EP3289182B1 - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
EP3289182B1
EP3289182B1 EP16733363.2A EP16733363A EP3289182B1 EP 3289182 B1 EP3289182 B1 EP 3289182B1 EP 16733363 A EP16733363 A EP 16733363A EP 3289182 B1 EP3289182 B1 EP 3289182B1
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EP
European Patent Office
Prior art keywords
blade
wall thickness
airfoil
transition
turbine blade
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.)
Active
Application number
EP16733363.2A
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German (de)
French (fr)
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EP3289182A1 (en
Inventor
Björn Buchholz
Ralph Gossilin
Daniela Koch
Marco Schüler
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Siemens Energy Global GmbH and Co KG
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Siemens AG
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Publication of EP3289182A1 publication Critical patent/EP3289182A1/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
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/301—Cross-sectional characteristics
    • 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

Definitions

  • the invention relates to a turbine blade according to the preamble of claim 1.
  • Hollow turbine blades in particular gas turbine blades, have a curvature on an outer surface that is necessary in terms of load and casting technology in the area of a transition from the airfoil to the platform flowable cooling medium there are difficult to cool.
  • Such turbine blades are for example from the US 6,019,579 and from the WO 2007/012592 known, the latter proposing to cool the mass accumulations by providing local cooling air channels.
  • the document also shows US 2,861,775 a turbine blade made from bent sheet metal.
  • a turbine blade with an extended lifespan is also out of the EP 1 355 041 A1 is known, the contour of the transition from the airfoil to the platform in the interior of the airfoil being adapted in order to obtain an airfoil wall thickness in the transition region which corresponds approximately to the wall thickness of the remaining airfoil.
  • the contour is adjusted along the entire closed circuit, i.e. along the platform.
  • the reduced wall thickness can have a negative effect on the life of the turbine blade, which is undesirable.
  • a turbine blade corresponding to the generic term, it is provided that in the area of the transition it has an inner surface delimiting a cavity, the contour of which is adapted in a first section of the inner surface in such a way that an essentially uniform blade wall thickness is present in the area of the transition, wherein in the transition the contour course of the inner surface on a second inner surface section of the airfoil, which lies opposite the front edge, is such that there the blade wall thickness is increased compared to the blade wall thickness of the transition of the first section of the inner surface.
  • the contour progression on an inner surface section of the airfoil opposite the front edge is such that there the blade wall thickness is increased compared to the airfoil wall thickness of the transition, away from the local inner surface section.
  • the turbine blade thus has a contour on the inside at the level of the platform which is different along the circumference of the cavity.
  • the inner contour of the cavity along a radial axis of a gas turbine equipped with it is rather straight and is flush with the inner surface which is opposite the front edge away from the transition.
  • the inner contour that avoids mass accumulation is thus only provided on those areas of the airfoil that can be found further downstream of the leading edge.
  • the second inner surface section preferably extends with increased blade wall thickness starting at the front edge of the airfoil along the suction side wall and / or the pressure side wall along the profile center line to a position which is equal to or less than 9% of the length of the profile center line.
  • the strength, in particular in the front edge area of the turbine blade, can be locally increased, which leads to an increased service life of the areas in question.
  • the platform has a platform wall thickness and the airfoil has a blade wall thickness beyond the transition, the ratio of the blade wall thickness to platform wall thickness being between 0.5 and 1 in the region with a substantially uniform blade wall thickness of the transition.
  • Such a turbine blade can be cooled particularly homogeneously, which reduces thermomechanical loads in the material of the turbine blade.
  • FIG. 1 shows a perspective view of a turbine blade 10.
  • the perspective is selected so that the top view of a fastening area 12 as the guide vane configured turbine blade 10 is shown.
  • FIG 2 is the longitudinal section through the turbine blade 10 according to the section line II-II FIG. 1 shown.
  • the turbine blade 10 has, in succession along a radial axis 14, the fastening region 12, an adjacent blade platform 16 and an airfoil 18.
  • a blade root 20 is formed, which serves to fasten the turbine blade 10 to a turbine guide vane carrier, not shown.
  • the invention is illustrated by way of example using a turbine blade designed as a guide blade with two platforms. Nevertheless, other configurations are possible, in particular the turbine blade can also be configured as a rotor blade of a turbine. At least the base body of the turbine blade is produced by a casting process and comprises at least the blade 18 and at least one platform 16.
  • the turbine blade 10 according to the invention and in particular its blade 18, is hollow on the inside, so that it comprises a cavity 25, which can be designed in a known manner as a cooling channel with or without impingement cooling.
  • the airfoil 18 extends from a front edge 28 to a rear edge 30.
  • the airfoil 18 includes an in FIG. 1 only schematically indicated suction-side vane wall 32 and a pressure-side vane wall 34.
  • the vane walls 32, 34 have a wall thickness D which is essentially constant.
  • transition 36 between the airfoil 18 and the platform 16, which is rounded on the outer surface of the turbine blade 10 and is therefore like a fillet.
  • the airfoil 18 has an inner surface opposite the outer surfaces. In the area of the suction-side blade wall 32, this is partially adapted to the outer contour of the transition, that is, along the radial axis 14 from a blade tip to the blade root, so that an essentially uniform blade wall thickness D1 is also present there in the transition 36.
  • the inner surface in the region of the transition 36 comprises a second inner surface section 40 opposite the front edge 28, the contour course of which is such that there the blade wall thickness (D 2 ) is increased compared to the blade wall thickness D 1 of the transition away from the second inner surface section 40.
  • the second inner surface section 40 is located only in the immediate vicinity of the front edge and forms a straight line with the inner surface of the remaining airfoil along the radial direction 14 or viewed in longitudinal section, whereas the remaining inner surface of the suction and / or pressure side in the transition, ie a first Inner surface portion 41 is curved while maintaining an approximately uniform blade wall thickness D 1 .
  • the second inner surface section 40 with the increased wall thickness D 2 is followed by the first inner surface section 41 with a wall thickness D 1 which corresponds to the wall thickness D of the airfoil.
  • the invention relates to a cast turbine blade 10 with a platform 16 and with a hollow airfoil 18 arranged thereon, the airfoil 18 comprising a pressure-side airfoil wall 34 and a suction-side airfoil wall 32 which are arranged centrally along one of them extend curved profile center line 42 from a common front edge 28 to a common rear edge 30 and with a transition 36 between the airfoil and platform 36 which has an outer contour, the airfoil walls 32, 34 each having a locally determined airfoil wall thickness D, the turbine blade inside Has contour course, which is partially adapted to the outer contour course of the transition 36 in such a way that an essentially uniform blade wall thickness is present in the region of the transition 36.
  • the contour profile on a second inner surface section 40 of the airfoil opposite the front edge 28 is such that the blade wall thickness is increased there compared to the blade wall thickness of the transition away from the front edge.

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

Description

Die Erfindung betrifft eine Turbinenschaufel gemäß dem Gattungsbegriff des Anspruchs 1.The invention relates to a turbine blade according to the preamble of claim 1.

Hohle Turbinenschaufeln, insbesondere Gasturbinenschaufeln, weisen im Bereich eines Übergangs vom Schaufelblatt zur Plattform eine belastungsmäßig und gusstechnisch notwendige Krümmung auf einer Außenoberfläche auf, wobei es in diesem hohlkehlartigen Übergang aufgrund einer geradlinigen Innengestalt der im Inneren vorgesehenen Kühlkanälen es lokal zu Massenanhäufungen kommt, die durch ein dort strömbares Kühlmedium schwerer kühlbar sind. Derartige Turbinenschaufeln sind beispielsweise aus der US 6,019,579 und aus der WO 2007/012592 bekannt, wobei letztere vorschlägt, die Masseanhäufungen durch Vorsehen von lokalen Kühlluftkanälen zu kühlen. Des Weiteren zeigt das Dokument US 2,861,775 eine aus gebogenen Blechen hergestellte Turbinenschaufel.Hollow turbine blades, in particular gas turbine blades, have a curvature on an outer surface that is necessary in terms of load and casting technology in the area of a transition from the airfoil to the platform flowable cooling medium there are difficult to cool. Such turbine blades are for example from the US 6,019,579 and from the WO 2007/012592 known, the latter proposing to cool the mass accumulations by providing local cooling air channels. The document also shows US 2,861,775 a turbine blade made from bent sheet metal.

Eine Turbinenschaufel mit einer verlängerten Lebensdauer ist zudem aus dem EP 1 355 041 A1 bekannt, wobei die Kontur des Übergangs vom Schaufelblatt zur Plattform im Schaufelinneren angepasst ist, um auch im Übergangbereich eine Schaufelblatt-Wandstärke zu erhalten, die in etwa der Wandstärke des restlichen Schaufelblatts entspricht. Dabei ist die Kontur entlang des gesamten, geschlossenen Umlaufs, also entlang der Plattform, angepasst. Die verringerte Wandstärke kann aus Festigkeitsgründen jedoch die Lebensdauer der Turbinenschaufel negativ beeinflussen, was unerwünscht ist.A turbine blade with an extended lifespan is also out of the EP 1 355 041 A1 is known, the contour of the transition from the airfoil to the platform in the interior of the airfoil being adapted in order to obtain an airfoil wall thickness in the transition region which corresponds approximately to the wall thickness of the remaining airfoil. The contour is adjusted along the entire closed circuit, i.e. along the platform. However, for reasons of strength, the reduced wall thickness can have a negative effect on the life of the turbine blade, which is undesirable.

Es ist daher Aufgabe der Erfindung, eine gegossene Turbinenschaufel aufzuzeigen, bei der der Übergangsbereich vom Schaufelblatt zur Plattform weiterhin hinreichend kühlbar ist unter Erreichung einer verlängerten Lebensdauer.It is therefore an object of the invention to show a cast turbine blade in which the transition area from the airfoil to the platform can still be adequately cooled while achieving an extended service life.

Die Aufgabe wird erfindungsgemäß durch eine Turbinenschaufel mit den im Anspruch 1 angegebenen Merkmalen gelöst. Vorteilhafte Ausgestaltungen sind in den abhängigen Ansprüchen wiedergegeben, deren Merkmale in beliebiger Weise miteinander kombiniert werden können.The object is achieved by a turbine blade with the features specified in claim 1. Advantageous embodiments are given in the dependent claims, the features of which can be combined with one another in any manner.

Erfindungsgemäß ist für eine dem Gattungsbegriff entsprechende Turbinenschaufel vorgesehen, dass sie im Bereich des Übergangs eine einen Hohlraum begrenzende Innenfläche aufweist, deren Kontur in einem ersten Abschnitt der Innenfläche in der Weise angepasst ist, dass im Bereich des Übergangs eine im Wesentlichen gleichmäßige Schaufelwanddicke vorhanden ist, wobei im Übergang der Konturverlauf der Innenfläche an einem zweiten Innenflächenabschnitt des Schaufelblatts, welcher der Vorderkante gegenüber liegt, dergestalt ist, dass dort die Schaufelwanddicke vergrößert ist, verglichen mit der Schaufelwanddicke des Übergangs des ersten Abschnitts der Innenfläche. Mit anderen Worten: im Übergang ist der Konturverlauf an einem der Vorderkante gegenüberliegenden Innenflächenabschnitt des Schaufelblatts dergestalt, dass dort die Schaufelwanddicke vergrößert ist, verglichen mit der Schaufelwanddicke des Übergangs, abseits des lokalen Innenflächenabschnitts.According to the invention, for a turbine blade corresponding to the generic term, it is provided that in the area of the transition it has an inner surface delimiting a cavity, the contour of which is adapted in a first section of the inner surface in such a way that an essentially uniform blade wall thickness is present in the area of the transition, wherein in the transition the contour course of the inner surface on a second inner surface section of the airfoil, which lies opposite the front edge, is such that there the blade wall thickness is increased compared to the blade wall thickness of the transition of the first section of the inner surface. In other words: in the transition, the contour progression on an inner surface section of the airfoil opposite the front edge is such that there the blade wall thickness is increased compared to the airfoil wall thickness of the transition, away from the local inner surface section.

Damit weist die Turbinenschaufel im Inneren auf Höhe der Plattform eine Kontur auf, die längs des Umlaufs des Hohlraums unterschiedlich ist. Im Bereich der Vorderkante ist die innere Kontur des Hohlraums entlang einer Radialachse einer damit ausgestatten Gasturbine eher geradlinig und fluchtet mit derjenigen Innenfläche, welcher der Vorderkante abseits des Übergangs gegenüber liegt. Damit ist die die Masseanhäufungen vermeidende innere Kontur lediglich an denjenigen Bereichen des Schaufelblatts vorgesehen, die weiter stromab der Vorderkante zu finden sind.The turbine blade thus has a contour on the inside at the level of the platform which is different along the circumference of the cavity. In the area of the front edge, the inner contour of the cavity along a radial axis of a gas turbine equipped with it is rather straight and is flush with the inner surface which is opposite the front edge away from the transition. The inner contour that avoids mass accumulation is thus only provided on those areas of the airfoil that can be found further downstream of the leading edge.

Vorzugsweise erstreckt sich der zweite Innenflächenabschnitt mit vergrößerter Schaufelwanddicke beginnend an der Vorderkante des Schaufelblatts entlang der Saugseitenwand und/oder der Druckseitenwand längs der Profilmittenlinie bis zu einer Position, die gleich oder geringer ist als 9 % der Länge der Profilmittenlinie.The second inner surface section preferably extends with increased blade wall thickness starting at the front edge of the airfoil along the suction side wall and / or the pressure side wall along the profile center line to a position which is equal to or less than 9% of the length of the profile center line.

Mit der Erfindung kann die Festigkeit, insbesondere im Vorderkantenbereich der Turbinenschaufel, lokal vergrößert werden, was zu einer erhöhten Lebensdauer der betreffenden Bereiche führt.With the invention, the strength, in particular in the front edge area of the turbine blade, can be locally increased, which leads to an increased service life of the areas in question.

Es hat sich dabei als besonders vorteilhaft herausgestellt, dass die Plattform eine Plattformwanddicke und das Schaufelblatt abseits des Übergangs eine Schaufelwanddicke aufweisen, wobei im Bereich mit im Wesentlichen gleichmäßiger Schaufelwanddicke des Übergangs, das Verhältnis von Schaufelwanddicke zu Plattformwanddicke zwischen 0,5 und 1 liegt.It has been found to be particularly advantageous that the platform has a platform wall thickness and the airfoil has a blade wall thickness beyond the transition, the ratio of the blade wall thickness to platform wall thickness being between 0.5 and 1 in the region with a substantially uniform blade wall thickness of the transition.

Eine derartige Turbinenschaufel lässt sich besonders homogen kühlen, was thermomechanische Belastungen im Material der Turbinenschaufel reduziert.Such a turbine blade can be cooled particularly homogeneously, which reduces thermomechanical loads in the material of the turbine blade.

Ausführungsbeispiele der Erfindung sind in den nachfolgenden Figuren dargestellt.Exemplary embodiments of the invention are shown in the following figures.

In allen Figuren sind identische Merkmale mit den gleichen Bezugszeichen versehen.Identical features are provided with the same reference symbols in all the figures.

Es zeigen:

FIG 1
eine Draufsicht auf den Fußbereich einer als Leitschaufel ausgestalteten Turbinenschaufel und
FIG 2
einen Längsschnitt durch die Turbinenschaufel gemäß FIG 1, entlang der Schnittlinie II-II.
Show it:
FIG. 1
a plan view of the foot region of a turbine blade designed as a guide blade and
FIG 2
a longitudinal section through the turbine blade according to FIG. 1 , along the section line II-II.

Die FIG 1 zeigt in perspektivischer Ansicht eine Turbinenschaufel 10. Die Perspektive ist so gewählt, dass die Draufsicht auf einen Befestigungsbereich 12 der als Leitschaufel ausgestalteten Turbinenschaufel 10 dargestellt ist. In FIG 2 ist der Längsschnitt durch die Turbinenschaufel 10 gemäß der Schnittlinie II-II aus FIG 1 gezeigt. Die Turbinenschaufel 10 weist entlang einer Radialachse 14 aufeinanderfolgend den Befestigungsbereich 12, eine daran angrenzende Schaufelplattform 16 sowie ein Schaufelblatt 18 auf. Im Befestigungsbereich 12 ist ein Schaufelfuß 20 ausgebildet, der zur Befestigung der Turbinenschaufel 10 an einem nicht dargestellten Turbinenleitschaufelträger dient.The FIG. 1 shows a perspective view of a turbine blade 10. The perspective is selected so that the top view of a fastening area 12 as the guide vane configured turbine blade 10 is shown. In FIG 2 is the longitudinal section through the turbine blade 10 according to the section line II-II FIG. 1 shown. The turbine blade 10 has, in succession along a radial axis 14, the fastening region 12, an adjacent blade platform 16 and an airfoil 18. In the fastening area 12, a blade root 20 is formed, which serves to fasten the turbine blade 10 to a turbine guide vane carrier, not shown.

Die Darstellung der Erfindung erfolgt beispielhaft anhand einer als Leitschaufel mit zwei Plattformen ausgestalteten Turbinenschaufel. Nichts desto trotz sind andere Ausgestaltungen möglich, insbesondere kann die Turbinenschaufel auch als Laufschaufel einer Turbine ausgestaltet sein. Zumindest der Grundkörper der Turbinenschaufel ist durch ein Gussverfahren hergestellt und umfasst wenigstens das Schaufelblatt 18, sowie wenigstens eine Plattform 16.The invention is illustrated by way of example using a turbine blade designed as a guide blade with two platforms. Nevertheless, other configurations are possible, in particular the turbine blade can also be configured as a rotor blade of a turbine. At least the base body of the turbine blade is produced by a casting process and comprises at least the blade 18 and at least one platform 16.

Wie aus den Figuren hervorgeht, ist die erfindungsgemäße Turbinenschaufel 10 und insbesondere deren Schaufelblatt 18 im Inneren hohl ausgeführt, so dass sie einen Hohlraum 25 umfasst, der in bekannter Art und Weise als Kühlkanal mit oder ohne Prallkühlung ausgestaltet sein kann.As can be seen from the figures, the turbine blade 10 according to the invention, and in particular its blade 18, is hollow on the inside, so that it comprises a cavity 25, which can be designed in a known manner as a cooling channel with or without impingement cooling.

Das Schaufelblatt 18 erstreckt sich von einer Vorderkante 28 zu einer Hinterkante 30. Dabei umfasst das Schaufelblatt 18 eine in FIG 1 nur schematisch angedeutete saugseitige Schaufelwand 32 sowie eine druckseitige Schaufelwand 34. Entlang der Radialrichtung 14 weisen die Schaufelwände 32, 34 eine Wanddicke D auf, die im Wesentlichen gleichbleibend ist.The airfoil 18 extends from a front edge 28 to a rear edge 30. The airfoil 18 includes an in FIG. 1 only schematically indicated suction-side vane wall 32 and a pressure-side vane wall 34. Along the radial direction 14, the vane walls 32, 34 have a wall thickness D which is essentially constant.

Fertigungsbedingt besteht zwischen dem Schaufelblatt 18 und der Plattform 16 ein Übergang 36, der auf der äußeren Oberfläche der Turbinenschaufel 10 abgerundet und somit hohlkehlartig ist.Due to manufacturing, there is a transition 36 between the airfoil 18 and the platform 16, which is rounded on the outer surface of the turbine blade 10 and is therefore like a fillet.

Im Inneren weist das Schaufelblatt 18 eine den äußeren Flächen gegenüber liegende Innenfläche auf. Diese ist im Bereich der saugseitigen Schaufelwand 32 dergestalt, dass sie teilweise dem äußeren Konturverlauf des Übergangs, also längs der Radialachse 14 von einer Schaufelspitze zum Schaufelfuß, angepasst ist, so dass auch dort im Übergang 36 eine im Wesentlichen gleichmäßige Schaufelwanddicke D1 vorhanden ist.Inside, the airfoil 18 has an inner surface opposite the outer surfaces. In the area of the suction-side blade wall 32, this is partially adapted to the outer contour of the transition, that is, along the radial axis 14 from a blade tip to the blade root, so that an essentially uniform blade wall thickness D1 is also present there in the transition 36.

Die Innenfläche im Bereich des Übergangs 36 umfasst einen der Vorderkante 28 gegenüberliegenden zweiten Innenflächenabschnitt 40, dessen Konturverlauf derartig ist, dass dort die Schaufelwanddicke (D2) vergrößert ist, verglichen mit der Schaufelwanddicke D1 des Übergangs abseits des zweiten Innenflächenabschnitts 40. Mit anderen Worten: der zweite Innenflächenabschnitt 40 ist lediglich in der unmittelbaren Umgebung der Vorderkante angesiedelt und bildet mit Innenfläche des restlichen Schaufelblatts längs der Radialrichtung 14 bzw. im Längsschnitt betrachtet eine Gerade, wohingegen die restliche Innenfläche der Saug- und/oder Druckseite im Übergang, d.h. ein erster Innenflächenabschnitt 41 unter Beibehaltung einer annähernd gleichmäßigen Schaufelwanddicke D1 gekrümmt ist. Mithin folgt ausgehend von der Vorderkante 28 längs des Übergangs 36 dem zweiten Innenflächenabschnitt 40 mit der vergrößerten Wandstärke D2 der erste Innenflächenabschnitt 41 mit einer Wandstärke D1, die der Wandstärke D des Schaufelblatts entspricht.The inner surface in the region of the transition 36 comprises a second inner surface section 40 opposite the front edge 28, the contour course of which is such that there the blade wall thickness (D 2 ) is increased compared to the blade wall thickness D 1 of the transition away from the second inner surface section 40. In other words : the second inner surface section 40 is located only in the immediate vicinity of the front edge and forms a straight line with the inner surface of the remaining airfoil along the radial direction 14 or viewed in longitudinal section, whereas the remaining inner surface of the suction and / or pressure side in the transition, ie a first Inner surface portion 41 is curved while maintaining an approximately uniform blade wall thickness D 1 . Thus, starting from the front edge 28 along the transition 36, the second inner surface section 40 with the increased wall thickness D 2 is followed by the first inner surface section 41 with a wall thickness D 1 which corresponds to the wall thickness D of the airfoil.

Hierdurch kann ein im Bereich der Vorderkante 28 aufgedickter Übergangsbereich einer Turbinenschaufel 10 bereit gestellt werden, der eine größere Steifigkeit aufweist als im restlichen Bereich. Dies kann die Lebensdauer der Turbinenschaufel 10 verbessern.In this way, a transition region of a turbine blade 10 which is thickened in the region of the front edge 28 and which has a greater rigidity than in the rest of the region. This can improve the life of the turbine blade 10.

Insgesamt betrifft die Erfindung eine gegossene Turbinenschaufel 10 mit einer Plattform 16 und mit einem daran angeordneten hohlen Schaufelblatt 18, wobei das Schaufelblatt 18 eine druckseitige Schaufelwand 34 und eine saugseitige Schaufelwand 32 umfasst, die sich längs einer mittig davon angeordneten gewölbten Profilmittenlinie 42 von einer gemeinsamen Vorderkante 28 zu einer gemeinsamen Hinterkante 30 erstrecken sowie mit einem einen äußeren Konturverlauf aufweisenden Übergang 36 zwischen Schaufelblatt und Plattform 36, wobei die Schaufelwände 32, 34 jeweils eine lokal zu erfassende Schaufelwanddicke D aufweisen, wobei die Turbinenschaufel im Inneren einen Konturverlauf aufweist, welcher teilweise dem äußeren Konturverlauf des Übergangs 36 in der Weise angepasst ist, dass im Bereich des Übergangs 36 eine im Wesentlichen gleichmäßige Schaufelwanddicke vorhanden ist. Um die Lebensdauer einer derartigen Turbinenschaufel weiter zu verbessern ist vorgesehen, dass im Übergang 36 der Konturverlauf an einem der Vorderkante 28 gegenüberliegenden zweiten Innenflächenabschnitt 40 des Schaufelblatts dergestalt ist, dass dort die Schaufelwanddicke vergrößert ist, verglichen mit der Schaufelwanddicke des Übergangs abseits der Vorderkante.Overall, the invention relates to a cast turbine blade 10 with a platform 16 and with a hollow airfoil 18 arranged thereon, the airfoil 18 comprising a pressure-side airfoil wall 34 and a suction-side airfoil wall 32 which are arranged centrally along one of them extend curved profile center line 42 from a common front edge 28 to a common rear edge 30 and with a transition 36 between the airfoil and platform 36 which has an outer contour, the airfoil walls 32, 34 each having a locally determined airfoil wall thickness D, the turbine blade inside Has contour course, which is partially adapted to the outer contour course of the transition 36 in such a way that an essentially uniform blade wall thickness is present in the region of the transition 36. In order to further improve the service life of such a turbine blade, it is provided that in the transition 36 the contour profile on a second inner surface section 40 of the airfoil opposite the front edge 28 is such that the blade wall thickness is increased there compared to the blade wall thickness of the transition away from the front edge.

Claims (5)

  1. Cast, hollow turbine blade (10),
    having a platform and having a hollow blade airfoil arranged thereon, wherein the blade airfoil (18) comprises a pressure-side blade airfoil wall (34) and a suction-side blade airfoil wall (32) which extend along a centrally arranged curved profile centerline (42) from a common leading edge (28) to a common trailing edge (30), and having a transition (36), exhibiting an external contour profile, between the blade airfoil (18) and the platform (16),
    wherein the blade walls (32, 34) each have a blade wall thickness (D) to be determined locally,
    wherein the turbine blade (10) has, in the region of the transition (36), an inner face bounding a cavity, the contour of said inner face being adapted to the inner face in a first portion (41) in such a way that there is a substantially uniform blade wall thickness (D1) in the region of the transition (36),
    characterized in that,
    in the transition (36), the contour profile of the inner face on a second inner-face portion (40), located opposite the leading edge (28), of the blade airfoil (18) is such that the blade wall thickness (D2) is increased there compared with the blade wall thickness (D1) of the transition (36) of the first portion (41) of the inner face.
  2. Turbine blade (10) according to Claim 1,
    in which the contour profile in the second inner-face portion (40) is rectilinear along a radial axis (14).
  3. Turbine blade (10) according to Claim 1 or 2,
    in which the platform has a platform wall thickness (D3) and the blade airfoil (18), away from the second inner-face portion (40), has a blade wall thickness (D), wherein, in the region with a substantially uniform blade wall thickness, the ratio (D/D3) of blade wall thickness (D) to platform wall thickness (D3) is between 0.5 and 1.
  4. Turbine blade (10) according to Claim 1, 2 or 3,
    in which the second inner-face portion (40) with an increased blade wall thickness (D2) extends from the leading edge (28) along the suction-side wall (32) and/or along the pressure-side wall (34), along the profile centerline (42), to a position which is less than 15% of the length of the profile centerline (42).
  5. Turbine blade according to one of Claims 1 to 4,
    which is configured as a turbine guide vane.
EP16733363.2A 2015-07-03 2016-06-21 Turbine blade Active EP3289182B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15175301.9A EP3112589A1 (en) 2015-07-03 2015-07-03 Turbine blade
PCT/EP2016/064274 WO2017005484A1 (en) 2015-07-03 2016-06-21 Turbine blade

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EP3289182B1 true EP3289182B1 (en) 2020-03-25

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EP16733363.2A Active EP3289182B1 (en) 2015-07-03 2016-06-21 Turbine blade

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EP (2) EP3112589A1 (en)
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Publication number Publication date
EP3112589A1 (en) 2017-01-04
US10301944B2 (en) 2019-05-28
WO2017005484A1 (en) 2017-01-12
CN107735548B (en) 2019-07-12
US20180187551A1 (en) 2018-07-05
CN107735548A (en) 2018-02-23
EP3289182A1 (en) 2018-03-07
JP6469897B2 (en) 2019-02-13
JP2018524511A (en) 2018-08-30

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