winkelelement (16a, 22b, 23b) hinter das erste Winkelelement (18a) greift.A blade according to any one of claims 5 to 7, characterized in that an inwardly angled first angled member (18a) is disposed on the upper blade member (18) and that the tie rod (14, 21) engages the upper blade member (18) therethrough is that he with a second angle element (16a, 22b, 23b) behind the first angle element (18a) engages. Laufschaufel nach Anspruch 5, dadurch gekennzeichnet, dass der Zuganker (21) aus mehreren in Schaufellängsrichtung parallel angeordneten Teilankern (22, 23) besteht.Blade according to claim 5, characterized in that the tie rod (21) consists of a plurality of blade anchors arranged in parallel in the longitudinal direction (22, 23). Laufschaufel nach Anspruch 9, dadurch gekennzeichnet, dass die Teilanker (22, 23) quer zur Schaufellängsrichtung voneinander beabstandet sind, und dass der Abstand der Teilanker (22, 23) durch nachträglich einsetzbare Abstandshalter (24, 25) festgelegt wird.A blade according to claim 9, characterized in that the partial anchors (22, 23) are spaced apart from each other transversely to the blade longitudinal direction, and that the distance of the partial anchors (22, 23) by subsequently usable spacers (24, 25) is fixed.
EP09178286.2A 2008-12-12 2009-12-08 Gas turbine rotor blade Active EP2196624B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01957/08A CH700071A1 (en) 2008-12-12 2008-12-12 Moving blade for a gas turbine.

Publications (2)

Publication Number Publication Date
EP2196624A1 true EP2196624A1 (en) 2010-06-16
EP2196624B1 EP2196624B1 (en) 2016-10-05

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Country Status (4)

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US (1) US8911213B2 (en)
EP (1) EP2196624B1 (en)
JP (1) JP5553589B2 (en)
CH (1) CH700071A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2781691A1 (en) 2013-03-19 2014-09-24 Alstom Technology Ltd Method for reconditioning a hot gas path part of a gas turbine
EP3029268A1 (en) * 2014-12-01 2016-06-08 Siemens Aktiengesellschaft Turbine rotor blade

Families Citing this family (6)

* Cited by examiner, † Cited by third party
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US8398374B2 (en) * 2010-01-27 2013-03-19 General Electric Company Method and apparatus for a segmented turbine bucket assembly
US8967974B2 (en) * 2012-01-03 2015-03-03 General Electric Company Composite airfoil assembly
RU2656052C1 (en) * 2017-04-04 2018-05-30 Акционерное общество "Климов" Working blade of the gas turbine
US11542820B2 (en) 2017-12-06 2023-01-03 General Electric Company Turbomachinery blade and method of fabricating
DE102018210262A1 (en) * 2018-06-25 2020-01-02 MTU Aero Engines AG Turbomachinery blade arrangement
RU189517U1 (en) * 2018-12-24 2019-05-24 Федеральное государственное бюджетное образовательное учреждение высшего образования "Санкт-Петербургский государственный архитектурно-строительный университет" WORK FELT GAS TURBINE

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7905608A (en) 1978-08-09 1980-02-12 Mtu Muenchen Gmbh GAS TURBINE SHOVEL.
FR2463849A1 (en) 1979-08-23 1981-02-27 Onera (Off Nat Aerospatiale) Blade for gas turbine rotor - has outer ceramic liner fitted over metal core and held by enlarged head and pin into rotor root fixing
US4473336A (en) 1981-09-26 1984-09-25 Rolls-Royce Limited Turbine blades
US4563128A (en) 1983-02-26 1986-01-07 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Ceramic turbine blade having a metal support core
US4786234A (en) 1982-06-21 1988-11-22 Teledyne Industries, Inc. Turbine airfoil
US6331217B1 (en) 1997-10-27 2001-12-18 Siemens Westinghouse Power Corporation Turbine blades made from multiple single crystal cast superalloy segments
US20060120869A1 (en) 2003-03-12 2006-06-08 Wilson Jack W Cooled turbine spar shell blade construction
EP1905954A1 (en) 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Turbine blade

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2538029A1 (en) * 1982-12-15 1984-06-22 Onera (Off Nat Aerospatiale) IMPROVEMENTS TO CERAMIC, ROTATING OR FIXED BLADES OF TURBOMACHINES
DE3521782A1 (en) * 1985-06-19 1987-01-02 Mtu Muenchen Gmbh HYBRID SHOVEL MADE OF METAL AND CERAMIC
JPH03213601A (en) * 1990-01-19 1991-09-19 Toshiba Corp Builtup turbine bucket
US5489194A (en) * 1990-09-14 1996-02-06 Hitachi, Ltd. Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade
DE502006006333D1 (en) * 2006-05-31 2010-04-15 Siemens Ag turbine blade

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7905608A (en) 1978-08-09 1980-02-12 Mtu Muenchen Gmbh GAS TURBINE SHOVEL.
DE2834843A1 (en) 1978-08-09 1980-06-26 Motoren Turbinen Union COMPOSED CERAMIC GAS TURBINE BLADE
FR2463849A1 (en) 1979-08-23 1981-02-27 Onera (Off Nat Aerospatiale) Blade for gas turbine rotor - has outer ceramic liner fitted over metal core and held by enlarged head and pin into rotor root fixing
US4473336A (en) 1981-09-26 1984-09-25 Rolls-Royce Limited Turbine blades
US4786234A (en) 1982-06-21 1988-11-22 Teledyne Industries, Inc. Turbine airfoil
US4563128A (en) 1983-02-26 1986-01-07 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Ceramic turbine blade having a metal support core
US6331217B1 (en) 1997-10-27 2001-12-18 Siemens Westinghouse Power Corporation Turbine blades made from multiple single crystal cast superalloy segments
US20060120869A1 (en) 2003-03-12 2006-06-08 Wilson Jack W Cooled turbine spar shell blade construction
EP1905954A1 (en) 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Turbine blade

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2781691A1 (en) 2013-03-19 2014-09-24 Alstom Technology Ltd Method for reconditioning a hot gas path part of a gas turbine
US9926785B2 (en) 2013-03-19 2018-03-27 Ansaldo Energia Ip Uk Limited Method for reconditioning a hot gas path part of a gas turbine
EP3029268A1 (en) * 2014-12-01 2016-06-08 Siemens Aktiengesellschaft Turbine rotor blade

Also Published As

Publication number Publication date
US20100150727A1 (en) 2010-06-17
EP2196624B1 (en) 2016-10-05
CH700071A1 (en) 2010-06-15
US8911213B2 (en) 2014-12-16
JP2010138907A (en) 2010-06-24
JP5553589B2 (en) 2014-07-16

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