EP2597266B1 - Rotor blade and flow machine - Google Patents

Rotor blade and flow machine Download PDF

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Publication number
EP2597266B1
EP2597266B1 EP20110190041 EP11190041A EP2597266B1 EP 2597266 B1 EP2597266 B1 EP 2597266B1 EP 20110190041 EP20110190041 EP 20110190041 EP 11190041 A EP11190041 A EP 11190041A EP 2597266 B1 EP2597266 B1 EP 2597266B1
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EP
European Patent Office
Prior art keywords
blade
sealing
root
platform
rotor
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
EP20110190041
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German (de)
French (fr)
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EP2597266A1 (en
Inventor
Rudolf Stanka
Manfred Feldmann
Manfred Schill
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Priority to EP20110190041 priority Critical patent/EP2597266B1/en
Publication of EP2597266A1 publication Critical patent/EP2597266A1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and 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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular

Definitions

  • the invention relates to a blade for a turbomachine according to the preamble of patent claim 1 and a turbomachine.
  • Blades for a turbomachine such as an aircraft engine or a stationary gas turbine have a blade root, an airfoil and a blade neck or a blade shank arranged between the blade root and the blade leaf, which forms an inner platform.
  • the platform constitutes a radially inner boundary of a hot gas channel and is intended to prevent a radial gas exchange between the hot gas channel and a hub-side cooling air channel.
  • a front sealing wall and a rear sealing wall may be arranged, extending from the platform in the direction of the blade root and an interior with a mean pressure gradient with respect to the hot gas duct and limit the cooling air channel.
  • a blade with such sealing walls is, for example, in the German patent application DE 10 2009 007 664 A1 shown.
  • the sealing walls are provided in the region of the inner platform with a rounded or a parabolic transition cross-section such that at least one of the sealing walls is offset with respect to a blade root edge in the direction of a radial longitudinal axis or vertical axis of the blade neck. Since the sealing walls stiffen the blade neck, stresses can be transmitted to the blade root. At the same time, voltage peaks, which are caused, for example, by a torsion of the blade, by centrifugal forces or by gas forces, are reduced at the blade root. However, the stiffening can have a negative effect on the excitation behavior of the blade, for example with respect to the position of resonance vibrations.
  • the object of the invention is to provide a blade for a turbomachine, which eliminates the aforementioned disadvantages and in addition to a reduced bending stiffness has improved vibration behavior. Furthermore, it is an object of the invention to provide a turbomachine with a quiet rotor.
  • a rotor blade according to the invention for a turbomachine has a blade root, an airfoil and a blade neck which is arranged between the blade root and the blade leaf and forms an inner platform.
  • the blade neck has a front-side sealing wall which is viewed in the flow direction and a rear sealing wall which is viewed in the flow direction and which delimits with the platform a triangular interior which narrows radially from outside to inside.
  • the blade according to the invention is characterized by a reduced flexural rigidity in the blade neck region, since the alignment of the sealing walls results in a change in the mass distribution in the region of the blade neck. However, the torsional rigidity of the blade is maintained, which has a positive effect on the vibration behavior.
  • one of the sealing walls is shovel side offset in the direction of the other sealing wall.
  • the interior can be formed asymmetrically.
  • the sealing walls are offset on the blade root side in the direction of the respective other sealing wall.
  • the interior can be formed both asymmetrically and symmetrically.
  • the sealing walls are merged blade side on the blade vertical axis.
  • the sealing walls are brought together at the blade root.
  • a cooling air flow can be conducted from an upstream side of the blade to the downstream side of the blade, without fear of a blade-side heating of the cooling air flow, since the interior due to the merging of the sealing walls according to the invention form a minimal contact area or almost no contact area with the blade root.
  • a turbomachine according to the invention has a multiplicity of rotor blades according to the invention.
  • Such a turbomachine is characterized in particular by an improved cooling air flow, a reduced mixing of a hot gas flow with a cooling air flow, no or almost no warming up of the cooling air flow by blade-side convection heat and due to the improved vibration behavior of the blade by a quiet rotor run.
  • FIG. 1 shows a side view of a mounted blade according to the invention.
  • FIG. 1 has a blade 1 according to the invention for a turbomachine a blade root 2, an airfoil 4 and arranged between the blade root 2 and the blade 4 blade neck 6.
  • the turbomachine is preferably an aircraft engine, but may also be a stationary gas turbine.
  • the blade 1 is mounted with a plurality of similar blades to a blade row and this used by means of their blade root 2 in an unnumbered axial groove of a rotor hub 8.
  • the blade row can be arranged both on the turbine side and on the compressor side.
  • the rotor hub 8 is mounted about a rotation axis 10 and forms a rotor section with the blade row.
  • a locking plate 12 is inserted into the axial groove, whose end portions are bent radially outward.
  • the blade neck 6 forms an inner platform 14 which, viewed in the flow direction, has a front projection 16 and a rear projection 18 and which, together with the platforms of the remaining blades of the blade row, forms a radially inward side boundary of a hot gas channel 20.
  • the platform 14 or the inner cover strip with the remaining inner platforms forms a radially outer boundary of a hub-side cooling air channel 22 and thus separates the hot gas duct 20 and the cooling air duct 22 from each other.
  • Radial outboard the hot gas duct 20 is bounded by a tip side arranged outer shroud 24 of the blade 1.
  • the cooling air channel 22 is bounded radially inwardly by a drum body 26 of the rotor hub 8.
  • the blade neck 6 is formed as a web with side pockets which form an interior space 28.
  • the interior space 28 is delimited by the platform 14 and a front sealing wall 30, viewed in the flow direction, and a rear sealing wall 32, and has an average pressure gradient with respect to the hot gas duct 20 and the cooling air duct 22.
  • the sealing walls 30, 32 are rectilinear and extend from transition regions of the projections 16, 18 on the blade neck 6 in the direction of the blade root 2. Starting from the platform 14, the sealing walls 30, 32 obliquely to the vertical axis 34 of the blade 1 and employed on the Blade foot 2 or at its pointing in the direction of the platform 14 edge 36 merged.
  • the sealing walls 30, 32 have approximately the same length and are employed at approximately the same angle to the vertical axis 34, so that the inner space 28 is almost symmetrical to the vertical axis 34 and the platform 14 with the sealing walls 30, 32 form an almost isosceles triangle.
  • the interior space 28 has a triangular, in particular a triangular, cross-section which, viewed from the platform 14 in the direction of the blade root 2, narrows continuously or closes radially from outside to inside. Accordingly, the interior 28 widens funnel-shaped viewed from the blade root 2 in the direction of the platform 14 and opens radially from the inside to the outside.
  • the sealing walls 30, 32 are brought together on the blade root 2 or on its edge 36 on the vertical axis 34.
  • a blade for a turbomachine with a blade root, an airfoil and with a blade neck disposed between the blade root and the blade blade, which forms an inner platform, wherein the blade neck has a front sealing wall and a rear sealing wall, which is triangular with the platform, Preferably define a triangular, interior, which narrows radially from outside to inside, and a turbomachine with a plurality of such blades.

Landscapes

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

Description

Die Erfindung betrifft eine Laufschaufel für eine Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1 sowie eine Strömungsmaschine.The invention relates to a blade for a turbomachine according to the preamble of patent claim 1 and a turbomachine.

Laufschaufeln für eine Strömungsmaschine wie ein Flugzeugtriebwerk oder eine stationäre Gasturbine haben einen Schaufelfuß, ein Schaufelblatt sowie einen zwischen dem Schaufelfuß und dem Schaufelblatt angeordneten Schaufelhals bzw. einen Schaufelschaft, der eine innere Plattform bildet. Die Plattform stellt eine radial innere Begrenzung eines Heißgaskanals dar und soll einen radialen Gasaustausch zwischen dem Heißgaskanal und einem nabenseitigen Kühlluftkanal verhindern. Um einen axialen Gasaustausch im Bereich des Kühlluftkanals zwischen benachbarten Laufschaufeln hindurch zu beeinflussen, können im Schaufelhalsbereich jeweils eine vordere Dichtwand und eine hintere Dichtwand angeordnet sein, die sich von der Plattform in Richtung des Schaufelfußes erstrecken und einen Innenraum mit einem mittleren Druckgefälle gegenüber dem Heißgaskanal und dem Kühlluftkanal begrenzen. Eine Laufschaufel mit derartigen Dichtwänden ist bspw. in der deutschen Patentanmeldung DE 10 2009 007 664 A1 gezeigt. Die Dichtwände sind im Bereich der inneren Plattform mit einem abgerundeten oder einem parabolischen Übergangsquerschnitt derart versehen, dass zumindest eine der Dichtwände bezüglich eines Schaufelfußrandes in Richtung einer Radiallängsachse bzw. Hochachse des Schaufelhalses versetzt ist. Da die Dichtwände den Schaufelhals versteifen, können Spannungen an den Schaufelfuß weitergeleitet werden. Gleichzeitig werden Spannungsspitzen, die bspw. durch eine Torsion der Laufschaufel, durch Fliehkräfte oder durch Gaskräfte verursacht werden, am Schaufelfuß reduziert. Allerdings kann sich die Versteifung negativ auf das Anregungsverhalten der Laufschaufel, bspw. bezüglich der Position von Resonanzschwingungen, auswirken.Blades for a turbomachine such as an aircraft engine or a stationary gas turbine have a blade root, an airfoil and a blade neck or a blade shank arranged between the blade root and the blade leaf, which forms an inner platform. The platform constitutes a radially inner boundary of a hot gas channel and is intended to prevent a radial gas exchange between the hot gas channel and a hub-side cooling air channel. In order to influence an axial gas exchange in the region of the cooling air duct between adjacent blades, in the blade neck region in each case a front sealing wall and a rear sealing wall may be arranged, extending from the platform in the direction of the blade root and an interior with a mean pressure gradient with respect to the hot gas duct and limit the cooling air channel. A blade with such sealing walls is, for example, in the German patent application DE 10 2009 007 664 A1 shown. The sealing walls are provided in the region of the inner platform with a rounded or a parabolic transition cross-section such that at least one of the sealing walls is offset with respect to a blade root edge in the direction of a radial longitudinal axis or vertical axis of the blade neck. Since the sealing walls stiffen the blade neck, stresses can be transmitted to the blade root. At the same time, voltage peaks, which are caused, for example, by a torsion of the blade, by centrifugal forces or by gas forces, are reduced at the blade root. However, the stiffening can have a negative effect on the excitation behavior of the blade, for example with respect to the position of resonance vibrations.

Aufgabe der Erfindung ist es, eine Laufschaufel für eine Strömungsmaschine zu schaffen, die die vorgenannten Nachteile beseitigt und neben einer reduzierten Biegesteifigkeit ein verbessertes Schwingverhalten aufweist. Des Weiteren ist es Aufgabe der Erfindung, eine Strömungsmaschine mit einem ruhigen Rotorlauf zu schaffen.The object of the invention is to provide a blade for a turbomachine, which eliminates the aforementioned disadvantages and in addition to a reduced bending stiffness has improved vibration behavior. Furthermore, it is an object of the invention to provide a turbomachine with a quiet rotor.

Diese Aufgabe wird gelöst durch eine Laufschaufel mit den Merkmalen des Patentanspruchs 1 und durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 7.This object is achieved by a blade having the features of patent claim 1 and by a turbomachine having the features of patent claim 7.

Eine erfindungsgemäße Laufschaufel für eine Strömungsmaschine hat einen Schaufelfuß, ein Schaufelblatt sowie einen zwischen dem Schaufelfuß und dem Schaufelblatt angeordneten Schaufelhals, der eine innere Plattform bildet. Erfindungsgemäß hat der Schaufelhals eine in Strömungsrichtung betrachtete vorde-re Dichtwand und eine in Strömungsrichtung betrachtete hintere Dichtwand, die mit der Plattform einen dreieckartigen Innenraum begrenzen, der sich radial von außen nach innen verengt.A rotor blade according to the invention for a turbomachine has a blade root, an airfoil and a blade neck which is arranged between the blade root and the blade leaf and forms an inner platform. According to the invention, the blade neck has a front-side sealing wall which is viewed in the flow direction and a rear sealing wall which is viewed in the flow direction and which delimits with the platform a triangular interior which narrows radially from outside to inside.

Die erfindungsgemäße Laufschaufel zeichnet sich durch eine reduzierte Biegesteifigkeit im Schaufelhalsbereich aus, da durch die Ausrichtung der Dichtwände eine veränderte Massenverteilung im Bereich des Schaufelhalses erreicht wird. Die Torsionssteifigkeit der Laufschaufel bleibt jedoch erhalten, was sich positiv auf das Schwingverhalten auswirkt.The blade according to the invention is characterized by a reduced flexural rigidity in the blade neck region, since the alignment of the sealing walls results in a change in the mass distribution in the region of the blade neck. However, the torsional rigidity of the blade is maintained, which has a positive effect on the vibration behavior.

Bei einem Ausführungsbeispiel ist eine der Dichtwände schaufelfußseitig in Richtung der anderen Dichtwand versetzt. Hierdurch kann der Innenraum asymmetrisch ausgebildet sein.In one embodiment, one of the sealing walls is shovel side offset in the direction of the other sealing wall. As a result, the interior can be formed asymmetrically.

Bei einem alternativen Ausführungsbeispiel sind die Dichtwände schaufelfußseitig in Richtung der jeweils anderen Dichtwand versetzt. Hierdurch kann der Innenraum sowohl asymmetrisch als auch symmetrisch ausgebildet sein.In an alternative embodiment, the sealing walls are offset on the blade root side in the direction of the respective other sealing wall. As a result, the interior can be formed both asymmetrically and symmetrically.

Bei einem weiteren Ausführungsbeispiel sind die Dichtwände schaufelfußseitig auf der Schaufelhochachse zusammengeführt. Hierdurch wird eine hohe Symmetrie im Bereich des Schaufelfußhals erreicht, was sich günstig auf das Schwingverhalten auswirkt.In a further embodiment, the sealing walls are merged blade side on the blade vertical axis. As a result, a high symmetry in the region of the blade root is achieved, which has a favorable effect on the vibration behavior.

Bevorzugterweise sind die Dichtwände an dem Schaufelfuß zusammengeführt. Hierdurch erfolgt eine Massenkonzentration auf der Hochachse im Bereich der Nabe und somit drehachsennah, was sich sehr positiv auf das Schwingverhalten auswirkt. Gleichzeitig kann ein Kühlluftstrom von einer stromaufwärtigen Schaufelseite zur stromabwärtigen Schaufelseite geführt werden, ohne dass eine schaufelfußseitige Erwärmung des Kühlluftstroms zu befürchten ist, da der Innenraum aufgrund der erfindungsgemäßen Zusammenführung der Dichtwände eine minimalen Kontaktbereich bzw. nahezu keinen Kontaktbereich mit dem Schaufelfuß bilden.Preferably, the sealing walls are brought together at the blade root. This results in a mass concentration on the vertical axis in the region of the hub and thus rotational axis close, which has a very positive effect on the vibration behavior. At the same time, a cooling air flow can be conducted from an upstream side of the blade to the downstream side of the blade, without fear of a blade-side heating of the cooling air flow, since the interior due to the merging of the sealing walls according to the invention form a minimal contact area or almost no contact area with the blade root.

Eine erfindungsgemäße Strömungsmaschine hat eine Vielzahl von erfindungsgemäßen Laufschaufeln. Eine derartige Strömungsmaschine zeichnet sich insbesondere durch eine verbesserte Kühlluftführung, eine reduzierte Vermischung eines Heißgasstromes mit einem Kühlluftstrom, durch keine bzw. nahezu keine Aufwärmung des Kühlluftstroms durch schaufelfußseitige Konvektionswärme und aufgrund des verbesserten Schwingverhaltens der Laufschaufel durch einen ruhigen Rotorlauf aus.A turbomachine according to the invention has a multiplicity of rotor blades according to the invention. Such a turbomachine is characterized in particular by an improved cooling air flow, a reduced mixing of a hot gas flow with a cooling air flow, no or almost no warming up of the cooling air flow by blade-side convection heat and due to the improved vibration behavior of the blade by a quiet rotor run.

Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.

Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand einer schematischen Darstellung näher erläutert. Die einzige Figur 1 zeigt eine Seitenansicht einer montierten erfindungsgemäßen Laufschaufel.In the following, a preferred embodiment of the invention is explained in more detail with reference to a schematic representation. The only FIG. 1 shows a side view of a mounted blade according to the invention.

Gemäß der Darstellung in Figur 1 hat eine erfindungsgemäße Laufschaufel 1 für eine Strömungsmaschine einen Schaufelfuß 2, ein Schaufelblatt 4 sowie einen zwischen dem Schaufelfuß 2 und dem Schaufelblatt 4 angeordneten Schaufelhals 6. Die Strömungsmaschine ist bevorzugterweise ein Flugzeugtriebwerk, kann jedoch auch eine stationäre Gasturbine sein. Die Laufschaufel 1 ist mit einer Vielzahl gleichartiger Laufschaufeln zu einer Laufschaufelreihe montiert und hierzu mittels ihres Schaufelfußes 2 in eine nicht bezifferte Axialnut einer Rotornabe 8 eingesetzt. Die Laufschaufelreihe kann sowohl turbinenseitig als auch verdichterseitig angeordnet sein. Die Rotornabe 8 ist um eine Drehachse 10 gelagert und bildet mit der Laufschaufelreihe einen Rotorabschnitt. Zur axialen Sicherung der Laufschaufel 1 an der Rotornabe 8 ist in die Axialnut ein Sicherungsblech 12 eingesetzt, dessen Endabschnitte radial nach außen gebogen sind.As shown in FIG. 1 has a blade 1 according to the invention for a turbomachine a blade root 2, an airfoil 4 and arranged between the blade root 2 and the blade 4 blade neck 6. The turbomachine is preferably an aircraft engine, but may also be a stationary gas turbine. The blade 1 is mounted with a plurality of similar blades to a blade row and this used by means of their blade root 2 in an unnumbered axial groove of a rotor hub 8. The blade row can be arranged both on the turbine side and on the compressor side. The rotor hub 8 is mounted about a rotation axis 10 and forms a rotor section with the blade row. For axial securing of the blade 1 to the rotor hub 8, a locking plate 12 is inserted into the axial groove, whose end portions are bent radially outward.

Der Schaufelhals 6 bildet eine innere Plattform 14, die in Strömungsrichtung betrachtet einen vorderen Vorsprung 16 und einen hinteren Vorsprung 18 aufweist und die mit den Plattformen der übrigen Laufschaufeln der Laufschaufelreihe eine radial innenliegende Seitenbegrenzung eines Heißgaskanals 20 darstellt. Zudem bildet die Plattform 14 bzw. das Innendeckband mit den übrigen inneren Plattformen eine radial außenliegende Begrenzung eines nabenseitigen Kühlluftkanals 22 und trennt somit den Heißgaskanal 20 und den Kühlluftkanal 22 voneinander. Radial außenliegend wird der Heißgaskanal 20 von einem spitzenseitig angeordneten Außendeckband 24 der Laufschaufel 1 begrenzt. Der Kühlluftkanal 22 wird radial innen von einem Trommelkörper 26 der Rotornabe 8 begrenzt.The blade neck 6 forms an inner platform 14 which, viewed in the flow direction, has a front projection 16 and a rear projection 18 and which, together with the platforms of the remaining blades of the blade row, forms a radially inward side boundary of a hot gas channel 20. In addition, the platform 14 or the inner cover strip with the remaining inner platforms forms a radially outer boundary of a hub-side cooling air channel 22 and thus separates the hot gas duct 20 and the cooling air duct 22 from each other. Radial outboard the hot gas duct 20 is bounded by a tip side arranged outer shroud 24 of the blade 1. The cooling air channel 22 is bounded radially inwardly by a drum body 26 of the rotor hub 8.

Der Schaufelhals 6 ist als ein Steg mit seitlichen Taschen ausgebildet, die einen Innenraum 28 bilden. Der Innenraum 28 ist von der Plattform 14 und einer in Strömungsrichtung betrachtet vorderen Dichtwand 30 und einer hinteren Dichtwand 32 begrenzt und weist gegenüber dem Heißgaskanal 20 und dem Kühlluftkanal 22 ein mittleres Druckgefälle auf. Die Dichtwände 30, 32 sind geradlinig ausgebildet und erstrecken sich von Übergangsbereichen der Vorsprünge 16, 18 an dem Schaufelhals 6 in Richtung des Schaufelfußes 2. Ausgehend von der Plattform 14 sind die Dichtwände 30, 32 schräg zur Hochachse 34 der Laufschaufel 1 angestellt und an dem Schaufelfuß 2 bzw. an dessen in Richtung der Plattform 14 weisenden Rand 36 zusammengeführt. Die Dichtwände 30, 32 haben in etwa ein gleiche Länge und sind etwa im gleichen Winkel zur Hochachse 34 angestellt, so dass der Innenraum 28 nahezu symmetrisch zur Hochachse 34 ist und die Plattform 14 mit den Dichtwänden 30, 32 nahezu ein gleichschenkeliges Dreieck bilden. Somit weist der Innenraum 28 einen dreieckartigen, insbesondere einem dreieckigen, Querschnitt auf, der sich von der Plattform 14 in Richtung des Schaufelfußes 2 betrachtet stetig verengt bzw. sich radial von außen nach innen schließt. Entsprechend erweitert sich der Innenraum 28 von dem Schaufelfuß 2 in Richtung der Plattform 14 betrachtet trichterförmig bzw. öffnet sich radial von innen nach außen. Insbesondere sind die Dichtwände 30, 32 an dem Schaufelfuß 2 bzw. an dessen Rand 36 auf der Hochachse 34 zusammengeführt.The blade neck 6 is formed as a web with side pockets which form an interior space 28. The interior space 28 is delimited by the platform 14 and a front sealing wall 30, viewed in the flow direction, and a rear sealing wall 32, and has an average pressure gradient with respect to the hot gas duct 20 and the cooling air duct 22. The sealing walls 30, 32 are rectilinear and extend from transition regions of the projections 16, 18 on the blade neck 6 in the direction of the blade root 2. Starting from the platform 14, the sealing walls 30, 32 obliquely to the vertical axis 34 of the blade 1 and employed on the Blade foot 2 or at its pointing in the direction of the platform 14 edge 36 merged. The sealing walls 30, 32 have approximately the same length and are employed at approximately the same angle to the vertical axis 34, so that the inner space 28 is almost symmetrical to the vertical axis 34 and the platform 14 with the sealing walls 30, 32 form an almost isosceles triangle. Thus, the interior space 28 has a triangular, in particular a triangular, cross-section which, viewed from the platform 14 in the direction of the blade root 2, narrows continuously or closes radially from outside to inside. Accordingly, the interior 28 widens funnel-shaped viewed from the blade root 2 in the direction of the platform 14 and opens radially from the inside to the outside. In particular, the sealing walls 30, 32 are brought together on the blade root 2 or on its edge 36 on the vertical axis 34.

Offenbart ist eine Laufschaufel für eine Strömungsmaschine mit einem Schaufelfuß, einem Schaufelblatt und mit einem zwischen dem Schaufelfuß und dem Schaufelblatt angeordneten Schaufelhals, der eine innere Plattform bildet, wobei der Schaufelhals eine vordere Dichtwand und eine hintere Dichtwand hat, die mit der Plattform einen dreieckartigen, bevorzugterweise einen dreieckigen, Innenraum begrenzen, der sich radial von außen nach innen betrachtet verengt, sowie eine Strömungsmaschine mit einer Vielzahl von derartigen Laufschaufeln.Disclosed is a blade for a turbomachine with a blade root, an airfoil and with a blade neck disposed between the blade root and the blade blade, which forms an inner platform, wherein the blade neck has a front sealing wall and a rear sealing wall, which is triangular with the platform, Preferably define a triangular, interior, which narrows radially from outside to inside, and a turbomachine with a plurality of such blades.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Laufschaufelblade
22
Schaufelfußblade
44
Schaufelblattairfoil
66
Schaufelhalsscoop-neck
88th
Rotornaberotor hub
1010
Drehachseaxis of rotation
1212
SicherungsblechLocking plate
1414
Plattformplatform
1616
vorderer Vorsprungfront projection
1818
hinterer Vorsprungrear projection
2020
HeißgaskanalHot gas duct
2222
KühlluftkanalCooling air duct
2424
AußendeckbandOuter shroud
2626
Trommelkörperdrum body
2828
Innenrauminner space
3030
vordere Dichtwandfront sealing wall
3232
hintere Dichtwandrear sealing wall
3434
Hochachsevertical axis
3636
Randedge

Claims (7)

  1. A rotor blade (1) for a flow machine, having a blade root (2), a blade leaf (4) and having a blade neck (6) that is arranged between the blade root (2) and the blade leaf (4) and forms an inner platform (14), wherein the blade neck (6) has a sealing wall (30) that is at the front when viewed in the direction of flow and a sealing wall (32) at the rear when viewed in the direction of flow, characterised in that the two sealing walls with the platform (14) delimit a triangular inner space (28) that tapers radially from the outside inwards.
  2. A rotor blade according to claim 1, wherein one of the sealing walls (30, 32) is offset on the blade-root side in the direction of the other sealing wall (32, 30).
  3. A rotor blade according to claim 1, wherein the sealing walls (30, 32) are offset on the blade-root side in the direction of the other respective sealing wall (32, 30).
  4. A rotor blade according to claim 3, wherein the sealing walls (30, 32) are brought together on the blade-root side on the vertical blade axis (39).
  5. A rotor blade according to claim 4, wherein the sealing walls (30, 32) are brought together at the blade root (2).
  6. A rotor blade according to one of the preceding claims, wherein the sealing walls (30, 32) are formed in a straight line.
  7. A flow machine having a plurality of rotor blades (1) according to one of the preceding claims.
EP20110190041 2011-11-22 2011-11-22 Rotor blade and flow machine Not-in-force EP2597266B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20110190041 EP2597266B1 (en) 2011-11-22 2011-11-22 Rotor blade and flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20110190041 EP2597266B1 (en) 2011-11-22 2011-11-22 Rotor blade and flow machine

Publications (2)

Publication Number Publication Date
EP2597266A1 EP2597266A1 (en) 2013-05-29
EP2597266B1 true EP2597266B1 (en) 2014-08-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20110190041 Not-in-force EP2597266B1 (en) 2011-11-22 2011-11-22 Rotor blade and flow machine

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EP (1) EP2597266B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
DE102008047492A1 (en) * 2008-09-17 2010-04-15 Mtu Aero Engines Gmbh Blade i.e. rotor blade, for e.g. turbine stage, has partial surface that is selected in blade longitudinal direction such that cooling channels to be formed in blade core are cut in longitudinal direction in middle axis of blade core
DE102009007664A1 (en) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Sealing device on the blade shank of a rotor stage of an axial flow machine

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Publication number Publication date
EP2597266A1 (en) 2013-05-29

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