EP2310634B1 - Rotating blade system for a row of rotating blades of a turbomachine - Google Patents

Rotating blade system for a row of rotating blades of a turbomachine Download PDF

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Publication number
EP2310634B1
EP2310634B1 EP09776055A EP09776055A EP2310634B1 EP 2310634 B1 EP2310634 B1 EP 2310634B1 EP 09776055 A EP09776055 A EP 09776055A EP 09776055 A EP09776055 A EP 09776055A EP 2310634 B1 EP2310634 B1 EP 2310634B1
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EP
European Patent Office
Prior art keywords
rotating
blade
blades
row
segments
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.)
Not-in-force
Application number
EP09776055A
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German (de)
French (fr)
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EP2310634A2 (en
Inventor
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2310634A2 publication Critical patent/EP2310634A2/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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • 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
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a blade system referred to in the preamble of claim 1. Art for a blade row of a turbomachine.
  • the invention further relates to a turbomachine specified in the preamble of claim 7 and a method for mounting a blade row for a turbomachine.
  • the blade system comprises two or more blade segments, of which each blade segment has at least two blades, which are arranged at least predominantly radially between a radially inner and a radially outer shroud and coupled to the Deckbändem with respect to a rotational axis of the blade row, at least the radially outer shrouds of Blade segments include mutually corresponding contact surfaces over which the blade segments abut each other.
  • the fan blade segments so-called clusters
  • the number of joints and gaps of the rotor blade system can be considerably reduced compared to blade systems made of individual rotor blades.
  • fewer attack surfaces provide for guided by the associated turbomachine gases, whereby the durability of such blade systems or blade rows can be increased.
  • the blade segments also form mechanically relatively stable units in the mounted state, whereby relative movements during operation and the associated wear are advantageously reduced.
  • a disadvantage of the known blade systems is the fact that the blade segments, unlike blade systems from individual blades no longer by torsion of the blades of a row of blades against each other can be tightened. As a result, the rotor clusters are mechanically decoupled from one another and are difficult to control in terms of vibration mechanics.
  • Object of the present invention is therefore to provide a blade system of the type mentioned, which has improved vibration mechanical properties.
  • An inventive blade system for a blade row of a turbomachine having improved vibration mechanical properties is provided in that radial equilibrium axes of adjacent blades of the at least two blade segments are each axially tilted at an angle to their respective base pitch, the angles having opposite signs relative to the ground tilt , In other words, it is provided that adjacent blades of the at least two blade segments are arranged starting from their respective base inclination tilted like a scissor.
  • the basic inclination which is also called “lean” is usually used during the operation of the associated turbomachine gas forces that generate corresponding bending moments on the blades, at least in certain operating areas of the turbomachine largely compensate.
  • the basic inclination, about which the equilibrium axes of the rotor blades are tilted, is in this case usually between 0 ° and 2 °, depending on the configuration of the turbomachine.
  • the equilibrium axis can run coaxially or axially parallel to a threading axis of the blade profiles depending on the geometries of the rotor blades.
  • the blades are cast in the inner shroud and / or in the outer shroud. This allows a cost-effective manner a mechanically stable and reliable connection of the blades to the relevant shroud.
  • the contact surfaces are designed as a mechanical latch.
  • the pressing forces achievable with the aid of the rotor blade system according to the invention can be distributed over a wide area, so that in contrast to the prior art, no elastic deformations occur, but the resulting forces in the area of the contact surfaces can be discontinued as contact forces.
  • This will be a mechanically particularly stable coupling of the at least two blade segments achieved, so that the blade system is not critical vibration mechanics.
  • an amount of the angle between 0.1 ° and 10 °, in particular between 0.1 ° and 5 °, and preferably between 0.1 ° and 2 °.
  • a turbomachine in particular a thermal gas turbine, with a blade row, which comprises a blade system of at least two blade segments, each of which blade segment at least two blades, with respect to a rotational axis of the blade row at least predominantly radially between a radially inner and a radially outer shroud and are coupled to the Deckbändem, wherein at least the radially outer shrouds of the two blade segments comprise mutually corresponding application areas, via which the blade segments are coupled together.
  • radial equilibrium axes of adjacent blades of the at least two blade segments are each tilted axially at an angle to their respective base pitch, wherein the angles have opposite signs with respect to the base pitch.
  • the blade row is arranged in a turbine region, in particular a low-pressure turbine region of the turbomachine.
  • a turbine region in particular a low-pressure turbine region of the turbomachine.
  • Another aspect of the invention relates to a method for mounting a blade row for a turbomachine, in particular for a thermal gas turbine, wherein at least two blade segments of a blade system according to one of the preceding embodiments provided and those blades of the at least two blade segments, each axially at an angle ( ⁇ a , ⁇ b ) are tilted relative to their respective base pitch, are arranged adjacent to each other, wherein the angles with respect to the base pitch of the blades have opposite signs.
  • This allows a mechanically stable and vibration-mechanically uncritical assembly of the blade row, whereby a significant reduction in manufacturing costs is given at the same time increased durability.
  • Another advantage is that the bracing contact forces between the blade segments only occur speed-dependent during operation of the turbomachine, so that the blade segments are particularly easy to assemble or disassemble in the state.
  • Further advantages arise when the connection areas of the blade segments are coupled together without deformation. In contrast to the prior art, in which due to the torsion of the blade profiles over the shrouds, the contact force must be generated at the connection areas by elastic deformation and also in the state, can with the aid of the inventive method and the center of gravity displacement of the blades during operation, a bias and thus a vibration mechanical uncritical coupling of the at least two blade segments are achieved without deformation.
  • the single figure shows a schematic perspective view of two coupled blade segments of a blade system for a blade row for arrangement in a low-pressure turbine section of a thermal gas turbine.
  • FIGURE is a schematic perspective view of two coupled blade segments 10a, 10b of a blade row blade system formed from a plurality of blade segments 10 for placement in a low pressure turbine section of a thermal gas turbine (not shown).
  • Each blade segment 10a, 10b comprises in the present embodiment in each case four blades 12 (Airfoils), which are arranged with respect to a rotation axis of the blade row mounted in the turbomachine predominantly radially between a radially inner shroud 14a, 14a 'and a radially outer shroud 14b, 14b' and the shrouds 14a, 14b and 14a ', 14b' are coupled.
  • Airfoils Airfoils
  • the radially outer shrouds 14b, 14b 'of the two blade segments 10a, 10b comprise mutually correspondingly formed contact surfaces 16a, 16b, with a Z-shaped profile (so-called Z-shroud).
  • the contact surfaces 16a, 16b which are arranged at an angle to one another are designed as mechanical latches.
  • the blades 12 are respectively cast into the inner and outer shrouds 14a, 14a ', 14b, 14b' to achieve a mechanically stable, lightweight connection.
  • As the several rotor blades 12 comprehensive blade segments 10 a, 10 b (so-called.
  • a adjacent blades 12 of at least two blade segments 10a, 10b are each axially by an angle ⁇ a, ⁇ b compared to their respective baseline slope (so-called. Lean) are arranged tilted.
  • the angles ⁇ a, ⁇ b are selected such that adjacent rotor blades 12 with respect to its respective base to tilt mutually opposite, but in amount equal angles ⁇ a and ⁇ b tilted like scissors.
  • a blade 12 is tilted rearward relative to the lean relative to a rotational axis of the blade system and the adjacent blade 12 is tilted forward accordingly.
  • a center of gravity displacement of the blades concerned 12 is achieved, which due to the centrifugal forces during operation of the associated turbomachine speed-dependent righting forces arise that settle according to the arrows 18a, 18b in the contact surfaces 16a, 16b as contact forces.
  • the blade segments 10a, 10b are mechanically coupled during operation, so that the entire blade system or the blade row is vibration-mechanically uncritical.
  • the contact forces increase with the speed.
  • angles ⁇ a , ⁇ b are in the illustrated embodiment about ⁇ 1 °. In principle, however, deviating angles ⁇ or, in terms of magnitude, different angles ⁇ a , ⁇ b can be selected. It is preferably contemplated that the marginal blades 12 of each blade segment 10 are also tilted about opposing angles ⁇ with respect to their respective base pitch. Alternatively or additionally, it may also be provided that inner rotor blades 12 of the respective blade segments 10 are tilted by an angle ⁇ relative to their respective base inclination.

Abstract

The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (αa, αb) relative to their respective base inclination, wherein the angles (αa, αb) in regard to the base inclination feature opposite signs. The invention concerns furthermore a continuous-flow machine as well as a method for the mounting of a moving blade sequence for a continuous-flow machine.

Description

Die Erfindung betrifft ein Laufschaufelsystem der im Oberbegriff des Patentanspruchs 1 genannten Art für eine Laufschaufelreihe einer Strömungsmaschine. Die Erfindung betrifft weiterhin eine Strömungsmaschine der im Oberbegriff des Patentanspruchs 7 angegebenen Art sowie ein Verfahren zum Montieren einer Laufschaufelreihe für eine Strömungsmaschine.The invention relates to a blade system referred to in the preamble of claim 1. Art for a blade row of a turbomachine. The invention further relates to a turbomachine specified in the preamble of claim 7 and a method for mounting a blade row for a turbomachine.

Ein derartiges Laufschaufelsystem für eine Laufschaufelreihe einer Strömungsmaschine ist bereits aus dem Dokument EP 1447 525 A1 bekannt. Das Laufschaufelsystem umfasst dabei zwei oder mehr Laufschaufelsegmente, von welchen jedes Laufschaufelsegment mindestens zwei Laufschaufeln aufweist, die bezüglich einer Drehachse der Laufschaufelreihe zumindest überwiegend radial zwischen einem radial inneren und einem radial äußeren Deckband angeordnet und mit den Deckbändem gekoppelt sind, Zumindest die radial äußeren Deckbänder der Laufschaufelsegmente umfassen miteinander korrespondierende Kontaktflächen, über welche die Laufschaufelsegmente aneinander anliegen. Mit Hilfe der Lanfschaufelsegmente (sog. Cluster) können im Vergleich zu Laufschaufelsystemen aus einzelnen Laufschaufeln die Anzahl der Fugen und Spalte des Laufschaufelsystems erheblich reduziert werden. Zudem bieten sich weniger Angriffsflächen für durch die zugeordnete Strömungsmaschine geführte Gase, wodurch die Haltbarkeit derartiger Laufschaufelsysteme beziehungsweise Laufschaufelreihen gesteigert werden kann. Die Laufschaufelsegmente bilden darüber hinaus im montierten Zustand mechanisch vergleichsweise stabile Einheiten, wodurch Relativbewegungen während des Betriebs und der damit verbundene Verschleiß vorteilhaft reduziert werden.Such a blade system for a blade row of a turbomachine is already out of the document EP 1447 525 A1 known. The blade system comprises two or more blade segments, of which each blade segment has at least two blades, which are arranged at least predominantly radially between a radially inner and a radially outer shroud and coupled to the Deckbändem with respect to a rotational axis of the blade row, at least the radially outer shrouds of Blade segments include mutually corresponding contact surfaces over which the blade segments abut each other. With the help of the fan blade segments (so-called clusters), the number of joints and gaps of the rotor blade system can be considerably reduced compared to blade systems made of individual rotor blades. In addition, fewer attack surfaces provide for guided by the associated turbomachine gases, whereby the durability of such blade systems or blade rows can be increased. The blade segments also form mechanically relatively stable units in the mounted state, whereby relative movements during operation and the associated wear are advantageously reduced.

Als nachteilig an dem bekannten Laufschaufelsystemen ist jedoch der Umstand anzusehen, dass die Laufschaufelsegmente im Unterschied zu Laufschaufelsystemen aus einzelnen Laufschaufeln nicht mehr durch Torsion der Laufschaufeln einer Laufschaufelreihe gegeneinander verspannt werden können. Dadurch sind die Laufschaufclsogmentc mechanisch zueinander entkoppelt und schwingungsmechanisch nur schwer beherrschbar.A disadvantage of the known blade systems, however, is the fact that the blade segments, unlike blade systems from individual blades no longer by torsion of the blades of a row of blades against each other can be tightened. As a result, the rotor clusters are mechanically decoupled from one another and are difficult to control in terms of vibration mechanics.

Aus dem Stand der Technik ist es ebenfalls bekannt, einzelne Turbinen-Laufschaufeln gegenüber der Radialrichtung zu verkippen, um unter Fliehkrafteinfluss durch Schaufelverformung die Reibungs- bzw. Dämpfungsverhältnisse im Bereich der sich berührenden Deckbandsegnente zu optimieren. Dabei können benachbarte Laufschaufeln gleich- oder gegensinnig verkippt sein. Siehe hierzu die Dokumente WO2005/026501 A1 und GB 2 215 407 A .It is also known from the prior art to tilt individual turbine blades with respect to the radial direction in order to optimize the friction or damping conditions in the region of the contacting shroud segments under the influence of centrifugal force by blade deformation. In this case, adjacent blades can be tilted in the same direction or in opposite directions. See the documents WO2005 / 026501 A1 and GB 2 215 407 A ,

Aufgabe der vorliegenden Erfindung ist es daher, ein Laufschaufelsystem der eingangs genannten Art zu schaffen, welches verbesserte schwingungsmechanische Eigenschaften aufweist.Object of the present invention is therefore to provide a blade system of the type mentioned, which has improved vibration mechanical properties.

Die Aufgabe wird erfindungsgemäß durch ein Laufschaufelsystem mit den Merkmalen des Patentanspruchs 1, eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 7 sowie durch ein Verfahren gemäß Patentanspruch 9 gelöst. Vorteilhafte Ausgestaltungen mit zweckmäßigen Weiterbildungen der Erfindung sind in den jeweiligen Unteransprüchen angegeben, wobei vorteilhafte Ausgestaltungen des Laufschaufelsystems beziehungsweise der Strömungsmaschine - soweit anwendbar-als vorteilhafte Ausgestaltungen des Verfahrens und umgekehrt anzusehen sind.The object is achieved by a blade system with the features of claim 1, a turbomachine with the features of claim 7 and by a method according to claim 9. Advantageous embodiments with expedient developments of the invention are specified in the respective subclaims, wherein advantageous embodiments of the blade system or the turbomachine - if applicable-are to be regarded as advantageous embodiments of the method and vice versa.

Ein erfindungsgemaßes Laufschaufelsystem für eine Laufschaufelreihe einer Strömungsmaschine, welches verbesserte schwingungsmechanische Eigenschaften aufweist, ist dadurch geschaffen, dass radiale Gleichgewichtsachsen benachbarter Laufschaufeln der wenigstens zwei Laufschaufelsegmente jeweils axial um einen Winkel gegenüber ihrer jeweiligen Grundneigung verkippt angeordnet sind, wobei die Winkel bezüglich der Gnmdneigung entgegengesetzte Vorzeichen aufweisen. Mit anderen Worten ist vorgesehen, dass benachbarte Laufschaufeln der wenigstens zwei Laufschaufelsegmente ausgehend von ihrer jeweiligen Grundneigung scherenartig verkippt angeordnet sind. Die Grundneigung, die auch als "Lean" bezeichnet wird, dient üblicherweise dazu, die während des Betriebs der zugeordneten Strömungsmaschine auftretenden Gaskräfte, die entsprechende Biegemomente an den Laufschaufeln erzeugen, zumindest in bestimmten Betriebsbereichen der Strömungsmaschine weitgehend auszugleichen. Die Grundneigung, um welche die Gleichgewichtsachsen der Laufschaufeln verkippt angeordnet sind, beträgt dabei in Abhängigkeit der Ausgestaltung der Strömungsmaschine üblicherweise zwischen 0° und 2°. Dabei kann die Gleichgewichtsachse in Abhängigkeit der Geometrien der Laufschaufeln koaxial bzw. achsparallel zu einer Auffädelachse der Laufschaufelprofile verlaufen. Mit Hilfe der erfindungsgemäßen Anordnung der benachbarten Laufschaufeln wird daher eine Schwerpunktsverlagerung insbesondere im Bereich der Kontaktflächen der radial äußeren Deckbänder erzielt. Durch die während des Betriebs der zugeordneten Strömungsmaschine entstehenden Fliehkräfte können somit auf konstruktiv einfache Weise drehzahlabhängige Anpresskräfte zwischen den zumindest zwei Laufschaufelsegmenten erzeugt werden, die zu einer verbesserten mechanischen Kopplung der Laufschaufelsegmente und einer entsprechenden Verbesserung der schwingungsmechanischen Eigenschaften führen.An inventive blade system for a blade row of a turbomachine having improved vibration mechanical properties is provided in that radial equilibrium axes of adjacent blades of the at least two blade segments are each axially tilted at an angle to their respective base pitch, the angles having opposite signs relative to the ground tilt , In other words, it is provided that adjacent blades of the at least two blade segments are arranged starting from their respective base inclination tilted like a scissor. The basic inclination, which is also called "lean", is usually used during the operation of the associated turbomachine gas forces that generate corresponding bending moments on the blades, at least in certain operating areas of the turbomachine largely compensate. The basic inclination, about which the equilibrium axes of the rotor blades are tilted, is in this case usually between 0 ° and 2 °, depending on the configuration of the turbomachine. In this case, the equilibrium axis can run coaxially or axially parallel to a threading axis of the blade profiles depending on the geometries of the rotor blades. With the help of the invention Arrangement of the adjacent blades, therefore, a center of gravity displacement is achieved, in particular in the region of the contact surfaces of the radially outer shrouds. As a result of the centrifugal forces occurring during operation of the associated turbomachine, rotationally dependent contact forces between the at least two blade segments can thus be generated in a structurally simple manner, which leads to improved mechanical coupling of the blade segments and a corresponding improvement in the vibration-mechanical properties.

Indem die Winkel, um welche die radialen Gleichgewichtsachsen gegenüber ihrer jeweiligen Grundneigungen verkippt angeordnet sind, betragsmäßig gleich sind, werden während des Betriebs des Laufschaufelsystems entsprechend betragsmäßig gleiche, einander entgegengerichtete Anpresskräfte an den Kontaktflächen der Laufschaufelsegmente erzeugt. Somit kann das Entstehen unerwünschter Biegemomente zwischen den Laufschaufelsegmenten zuverlässig verhindert werden.By virtue of the fact that the angles by which the radial equilibrium axes are tilted with respect to their respective basic inclinations are equal in magnitude, equal, oppositely directed contact forces are generated at the contact surfaces of the blade segments during operation of the rotor blade system. Thus, the generation of undesirable bending moments between the blade segments can be reliably prevented.

Weiter Vorteile ergeben sich, indem die Laufschaufeln wenigstens eines Laufschaufelsegments einstückig mit dem inneren Deckband und/oder mit dem äußeren Deckband ausgebildet sind. Hierdurch wird eine erhebliche Reduzierung von Fertigungskosten aufgrund der geringeren Anzahl zu montierender Bauteile erzielt.Further advantages result from the fact that the rotor blades of at least one blade segment are formed integrally with the inner shroud and / or with the outer shroud. As a result, a significant reduction in manufacturing costs due to the lower number of components to be mounted is achieved.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Laufschaufeln in das innere Deckband und/oder in das äußere Deckband eingegossen sind. Dies ermöglicht auf kostengünstige Weise eine mechanisch stabile und betriebssichere Anbindung der Laufschaufeln an das betreffende Deckband.In a further advantageous embodiment of the invention it is provided that the blades are cast in the inner shroud and / or in the outer shroud. This allows a cost-effective manner a mechanically stable and reliable connection of the blades to the relevant shroud.

Weitere Vorteile ergeben sich, wenn die Kontaktflächen als mechanische Verklinkung ausgebildet sind. Hierdurch können die mit Hilfe des erfindungsgemäßen Laufschaufelsystems erzielbaren Anpresskräfte flächig verteilt werden, so dass im Unterschied zum Stand der Technik keine elastischen Verformungen auftreten, sondern die entstehenden Kräfte im Bereich der Kontaktflächen als Anpresskräfte abgesetzt werden können. Hierdurch wird eine mechanisch besonders stabile Kopplung der wenigstens zwei Laufschaufelsegmente erzielt, so dass das Laufschaufelsystem schwingungsmechanisch unkritisch ist.Further advantages arise when the contact surfaces are designed as a mechanical latch. As a result, the pressing forces achievable with the aid of the rotor blade system according to the invention can be distributed over a wide area, so that in contrast to the prior art, no elastic deformations occur, but the resulting forces in the area of the contact surfaces can be discontinued as contact forces. This will be a mechanically particularly stable coupling of the at least two blade segments achieved, so that the blade system is not critical vibration mechanics.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass ein Betrag der Winkel zwischen 0,1° und 10°, insbesondere zwischen 0,1° und 5° und vorzugsweise zwischen 0,1° und 2° beträgt. Dies erlaubt einerseits eine vorteilhafte Anpassbarkeit an unterschiedlich ausgebildete Laufschaufeln bzw. Strömungsmaschinen und ermöglicht zudem eine präzise Schwerpunktverlagerung mit entsprechend gezielt anpassbaren Fliehkräften während des Betriebs.In a further advantageous embodiment of the invention it is provided that an amount of the angle between 0.1 ° and 10 °, in particular between 0.1 ° and 5 °, and preferably between 0.1 ° and 2 °. On the one hand, this allows an advantageous adaptability to differently shaped blades or turbomachines and, moreover, enables a precise shifting of the center of gravity with correspondingly specifically adaptable centrifugal forces during operation.

Ein weiterer Aspekt der Erfindung betrifft eine Strömungsmaschine, insbesondere eine thermische Gasturbine, mit einer Laufschaufelreihe, welche ein Laufschaufelsystem aus wenigstens zwei Laufschaufelsegmenten umfasst, von welchen jedes Laufschaufelsegment mindestens zwei Laufschaufeln aufweist, die bezüglich einer Drehachse der Laufschaufelreihe zumindest überwiegend radial zwischen einem radial inneren und einem radial äußeren Deckband angeordnet und mit den Deckbändem gekoppelt sind, wobei zumindest die radial äußeren Deckbänder der zwei Laufschaufelsegmente miteinander korrespondierende Anwendungsbereiche umfassen, über welche die Laufschaufelsegmente miteinander gekoppelt sind. Um verbesserte schwingungsmechanische Eigenschaften zu erzielen ist es dabei erfindungsgemäß vorgesehen, dass radiale Gleichgewichtsachsen benachbarter Laufschaufeln der wenigstens zwei Laufschaufelsegmente jeweils axial um einen Winkel gegenüber ihrer jeweiligen Grundneigung verkippt sind, wobei die Winkel bezüglich der Grundneigung entgegengesetzte Vorzeichen aufweisen. Auf diese Weise wird eine gezielte Schwerpunktsverlagerung der Laufschaufeln erreicht, so dass während des Betriebs der Laufschaufelreihe beziehungsweise der Strömungsmaschine eine aufrichtende Kraft auf die benachbarten Laufschaufeln entsteht, die zu einer mechanisch stabilen und schwingungsmechanisch unkritischen Kopplung der Anbindungsbereiche und damit der wenigstens zwei Laufschaufelsegmente führt.Another aspect of the invention relates to a turbomachine, in particular a thermal gas turbine, with a blade row, which comprises a blade system of at least two blade segments, each of which blade segment at least two blades, with respect to a rotational axis of the blade row at least predominantly radially between a radially inner and a radially outer shroud and are coupled to the Deckbändem, wherein at least the radially outer shrouds of the two blade segments comprise mutually corresponding application areas, via which the blade segments are coupled together. In order to achieve improved vibration mechanical properties, it is provided according to the invention that radial equilibrium axes of adjacent blades of the at least two blade segments are each tilted axially at an angle to their respective base pitch, wherein the angles have opposite signs with respect to the base pitch. In this way, a targeted center of gravity displacement of the blades is achieved, so that during operation of the blade row or the turbomachine a righting force on the adjacent blades arises, which leads to a mechanically stable and vibration mechanical uncritical coupling of the connection areas and thus the at least two blade segments.

Weitere Vorteile ergeben sich, indem das Laufschaufelsystem der Laufschaufelreihe gemäß einem der vorhergehenden Ausführungsbeispiele ausgebildet ist. Die sich hieraus ergebenden Vorteile sind den entsprechenden Vorteilsbeschreibungen zu entnehmen.Further advantages result from the blade system of the blade row being designed in accordance with one of the preceding exemplary embodiments. The resulting advantages can be found in the corresponding description of benefits.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Laufschaufelreihe in einem Turbinenbereich, insbesondere einem Niederdruck-Turbinenbereich der Strömungsmaschine angeordnet ist. Hierdurch ist es möglich, die Strömungsmaschine mit wenigen Laufschaufelreihen zu versehen, wodurch erhebliche Gewichts- und Kosteneinsparungen gegeben sind. Aufgrund der Kopplung der Laufschaufeln mit den Deckbändem einerseits und der Kopplung der wenigstens zwei Laufschaufelsegmente miteinander andererseits, reduzieren sich in der Laufschaufelreihe die Anzahl der Fugen und Spalte, wodurch etwaige Strömungsverluste entsprechend reduziert werden. Zudem bieten sich den im Turbinenbereich auftretenden, aggressiven Heißgasen weniger Angriffsflächen, wodurch die Haltbarkeit der Laufschaufelreihe und der Strömungsmaschine insgesamt gesteigert wird.In a further advantageous embodiment of the invention it is provided that the blade row is arranged in a turbine region, in particular a low-pressure turbine region of the turbomachine. This makes it possible to provide the turbomachine with a few blade rows, which are significant weight and cost savings. Due to the coupling of the blades with the Deckbändem one hand, and the coupling of the at least two blade segments together on the other hand, reduce the number of joints and gaps in the blade row, whereby any flow losses are reduced accordingly. In addition, the aggressive hot gases occurring in the turbine area have fewer attack surfaces, which increases the overall durability of the blade row and of the turbomachine.

Ein weiterer Aspekt der Erfindung betrifft ein Verfahren zum Montieren einer Laufschaufelreihe für eine Strömungsmaschine, insbesondere für eine thermische Gasturbine, bei welchem wenigstens zwei Laufschaufelsegmente eines Laufschaufelsystems gemäß einem der vorhergehenden Ausführungsbeispiele bereitgestellt und diejenigen Laufschaufeln der wenigstens zwei Laufschaufelsegmente, die jeweils axial um einen Winkel (αa, αb) gegenüber ihrer jeweiligen Grundneigung verkippt sind, benachbart zueinander angeordnet werden, wobei die Winkel bezüglich der Grundneigung der Laufschaufeln entgegengesetzte Vorzeichen aufweisen. Dies erlaubt eine mechanisch stabile und schwingungsmechanisch unkritische Montage der Laufschaufelreihe, wodurch eine erhebliche Reduzierung der Fertigungskosten bei gleichzeitig erhöhter Haltbarkeit gegeben ist. Ein weiterer Vorteil besteht darin, dass die verspannenden Anpresskräfte zwischen den Laufschaufelsegmenten erst drehzahlabhängig während des Betriebs der Strömungsmaschine auftreten, so dass die Laufschaufelsegmente im Stand besonders leicht montierbar bzw. demontierbar sind. Weiter Vorteile ergeben sich, wenn die Anbindungsbereiche der Laufschaufelsegmente verformungsfrei miteinander gekoppelt werden. Im Unterschied zum Stand der Technik, in welchem aufgrund der Torsion der Schaufelprofile gegenüber den Deckbändern die Anpresskraft an den Anbindungsbereichen durch elastische Verformung erzeugt werden muss und auch im Stand wirft, kann mit Hilfe des erfindungsgemäßen Verfahrens und der Schwerpunktverlagerung der Laufschaufeln während des Betriebs eine Vorspannung und damit eine schwingungsmechanisch unkritische Kopplung der wenigstens zwei Laufschaufelsegmente auch ohne Verformung erzielt werden.Another aspect of the invention relates to a method for mounting a blade row for a turbomachine, in particular for a thermal gas turbine, wherein at least two blade segments of a blade system according to one of the preceding embodiments provided and those blades of the at least two blade segments, each axially at an angle ( α a , α b ) are tilted relative to their respective base pitch, are arranged adjacent to each other, wherein the angles with respect to the base pitch of the blades have opposite signs. This allows a mechanically stable and vibration-mechanically uncritical assembly of the blade row, whereby a significant reduction in manufacturing costs is given at the same time increased durability. Another advantage is that the bracing contact forces between the blade segments only occur speed-dependent during operation of the turbomachine, so that the blade segments are particularly easy to assemble or disassemble in the state. Further advantages arise when the connection areas of the blade segments are coupled together without deformation. In contrast to the prior art, in which due to the torsion of the blade profiles over the shrouds, the contact force must be generated at the connection areas by elastic deformation and also in the state, can with the aid of the inventive method and the center of gravity displacement of the blades during operation, a bias and thus a vibration mechanical uncritical coupling of the at least two blade segments are achieved without deformation.

Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich anhand der nachfolgenden Beschreibung eines Ausführungsbeispiels sowie anhand der Zeichnung. Dabei zeigt die einzige Figur eine schematische Perspektivansicht von zwei miteinander gekoppelten Laufschaufelsegmenten eines Laufschaufelsystems für eine Laufschaufelreihe zur Anordnung in einem Niederdruck-Turbinenbereich einer thermischen Gasturbine.Further advantages, features and details of the invention will become apparent from the following description of an embodiment and from the drawing. The single figure shows a schematic perspective view of two coupled blade segments of a blade system for a blade row for arrangement in a low-pressure turbine section of a thermal gas turbine.

Die einzige Figur zeigt eine schematische Perspektivansicht von zwei miteinander gekoppelten Laufschaufelsegmenten 10a, 10b eines aus einer Mehrzahl von Laufschaufelsegmenten 10 ausgebildeten Laufschaufelsystems für eine Laufschaufelreihe, die zur Anordnung in einem Niederdruck-Turbinenbereich einer thermischen Gasturbine (nicht dargestellt) dient. Jedes Laufschaufelsegment 10a, 10b umfasst im vorliegenden Ausführungsbeispiel jeweils vier Laufschaufeln 12 (Airfoils), die bezüglich einer Drehachse der in der Strömungsmaschine montierten Laufschaufelreihe überwiegend radial zwischen einem radial inneren Deckband 14a, 14a' und einem radial äußeren Deckband 14b, 14b' angeordnet und mit den Deckbändern 14a, 14b beziehungsweise 14a', 14b' gekoppelt sind. Die radial äußeren Deckbänder 14b, 14b' der beiden Laufschaufelsegmente 10a, 10b umfassen miteinander korrespondierend ausgebildete Kontaktflächen 16a, 16b, mit einem Z-förmigen Verlauf (sog. Z-shroud). Die winklig zueinander angeordneten Kontaktflächen 16a, 16b sind dabei als mechanische Verklinkung ausgebildet. Die Laufschaufeln 12 sind jeweils in die inneren und äußeren Deckbänder 14a, 14a', 14b, 14b' eingegossen, um eine mechanisch stabile Verbindung mit geringem Gewicht zu erzielen. Da die mehrere Laufschaufeln 12 umfassenden Laufschaufelsegmente 10a, 10b (sog. Cluster) im Unterschied zu einzelnen Laufschaufeln 12 nicht mehr durch Torsion gegenüber den Deckbändern 14a, 14a', 14b, 14b' gegeneinander verspannt werden können, wird die erforderliche Anpresskraft zwischen den Kontaktflächen 16a, 16b während des Betriebs der zugeordneten Strömungsmaschine dadurch erzeugt, dass radiale Gleichgewichtsachsen A benachbarter Laufschaufeln 12 der wenigstens zwei Laufschaufelsegmente 10a, 10b jeweils axial um einen Winkel αa, αb gegenüber ihrer jeweiligen Grundneigung (sog. Lean) verkippt angeordnet sind. Die Winkel αa, αb sind dabei derart gewählt, dass benachbarte Laufschaufeln 12 bezüglich ihrer jeweiligen Grundneigung um einander entgegen gesetzte, aber betragsmäßig gleiche Winkel αa bzw. αb scherenartig verkippt sind. Mit anderen Worten ist eine Laufschaufel 12 gegenüber dem Lean bezüglich einer Drehachse des Laufschaufelsystems nach hinten und die benachbarte Laufschaufel 12 entsprechend nach vorne verkippt. Hierdurch wird eine Schwerpunktverlagerung der betroffenen Laufschaufeln 12 erreicht, wodurch aufgrund der Fliehkräfte während des Betriebs der zugeordneten Strömungsmaschine drehzahlabhängige aufrichtende Kräfte entstehen, die sich gemäß den Pfeilen 18a, 18b in den Kontaktflächen 16a, 16b als Anpresskräfte absetzen. Auf diese Weise sind die Laufschaufelsegmente 10a, 10b während des Betriebs mechanisch gekoppelt, so dass das gesamte Laufschaufelsystem beziehungsweise die Laufschaufelreihe schwingungsmechanisch unkritisch ist. Die Anpresskräfte steigen dabei mit der Drehzahl an. Umgekehrt wirkt zwischen den Laufschaufelsegmenten 10a, 10b im Stand keine Anpresskraft, wodurch diese entsprechend leicht montierbar und demontierbar sind. Die Winkel αa, αb betragen dabei im gezeigten Ausführungsbeispiel etwa ±1°. Grundsätzlich können jedoch abweichende Winkel α bzw. betragsmäßig unterschiedlich große Winkel αa, αb gewählt werden. Es ist vorzugsweise vorgesehen, dass die randständigen Laufschaufeln 12 jedes Laufschaufelsegments 10 ebenfalls um einander entgegengesetzte Winkel α gegenüber ihrer jeweiligen Grundneigung verkippt sind. Alternativ oder zusätzlich kann auch vorgesehen sein, dass innere Laufschaufeln 12 der jeweiligen Laufschaufelsegmente 10 um einen Winkel α gegenüber ihrer jeweiligen Grundneigung verkippt sind.The sole FIGURE is a schematic perspective view of two coupled blade segments 10a, 10b of a blade row blade system formed from a plurality of blade segments 10 for placement in a low pressure turbine section of a thermal gas turbine (not shown). Each blade segment 10a, 10b comprises in the present embodiment in each case four blades 12 (Airfoils), which are arranged with respect to a rotation axis of the blade row mounted in the turbomachine predominantly radially between a radially inner shroud 14a, 14a 'and a radially outer shroud 14b, 14b' and the shrouds 14a, 14b and 14a ', 14b' are coupled. The radially outer shrouds 14b, 14b 'of the two blade segments 10a, 10b comprise mutually correspondingly formed contact surfaces 16a, 16b, with a Z-shaped profile (so-called Z-shroud). The contact surfaces 16a, 16b which are arranged at an angle to one another are designed as mechanical latches. The blades 12 are respectively cast into the inner and outer shrouds 14a, 14a ', 14b, 14b' to achieve a mechanically stable, lightweight connection. As the several rotor blades 12 comprehensive blade segments 10 a, 10 b (so-called. Cluster), in contrast to individual blades 12 no longer by torsion relative to the shrouds 14a, 14a ', 14b, 14b' can be clamped against each other, the required contact force between the contact surfaces 16a, 16b generated during operation of the associated turbomachine that radial equilibrium axes A adjacent blades 12 of at least two blade segments 10a, 10b are each axially by an angle α a, α b compared to their respective baseline slope (so-called. Lean) are arranged tilted. The angles α a, α b are selected such that adjacent rotor blades 12 with respect to its respective base to tilt mutually opposite, but in amount equal angles α a and α b tilted like scissors. In other words, a blade 12 is tilted rearward relative to the lean relative to a rotational axis of the blade system and the adjacent blade 12 is tilted forward accordingly. As a result, a center of gravity displacement of the blades concerned 12 is achieved, which due to the centrifugal forces during operation of the associated turbomachine speed-dependent righting forces arise that settle according to the arrows 18a, 18b in the contact surfaces 16a, 16b as contact forces. In this way, the blade segments 10a, 10b are mechanically coupled during operation, so that the entire blade system or the blade row is vibration-mechanically uncritical. The contact forces increase with the speed. Conversely, no contact force acts between the blade segments 10a, 10b in the stationary state, as a result of which they are correspondingly easy to assemble and disassemble. The angles α a , α b are in the illustrated embodiment about ± 1 °. In principle, however, deviating angles α or, in terms of magnitude, different angles α a , α b can be selected. It is preferably contemplated that the marginal blades 12 of each blade segment 10 are also tilted about opposing angles α with respect to their respective base pitch. Alternatively or additionally, it may also be provided that inner rotor blades 12 of the respective blade segments 10 are tilted by an angle α relative to their respective base inclination.

Claims (10)

  1. A rotating-blade system for a row of rotating blades of a turbo-machine, in particular a thermal gas turbine, having at least two rotating-blade segments (10a, 10b), of which each rotating-blade segment (10a, 10b) comprises at least two rotating blades (12) which with regard to a rotational axis of the row of rotating blades are arranged at least predominantly radially between a radially inner and a radially outer shroud band (14a, 14a', 14b, 14b') and are coupled with the shroud bands (14a, 14a', 14b, 14b'), wherein at least the radially outer shroud bands (14b, 14b') of the two rotating-blade segments (10a, 10b) include contact surfaces (16a, 16b) that correspond with each other, characterised in that radial equilibrium axes (A) of adjacent rotating blades (12) of the at least two rotating-blade segments (10a, 10b) are in each case arranged so as to be tilted axially about an angle (αa, αb) in relation to their respective basic inclination, wherein the angles (αa, αb) with regard to the basic inclination have opposite signs.
  2. A rotating-blade system according to claim 1, characterised in that the angles (αa, αb) are equal in magnitude.
  3. A rotating-blade system according to claim 1 or 2, characterised in that the rotating blades (12) of at least one rotating-blade segment (10a, 10b) are formed in one piece with the inner shroud band (14a, 14a') and/or with the outer shroud band (14b, 14b').
  4. A rotating-blade system according to one of claims 1 to 3, characterised in that the rotating blades (12) are cast into the inner shroud band (14a, 14a') and/or into the outer shroud band (14b, 14b').
  5. A rotating-blade system according to one of claims 1 to 4, characterised in that the contact surfaces (16a, 16b) are formed as a kind of mechanical latching.
  6. A rotating-blade system according to one of claims 1 to 5, characterised in that an amount of the angles (αa, αb) amounts to between 0.1° and 10°, in particular between 0.1° and 5° and preferably between 0.1° and 2°.
  7. A turbo-machine, in particular a thermal gas turbine, having a row of rotating blades which comprises a rotating-blade system according to one of claims 1 to 6.
  8. A turbo-machine according to claim 7, characterised in that the row of rotating blades is arranged in a turbine region, in particular a low-pressure turbine region, of the turbo-machine.
  9. Method for mounting a row of rotating blades for a turbo-machine, in particular for a thermal gas turbine, in which at least two rotating-blade segments (10a, 10b) of a rotating-blade system provided according to one of claims 1 to 6 and those rotating blades (12) of the at least two rotating-blade segments (10a, 10b) that are in each case tilted axially about an angle (αa, αb) in relation to their respective basic inclination are arranged so as to be adjacent to each other, wherein the angles (αa, αb) with regard to the basic inclination of the rotating blades (12) have opposite signs.
  10. Method according to claim 9, characterised in that the rotating-blade segments (10a, 10b) are coupled together without deformation.
EP09776055A 2008-08-16 2009-08-01 Rotating blade system for a row of rotating blades of a turbomachine Not-in-force EP2310634B1 (en)

Applications Claiming Priority (2)

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DE102008038038A DE102008038038A1 (en) 2008-08-16 2008-08-16 Blade system for a blade row of a turbomachine
PCT/DE2009/001094 WO2010020210A2 (en) 2008-08-16 2009-08-01 Rotating blade system for a row of rotating blades of a turbomachine

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EP2310634A2 EP2310634A2 (en) 2011-04-20
EP2310634B1 true EP2310634B1 (en) 2012-03-14

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US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
EP2639004B1 (en) * 2012-03-15 2016-05-11 MTU Aero Engines GmbH Blade ring segment with inner end wall having an undulating height profile and method for producing same
ITTO20120517A1 (en) * 2012-06-14 2013-12-15 Avio Spa AERODYNAMIC PROFILE PLATE FOR A GAS TURBINE SYSTEM
US10774661B2 (en) 2017-01-27 2020-09-15 General Electric Company Shroud for a turbine engine
CN114233399B (en) * 2022-02-23 2022-05-17 成都中科翼能科技有限公司 Method for controlling contact stress of turbine rotor blade shroud contact surface

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GB2215407A (en) * 1988-03-05 1989-09-20 Rolls Royce Plc A bladed rotor assembly
GB2251034B (en) * 1990-12-20 1995-05-17 Rolls Royce Plc Shrouded aerofoils
DE59202211D1 (en) * 1991-08-08 1995-06-22 Asea Brown Boveri Cover sheet for turbine with axial flow.
FR2851285B1 (en) * 2003-02-13 2007-03-16 Snecma Moteurs REALIZATION OF TURBINES FOR TURBOMACHINES HAVING DIFFERENT ADJUSTED RESONANCE FREQUENCIES AND METHOD FOR ADJUSTING THE RESONANCE FREQUENCY OF A TURBINE BLADE
AU2003266505A1 (en) * 2003-09-10 2005-04-06 Hitachi, Ltd. Turbine rotor blade
US7648334B2 (en) * 2005-12-29 2010-01-19 Rolls-Royce Power Engineering Plc Airfoil for a second stage nozzle guide vane

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US20110142652A1 (en) 2011-06-16
ATE549487T1 (en) 2012-03-15
CA2734071A1 (en) 2010-02-25
WO2010020210A3 (en) 2010-11-18
WO2010020210A2 (en) 2010-02-25

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