EP2831376B1 - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
EP2831376B1
EP2831376B1 EP13712793.2A EP13712793A EP2831376B1 EP 2831376 B1 EP2831376 B1 EP 2831376B1 EP 13712793 A EP13712793 A EP 13712793A EP 2831376 B1 EP2831376 B1 EP 2831376B1
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EP
European Patent Office
Prior art keywords
turbine blade
platform
elements
platform elements
blade according
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
EP13712793.2A
Other languages
German (de)
French (fr)
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EP2831376A1 (en
Inventor
Herbert Brandl
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.)
Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Priority to EP13712793.2A priority Critical patent/EP2831376B1/en
Publication of EP2831376A1 publication Critical patent/EP2831376A1/en
Application granted granted Critical
Publication of EP2831376B1 publication Critical patent/EP2831376B1/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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/57—Seals
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/31—Retaining bolts or nuts
    • 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

Definitions

  • the present invention relates to the field of turbomachines. It relates to a turbine blade according to the preamble of claim 1, as it is used as a guide or blade, especially in gas turbines.
  • Blades for gas turbines which are used in the compressor or turbine part as guide or moving blades, are usually produced as a part by forging or investment casting. This also applies in particular to blades which have a platform and / or a shroud segment.
  • the turbine blade according to the invention comprises an airfoil having a front edge and a trailing edge, which merges via a shank into a blade root designed for fastening the turbine blade, and a platform which is arranged at the lower end of the airfoil for delimiting a flow channel, the platform being separate Component is formed and positively connected to the airfoil. It is characterized by the fact that the platform is composed of several individual platform elements, which in the assembled state enclose the airfoil. Due to the composite design of the platform, it is possible to attach these directly to a blade, so that adjustments in the field of blade attachment can be avoided.
  • the platform is composed of two platform elements.
  • Another embodiment of the invention is characterized in that the two platform elements abut in the assembled state with connecting surfaces in a parting plane which extends from the leading edge and the trailing edge of the airfoil in the axial direction to the associated edge of the platform.
  • the platform elements are each provided with outgoing from the parting plane recesses, which form in the assembled state adapted to the profile of the airfoil opening for the passing through the platform airfoil.
  • the platform is sealed to the airfoil.
  • a circumferential sealing groove is introduced into the platform elements for sealing against the airfoil along the opening, which receives a suitable seal.
  • the two platform elements are sealed against each other in the parting plane.
  • a sealing groove is provided for sealing in the parting plane, which receives a matched seal.
  • a further embodiment of the invention is characterized in that the two platform elements are detachably connected to each other.
  • the two platform elements can be screwed or riveted together.
  • aligned on the two platform elements parallel to the parting plane and abutting in the parting plane flange portions are formed, through which the two platform elements are screwed or riveted together.
  • the two platform elements are locked together by locking means.
  • the platform elements in the assembled state overlap each other with overlapping sections, wherein in the overlapping area between the overlapping sections a locking channel is formed, and the locking channel is filled with a filling.
  • the platform is attached to the turbine blade.
  • the platform is hooked to the turbine blade.
  • the platform or the platform elements are equipped with hooks with which they are hooked into a groove in the region of the shaft of the turbine blade (are).
  • the platform or the platform elements may be materially connected to the turbine blade.
  • the platform or platform elements are connected by means of a cast into a locking channel filling with the turbine blade such that the connection surfaces of a portion of the turbine blade and the platform or platform elements are equipped with opposing recesses, which together form a cavity, the is suitable to be filled with a solidifying filler, for example.
  • a solidifying filler for example.
  • FIG. 2 is a perspective view of a turbine blade with a platform according to an embodiment of the invention reproduced.
  • the turbine blade 10 which may be, for example, a blade or vane of a gas turbine, comprises an airfoil 11 which terminates at the top in a blade tip 12 and has a leading edge 13 and a trailing edge 14.
  • the blade 11 goes down to a shaft 15, to which a blade root 16 adjoins, which is formed fir-tree-like manner in a conventional manner to be used in a corresponding receptacle on the rotor.
  • the blade 11 is enclosed at its lower end by a platform 17, according to Fig. 1 is composed of two separate platform elements 17a and 17b in a parting plane 19, wherein the two platform elements 17a, b abut one another with corresponding connection surfaces 19a and 19b ( Fig. 1 ).
  • the composite platform 17 form an opening 18 through which the airfoil 11 can extend ( Fig. 2 ).
  • the dividing plane 19 extends on both sides of the airfoil 11 in the axial direction from the front edge 13 to the front edge of the platform 17 and from the trailing edge 14 to the rear edge of the platform 17th
  • Fig. 3 shows, by way of example, the fastening of the platform elements 17a, b on the blade 11 and the corresponding seal between the platform elements 17a, b and the blade 11.
  • hooks 23 are formed on the side of the platform elements 17a, b facing the blade 11, with which the platform elements 17a, b engage in a corresponding groove 22 on the shank 15 of the blade.
  • the blade root 16 remains free of any impairments by the platform 17.
  • a circumferential sealing groove 20 is provided in the platform elements 17a, b at the edge 18 facing edge, which receives a matched seal 21.
  • Fig. 4 shows an example of a screw connection of the two elements.
  • a connecting element 26 in particular in the form of a bolt
  • a rivet instead of the bolt can also be used a rivet.
  • a seal between the platform elements 17a, b are provided in the parting plane 19, a seal between the platform elements 17a, b are provided.
  • a sealing groove 24 is formed in the parting plane 19, which receives a matched seal 25.
  • connection between the platform elements 17a, b but also cohesively by means of welding or soldering done.
  • FIG. 5 Another possibility of the connection between the platform elements 17a, b is in Fig. 5 shown a special type of locking, known under the keyword "bi-cast" and for example in the publication US 5,797,725 is described.
  • the two platform elements 17a, b overlap with corresponding overlapping sections 28a and 28b, wherein in the overlapping area a locking channel 29 is formed, which is poured out after the joining of the platform elements 17a, b with a metallic filling 30, then a relative movement between the overlapping sections 28a, b safely prevented.
  • Fig. 5 (b) makes clear, laterally protruding lugs of the filling 30 can be provided in the locking channel 29 to prevent slipping out of the filling 30 in the longitudinal direction of the connecting channel 29.
  • Fig. 6 shows, alternatively to that of Fig. 3 , Another embodiment of the attachment of the platform elements 17a, b on the blade 11, which combines the functions of mechanical fastening and sealing together.
  • a cohesive connection of these components occurs by means of a solidifying filling 30, which can be poured into a locking channel 29 formed between the turbine blade components to be connected between them.
  • the facing surfaces of the recess 18 of the platform elements 17a, b and the blade 11 and the shaft 15 of the turbine blade 10 are provided with opposing grooves for introducing a pourable filling 30, in particular a molten metal.
  • a filling material is to be selected which remains under the conditions of the intended use of the turbine blade 10 in a solid state and undergoes no thermal damage. If the locking channel 29 is continuously designed so that it forms a closed ring around the blade 11 or the shaft 15 of the turbine blade 10 around, then this compound fulfills the dual function of attachment and sealing, since such a compound is naturally sufficiently fluid-tight. The requirement for an additional seal between the blade 11 or shaft 15 and platform 17 is thus eliminated.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Strömungsmaschinen. Sie betrifft eine Turbinenschaufel gemäss dem Oberbegriff des Anspruchs 1, wie sie als Leit- oder Laufschaufel insbesondere in Gasturbinen eingesetzt wird.The present invention relates to the field of turbomachines. It relates to a turbine blade according to the preamble of claim 1, as it is used as a guide or blade, especially in gas turbines.

STAND DER TECHNIKSTATE OF THE ART

Schaufeln für Gasturbinen, die im Kompressor- oder Turbinenteil als Leit- oder Laufschaufeln eingesetzt werden, werden üblicherweise als ein Teil durch Schmieden oder Feingiessen hergestellt. Dies gilt insbesondere auch für Schaufeln, die eine Plattform und/oder ein Deckbandsegment aufweisen.Blades for gas turbines, which are used in the compressor or turbine part as guide or moving blades, are usually produced as a part by forging or investment casting. This also applies in particular to blades which have a platform and / or a shroud segment.

Durch die immer weiter vorangetriebene Anhebung der Heissgastemperatur und die Verringerung des Kühlluftverbrauchs wird die Belastung von Leit- und
Laufschaufeln in der Gasturbine erhöht. Es ist daher wünschenswert, an den Schaufeln auftretende Spannungen durch konstruktive Massnahmen zu verringern. Bei gleicher Lebensdauer können Bauteile mit reduzierter Spannung höhere Temperaturen ertragen. Auf diese Weise kann der Forderung nach höherer Heissgastemperatur und geringerem Kühlluftverbrauch Rechnung getragen werden.Due to the ever-advancing increase in the hot-gas temperature and the reduction in the consumption of cooling air, the burden of control and
Blades in the gas turbine increased. It is therefore desirable to reduce stresses on the blades by constructive measures. For the same service life, components with reduced voltage can withstand higher temperatures. In this way, the demand for higher hot gas temperature and lower cooling air consumption can be taken into account.

Aus der Druckschrift EP 2 189 626 A1 ist eine Laufschaufelanordnung für eine Gasturbine bekannt, welche Laufschaufelanordnung an einem Schaufelträger befestigbar ist und jeweils ein Schaufelblattelement und ein Plattformelement umfasst, wobei die Plattformelemente einer Schaufelreihe ein durchgehendes inneres Deckband bilden. Eine reduzierte Spannung wird dort dadurch erreicht, dass Schaufelblattelement und Plattformelement als separate Elemente ausgebildet sind und jeweils für sich am Schaufelträger befestigbar sind. Nachteilig ist bei dieser Lösung, dass sie für Retrofit-Aufgaben nicht geeignet ist, weil sich durch das Plattformelement die Art der Befestigung am Rotor ändert, so dass der Rotor selbst angepasst werden muss.From the publication EP 2 189 626 A1 a blade assembly for a gas turbine is known, which blade assembly is attachable to a blade carrier and each comprising an airfoil element and a platform element, wherein the platform elements of a row of blades form a continuous inner shroud. A reduced voltage is achieved there by the fact that the airfoil element and platform element are formed as separate elements and are each fastened to the blade carrier. The disadvantage of this solution is that it is not suitable for retrofit tasks because the type of attachment to the rotor changes due to the platform element, so that the rotor itself has to be adapted.

Aus der Druckschrift US 7,762,781 B1 ist eine Anordnung aus Turbinenschaufel und Plattform bekannt, bei der die Plattform als separates Element ausgebildet ist, das durch spezielle Stifte an der Schaufel befestigt wird. Diese Lösung hat den Nachteil, dass die einzelnen Elemente in der Herstellung sehr aufwändig sind.From the publication US Pat. No. 7,762,781 B1 For example, an arrangement of turbine blade and platform is known in which the platform is formed as a separate element that is attached to the blade by special pins. This solution has the disadvantage that the individual elements in the production are very expensive.

Aus den Druckschriften US 4, 650,399 B1 und US 4, 583, 914 B1 ist eine Anordnung aus Turbinenschaufel und Plattform bekannt, bei der die Plattform zweiteilig ausgebildet ist und die beiden Teile der Plattform mittels einer formschlüssigen Nut- und Federverbindung am Fuß der Turbinenschaufel positiniert werden.From the pamphlets US 4, 650,399 B1 and US 4, 583, 914 B1 an arrangement of turbine blade and platform is known in which the platform is formed in two parts and the two parts of the platform are positively positioned by means of a positive tongue and groove connection at the bottom of the turbine blade.

Aus den Druckschriften US 7, 972,113 B1 und US 2001/0142684 A1 ist eine Anordnung aus Turbinenschaufel und Plattform bekannt, bei der die Plattform zweiteilig ausgebildet ist und die beiden Teile der Plattform einen Fuß der Turbinenschaufel formschlüssig aufnehmen.From the pamphlets US Pat. No. 7,972,113 B1 and US 2001/0142684 A1 an assembly of turbine blade and platform is known in which the platform is formed in two parts and the two parts of the platform receive a foot of the turbine blade form-fitting.

Aus den Druckschriften EP 1 992 787 A1 und US 2, 825, 539 B ist eine Anordnung aus Turbinenschaufel und Plattform bekannt, bei der die Plattform zweiteilig ausgebildet ist. Die beiden Teile der Plattform werden formschlüssig in einer tannenbaumförmigen Nut des Rotors aufgenommen.From the pamphlets EP 1 992 787 A1 and US Pat. No. 2,825,539 B An arrangement of turbine blade and platform is known in which the platform is formed in two parts. The two parts of the platform are positively received in a fir tree-shaped groove of the rotor.

Aus der EP 1 882 814 A1 ist eine Anordnung aus Turbinenschaufel und zwei Plattformen bekannt. Die beiden Teile der Plattform sind so gestaltet, dass sie zwischen zwei benachbarten Turbinenschaufeln passen. Dadurch wird die Zahl der Fugen zwischen den Plattformen reduziert.From the EP 1 882 814 A1 is known an arrangement of turbine blade and two platforms. The two parts of the platform are designed to fit between two adjacent turbine blades. This reduces the number of joints between the platforms.

Aus der US 2007/0189901 A1 ist eine Anordnung aus Turbinenschaufel und zwei Plattformen bekannt, bei der ein Übergang zwischen Plattform und Turbinenschaufel so ausgebildet ist, dass dort Kühlluft ausströmen kann.From the US 2007/0189901 A1 is known an arrangement of turbine blade and two platforms, in which a transition between the platform and the turbine blade is formed so that there cooling air can flow out.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist eine Aufgabe der Erfindung, eine Turbinenschaufel anzugeben, welche die Nachteile bekannter Turbinenschaufeln vermeidet und sich dadurch auszeichnet dass eine separate Plattform eingesetzt wird, die ohne Änderung auf der Befestigungsseite am Rotor angebracht werden kann.It is an object of the invention to provide a turbine blade, which avoids the disadvantages of known turbine blades and is characterized in that a separate platform is used, which can be mounted without modification on the mounting side of the rotor.

Diese und andere Aufgaben werden durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst.These and other objects are achieved by the entirety of the features of claim 1.

Die erfindungsgemässe Turbinenschaufel umfasst ein Schaufelblatt mit einer Vorderkante und einer Hinterkante, welches über einen Schaft in einen für die Befestigung der Turbinenschaufel ausgebildeten Schaufelfuss übergeht, sowie eine Plattform, welche am unteren Ende des Schaufelblattes zur Begrenzung eines Strömungskanals angeordnet ist, wobei die Plattform als separates Bauelement ausgebildet und mit dem Schaufelblatt formschlüssig verbindbar ist. Sie zeichnet sich dadurch aus, dass die Plattform aus mehreren einzelnen Plattformelementen zusammengesetzt ist, welche im zusammengesetzten Zustand das Schaufelblatt umschliessen. Durch die zusammengesetzte Ausbildung der Plattform ist es möglich, diese direkt an einer Schaufel zu befestigen, so dass Anpassungen im Bereich der Schaufelbefestigung vermieden werden können.The turbine blade according to the invention comprises an airfoil having a front edge and a trailing edge, which merges via a shank into a blade root designed for fastening the turbine blade, and a platform which is arranged at the lower end of the airfoil for delimiting a flow channel, the platform being separate Component is formed and positively connected to the airfoil. It is characterized by the fact that the platform is composed of several individual platform elements, which in the assembled state enclose the airfoil. Due to the composite design of the platform, it is possible to attach these directly to a blade, so that adjustments in the field of blade attachment can be avoided.

Gemäss einer Ausgestaltung der Erfindung ist die Plattform aus zwei Plattformelementen zusammengesetzt.According to one embodiment of the invention, the platform is composed of two platform elements.

Eine andere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die beiden Plattformelemente im zusammengesetzten Zustand mit Anschlussflächen in einer Trennebene aneinander stossen, die sich von der Vorderkante bzw. der Hinterkante des Schaufelblattes in axialer Richtung zur zugehörigen Kante der Plattform erstreckt.Another embodiment of the invention is characterized in that the two platform elements abut in the assembled state with connecting surfaces in a parting plane which extends from the leading edge and the trailing edge of the airfoil in the axial direction to the associated edge of the platform.

Insbesondere sind die Plattformelemente jeweils mit von der Trennebene ausgehenden Ausnehmungen versehen, die im zusammengesetzten Zustand eine an das Profil des Schaufelblattes angepasste Öffnung für das durch die Plattform hindurchgehende Schaufelblatt bilden.In particular, the platform elements are each provided with outgoing from the parting plane recesses, which form in the assembled state adapted to the profile of the airfoil opening for the passing through the platform airfoil.

Vorzugsweise ist die Plattform zum Schaufelblatt hin abgedichtet.Preferably, the platform is sealed to the airfoil.

Insbesondere ist zur Abdichtung gegenüber dem Schaufelblatt entlang der Öffnung eine umlaufende Dichtungsnut in die Plattformelemente eingebracht, welche eine passende Dichtung aufnimmt.In particular, a circumferential sealing groove is introduced into the platform elements for sealing against the airfoil along the opening, which receives a suitable seal.

Gemäss einer anderen Ausgestaltung der Erfindung sind die beiden Plattformelemente in der Trennebene gegeneinander abgedichtet.According to another embodiment of the invention, the two platform elements are sealed against each other in the parting plane.

Insbesondere ist zur Abdichtung in der Trennebene eine Dichtungsnut vorgesehen, welche eine angepasste Dichtung aufnimmt.In particular, a sealing groove is provided for sealing in the parting plane, which receives a matched seal.

Eine weitere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die beiden Plattformelemente lösbar miteinander verbunden sind.A further embodiment of the invention is characterized in that the two platform elements are detachably connected to each other.

Insbesondere können die beiden Plattformelemente miteinander verschraubt oder vernietet sein.In particular, the two platform elements can be screwed or riveted together.

Vorzugsweise sind an den beiden Plattformelementen parallel zur Trennebene ausgerichtete und in der Trennebene aneinander stossende Flanschabschnitte ausgebildet, durch welche hindurch die beiden Plattformelemente miteinander verschraubt oder vernietet sind.Preferably, aligned on the two platform elements parallel to the parting plane and abutting in the parting plane flange portions are formed, through which the two platform elements are screwed or riveted together.

Gemäss einer weiteren Ausgestaltung der Erfindung sind die beiden Plattformelemente durch Verriegelungsmittel miteinander verriegelt.According to a further embodiment of the invention, the two platform elements are locked together by locking means.

Insbesondere überlappen die Plattformelemente im zusammengesetzten Zustand einander mit Überlappungsabschnitten, wobei im Überlappungsbereich zwischen den Überlappungsabschnitten ein Verriegelungskanal ausgebildet ist, und der Verriegelungskanal mit einer Füllung ausgegossen ist.In particular, the platform elements in the assembled state overlap each other with overlapping sections, wherein in the overlapping area between the overlapping sections a locking channel is formed, and the locking channel is filled with a filling.

Gemäss einer weiteren Ausgestaltung der Erfindung ist die Plattform an der Turbinenschaufel befestigt.According to a further embodiment of the invention, the platform is attached to the turbine blade.

Insbesondere ist die Plattform an der Turbinenschaufel eingehakt.In particular, the platform is hooked to the turbine blade.

Vorzugsweise sind die Plattform bzw. die Plattformelemente mit Haken ausgestattet, mit welchen sie in eine Nut im Bereich des Schaftes der Turbinenschaufel eingehakt ist (sind).Preferably, the platform or the platform elements are equipped with hooks with which they are hooked into a groove in the region of the shaft of the turbine blade (are).

Alternativ können die Plattform bzw. die Plattformelemente stoffschlüssig mit der Turbinenschaufel verbunden sein.Alternatively, the platform or the platform elements may be materially connected to the turbine blade.

Gemäss einer besonders bevorzugten Variante sind die Plattform bzw. Plattformelemente mittels einer in einen Verriegelungskanal eingegossenen Füllung mit der Turbinenschaufel verbunden dergestalt, dass die Anschlussflächen eines Abschnitts der Turbinenschaufel und der Plattform bzw. Plattformelemente mit gegenüberliegenden Ausnehmungen ausgestattet sind, welche gemeinsam einen Hohlraum ausbilden, der geeignet ist, mit einem sich verfestigenden Füllmittel, bspw. einer Metallschmelze, ausgefüllt zu werden.According to a particularly preferred variant, the platform or platform elements are connected by means of a cast into a locking channel filling with the turbine blade such that the connection surfaces of a portion of the turbine blade and the platform or platform elements are equipped with opposing recesses, which together form a cavity, the is suitable to be filled with a solidifying filler, for example. A molten metal.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

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

Fig. 1
in einer perspektivischen Ansicht eine aus zwei einzelnen Elementen zusammensetzbare Plattform gemäss einem Ausführungsbeispiel der Erfindung;
Fig. 2
in einer perspektivischen Ansicht eine Turbinenschaufel mit einer Plattform gemäss Fig. 1;
Fig. 3
in einer Schnittansicht die Abdichtung eines Plattformelements gegen das Schaufelblatt in der Anordnung gemäss Fig. 2;
Fig. 4
in der Seitenansicht (a) und der Draufsicht von oben (b) ein Ausführungsbeispiel für eine verschraubte Plattform nach der Erfindung;
Fig. 5
in der Seitenansicht (a) und der Draufsicht von oben (b) ein Ausführungsbeispiel für eine verriegelte Plattform nach der Erfindung und
Fig. 6
eine alternative Ausführungsform der Befestigung und Abdichtung eines Plattformelements gegen das Schaufelblatt in der Anordnung gemäss Fig. 2.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
in a perspective view of a composite of two individual elements platform according to an embodiment of the invention;
Fig. 2
in a perspective view of a turbine blade with a platform according to Fig. 1 ;
Fig. 3
in a sectional view, the sealing of a platform element against the airfoil in the arrangement according to Fig. 2 ;
Fig. 4
in the side view (a) and the top view from above (b) an embodiment of a bolted platform according to the invention;
Fig. 5
in the side view (a) and the top view from above (b) an embodiment of a locked platform according to the invention and
Fig. 6
an alternative embodiment of the attachment and sealing of a platform element against the airfoil in the arrangement according to Fig. 2 ,

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

In Fig. 2 ist in einer perspektivischen Ansicht eine Turbinenschaufel mit einer Plattform gemäss einem Ausführungsbeispiel der Erfindung wiedergegeben. Die Turbinenschaufel 10, die beispielsweise eine Laufschaufel oder Leitschaufel einer Gasturbine sein kann, umfasst ein Schaufelblatt 11, welches oben in einer Schaufelspitze 12 endet und eine Vorderkante 13 und eine Hinterkante 14 aufweist. Das Schaufelblatt 11 geht nach unten zu in einen Schaft 15 über, an den sich ein Schaufelfuss 16 anschliesst, der in an sich bekannter Weise tannenbaumartig ausgebildet ist, um in eine entsprechende Aufnahme am Rotor eingesetzt zu werden.In Fig. 2 is a perspective view of a turbine blade with a platform according to an embodiment of the invention reproduced. The turbine blade 10, which may be, for example, a blade or vane of a gas turbine, comprises an airfoil 11 which terminates at the top in a blade tip 12 and has a leading edge 13 and a trailing edge 14. The blade 11 goes down to a shaft 15, to which a blade root 16 adjoins, which is formed fir-tree-like manner in a conventional manner to be used in a corresponding receptacle on the rotor.

Das Schaufelblatt 11 wird an seinem unteren Ende von einer Plattform 17 umschlossen, die gemäss Fig. 1 aus zwei separaten Plattformelementen 17a und 17b in einer Trennebene 19 zusammengesetzt ist, wobei die beiden Plattformelemente 17a,b mit entsprechenden Anschlussflächen 19a und 19b aneinander stossen (Fig. 1). Von den Anschlussflächen 19a und 19b ausgehend sind in die beiden Plattformelementen 17a,b Ausnehmungen 18a und 18b eingebracht, die bei zusammengesetzter Plattform 17 eine Öffnung 18 bilden, durch die hindurch sich das Schaufelblatt 11 erstrecken kann (Fig. 2). Wie aus den Fig. 1 und 2 zu entnehmen ist, erstreckt sich die Trennebene 19 auf beiden Seiten des Schaufelblattes 11 in axialer Richtung von der Vorderkante 13 bis zum vorderen Rand der Plattform 17 bzw. von der Hinterkante 14 bis zum hinteren Rand der Plattform 17.The blade 11 is enclosed at its lower end by a platform 17, according to Fig. 1 is composed of two separate platform elements 17a and 17b in a parting plane 19, wherein the two platform elements 17a, b abut one another with corresponding connection surfaces 19a and 19b ( Fig. 1 ). Starting from the connection surfaces 19a and 19b, recesses 18a and 18b are provided in the two platform elements 17a, b introduced, the composite platform 17 form an opening 18 through which the airfoil 11 can extend ( Fig. 2 ). Like from the Fig. 1 and 2 can be seen, the dividing plane 19 extends on both sides of the airfoil 11 in the axial direction from the front edge 13 to the front edge of the platform 17 and from the trailing edge 14 to the rear edge of the platform 17th

Fig. 3 zeigt beispielhaft die Befestigung der Plattformelemente 17a,b am Schaufelblatt 11 sowie die entsprechende Abdichtung zwischen den Plattformelementen 17a,b und dem Schaufelblatt 11. Zur Befestigung sind an der dem Schaufelblatt 11 zugewandten Seite der Plattformelemente 17a,b Haken 23 ausgebildet, mit denen die Plattformelemente 17a,b in eine entsprechende Nut 22 am Schaft 15 der Schaufel eingreifen. Auf diese Weise bleibt der Schaufelfuss 16 frei von irgendwelchen Beeinträchtigungen durch die Plattform 17. Zur Abdichtung ist in den Plattformelementen 17a,b am der Öffnung 18 zugewandten Rand eine umlaufende Dichtungsnut 20 vorgesehen, die eine angepasste Dichtung 21 aufnimmt. Fig. 3 shows, by way of example, the fastening of the platform elements 17a, b on the blade 11 and the corresponding seal between the platform elements 17a, b and the blade 11. For attachment, hooks 23 are formed on the side of the platform elements 17a, b facing the blade 11, with which the platform elements 17a, b engage in a corresponding groove 22 on the shank 15 of the blade. In this way, the blade root 16 remains free of any impairments by the platform 17. For sealing, a circumferential sealing groove 20 is provided in the platform elements 17a, b at the edge 18 facing edge, which receives a matched seal 21.

Die Verbindung der beiden Plattformelemente 17a und 17b kann auf unterschiedliche Weise erfolgen. Fig. 4 zeigt beispielhaft eine Verschraubung der beiden Elemente. Dazu sind an den beiden Plattformelementen 17a,b parallel zur Trennebene 19 ausgerichtete und in der Trennebene 19 aneinander stossende Flanschabschnitte 27a,b ausgebildet, durch welche hindurch die beiden Plattformelemente 17a,b mittels eines Verbindungselements 26, insbesondere in Form eines Schraubbolzens, miteinander verbunden sind. Anstelle des Schraubbolzens kann auch ein Niet eingesetzt werden. Wie in Fig. 4 (a) dargestellt, kann in der Trennebene 19 auch eine Abdichtung zwischen den Plattformelementen 17a,b vorgesehen werden. Hierzu ist in der Trennebene 19 eine Dichtungsnut 24 ausgebildet, die eine angepasste Dichtung 25 aufnimmt.The connection of the two platform elements 17a and 17b can be done in different ways. Fig. 4 shows an example of a screw connection of the two elements. For this purpose, aligned on the two platform elements 17a, b parallel to the parting plane 19 and abutting in the parting plane 19 flange portions 27a, b formed, through which the two platform elements 17a, b are connected to each other by means of a connecting element 26, in particular in the form of a bolt , Instead of the bolt can also be used a rivet. As in Fig. 4 (a) shown, in the parting plane 19, a seal between the platform elements 17a, b are provided. For this purpose, a sealing groove 24 is formed in the parting plane 19, which receives a matched seal 25.

Anstelle der lösbaren Verschraubung kann die Verbindung zwischen den Plattformelementen 17a,b aber auch stoffschlüssig mittels Schweissen oder Löten erfolgen.Instead of the detachable screw connection, the connection between the platform elements 17a, b but also cohesively by means of welding or soldering done.

Als weitere Möglichkeit der Verbindung zwischen den Plattformelementen 17a,b ist in Fig. 5 eine spezielle Art der Verriegelung gezeigt, die unter dem Stichwort "bi-cast" bekannt und beispielsweise in der Druckschrift US 5,797,725 beschrieben ist. In diesem Falle überlappen die beiden Plattformelemente 17a,b mit entsprechenden Überlappungsabschnitten 28a und 28b, wobei im Überlappungsbereich ein Verriegelungskanal 29 ausgebildet wird, der nach dem Zusammenfügen der Plattformelemente 17a,b mit einer metallischen Füllung 30 ausgegossen wird, die dann eine Relativbewegung zwischen den Überlappungsabschnitten 28a,b sicher verhindert. Wie der in Fig. 5(a) gezeigte Schnitt entlang der Ebene A-A aus Fig. 5(b) deutlich macht, können im Verriegelungskanal 29 seitlich herausstehende Nasen der Füllung 30 vorgesehen werden, um ein Herausrutschen der Füllung 30 in Längsrichtung des Verbindungskanals 29 zu verhindern.Another possibility of the connection between the platform elements 17a, b is in Fig. 5 shown a special type of locking, known under the keyword "bi-cast" and for example in the publication US 5,797,725 is described. In this case, the two platform elements 17a, b overlap with corresponding overlapping sections 28a and 28b, wherein in the overlapping area a locking channel 29 is formed, which is poured out after the joining of the platform elements 17a, b with a metallic filling 30, then a relative movement between the overlapping sections 28a, b safely prevented. In again Fig. 5 (a) shown section along the plane AA Fig. 5 (b) makes clear, laterally protruding lugs of the filling 30 can be provided in the locking channel 29 to prevent slipping out of the filling 30 in the longitudinal direction of the connecting channel 29.

Fig. 6 zeigt, alternativ zu derjenigen der Fig. 3, eine weitere Ausführungsart der Befestigung der Plattformelemente 17a,b am Schaufelblatt 11, die die Funktionen der mechanischen Befestigung und der Abdichtung miteinander vereint. An die Stelle einer kraft- und formschlüssigen Verbindung mittels der Befestigungselemente Nut 22 und Haken 23 sowie der Abdichtelemente Nut 20 und Dichtung 21, wie in Fig.3 beispielhaft dargestellt, tritt eine stoffschlüssige Verbindung dieser Komponenten mittels einer sich verfestigenden Füllung 30, welche in einen zwischen diesen zu verbindenden Turbinenschaufelkomponenten ausgebildeten Verriegelungskanal 29 eingiessbar ist. Dies zu erreichen, sind die zugewandten Anschlussflächen der Ausnehmung 18 der Plattformelemente 17a,b sowie des Schaufelblatts 11 bzw. des Schafts 15 der Turbinenschaufel 10 mit gegenüberliegenden Nuten zur Einbringung einer giessfähigen Füllung 30, insbesondere einer Metallschmelze, versehen. Nach Verfestigung des eingebrachten Füllmaterials, beispielsweise dessen Erstarrung oder Aushärtung, sind die Schaufelkomponenten fest miteinander verbunden. Dabei versteht es sich von selbst, dass ein Füllmaterial auszuwählen ist, welches unter den Bedingungen des bestimmungsgemässen Gebrauchs der Turbinenschaufel 10 in festem Aggregatzustand verbleibt und keine thermische Schädigung erfährt. Wird der Verriegelungskanal 29 durchgehend so ausgeführt, dass er einen geschlossenen Ring um das Blatt 11 bzw. den Schaft 15 der Turbinenschaufel 10 herum bildet, dann erfüllt diese Verbindung die Doppelfunktion der Befestigung und Abdichtung, da eine derartige Verbindung naturgemäss hinreichend fluiddicht ist. Das Erfordernis einer zusätzlichen Dichtung zwischen Schaufelblatt 11 oder -schaft 15 und Plattform 17 entfällt somit. Fig. 6 shows, alternatively to that of Fig. 3 , Another embodiment of the attachment of the platform elements 17a, b on the blade 11, which combines the functions of mechanical fastening and sealing together. In place of a non-positive and positive connection by means of the fastening elements groove 22 and hooks 23 and the sealing elements groove 20 and seal 21, as in Figure 3 by way of example, a cohesive connection of these components occurs by means of a solidifying filling 30, which can be poured into a locking channel 29 formed between the turbine blade components to be connected between them. To achieve this, the facing surfaces of the recess 18 of the platform elements 17a, b and the blade 11 and the shaft 15 of the turbine blade 10 are provided with opposing grooves for introducing a pourable filling 30, in particular a molten metal. After solidification of the introduced filling material, for example its solidification or hardening, the blade components are firmly connected. It goes without saying that a filling material is to be selected which remains under the conditions of the intended use of the turbine blade 10 in a solid state and undergoes no thermal damage. If the locking channel 29 is continuously designed so that it forms a closed ring around the blade 11 or the shaft 15 of the turbine blade 10 around, then this compound fulfills the dual function of attachment and sealing, since such a compound is naturally sufficiently fluid-tight. The requirement for an additional seal between the blade 11 or shaft 15 and platform 17 is thus eliminated.

Mit der Erfindung wird eine mechanische Entkopplung zwischen Plattform und Schaufel erreicht, die unerwünschte Spannungen vermeidet und gleichzeitig flexibel in der Anwendung ist und ohne Änderung der Schaufelbefestigung auch nachgerüstet werden kann.With the invention, a mechanical decoupling between platform and blade is achieved, which avoids undesirable stresses and at the same time is flexible in the application and can be retrofitted without changing the blade attachment.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1010
Turbinenschaufelturbine blade
1111
Schaufelblattairfoil
1212
Schaufelspitzeblade tip
1313
Vorderkanteleading edge
1414
Hinterkantetrailing edge
1515
Schaftshaft
1616
Schaufelfussblade root
1717
Plattformplatform
17a,b17a, b
Plattformelementplatform member
1818
Öffnungopening
18a,b18a, b
Ausnehmungrecess
1919
Trennebeneparting plane
19a,b19a, b
Anschlussflächeterminal area
20,2420.24
Dichtungsnutseal groove
21,2521,25
Dichtungpoetry
2222
Nutgroove
2323
Hakenhook
2626
Verbindungselement (z.B. Schraubbolzen, Niete)Connecting element (e.g., bolt, rivets)
27a,b27a, b
Flanschabschnittflange
28a,b28a, b
Überlappungsabschnittoverlapping portion
2929
Verriegelungskanallocking channel
3030
Füllungfilling

Claims (15)

  1. Turbine blade (10), comprising a blade body (11) with a leading edge (13) and a trailing edge (14), which body transforms via a shaft (15) into a blade root (16) designed for attaching the turbine blade (10), and comprising a platform (17) which is arranged at the lower end of the blade body (11) for delimiting a flow channel, wherein the platform (17) is configured as a separate component and can be connected by form fit to the blade body (11), wherein the platform (17) is composed of multiple individual platform elements (17a, b) which surround the blade body (11) in assembled state, wherein the platform (17) is attached to the turbine blade (10), characterised in that the platform (17) or the platform elements (17a, b) is/are connected by substance bonding to the turbine blade (10); wherein the turbine blade (11) or the blade shaft (15) firstly and the platform elements (17a, b) secondly are provided with a respective groove-like recess, and these groove-like recesses are arranged opposite each other so as to form a locking channel (29), and this locking channel (29) is filled with a cast filling (30); and wherein the locking channel (29) is formed so as to be continuous over the periphery of the turbine blade (11) or blade shaft (15).
  2. Turbine blade according to claim 1, characterised in that the platform (17) is composed of two platform elements (17a, b).
  3. Turbine blade according to claim 2, characterised in that in assembled state, the two platform elements (17a, b) abut each other with connecting faces (19a, b) in a separating plane (19) which extends from the leading edge (13) or trailing edge (14) of the turbine blade (11) to the associated edge of the platform (17) in the axial direction.
  4. Turbine blade according to claim 3, characterised in that the platform elements (17a, b) are each provided with recesses (18a, b) which start from the separating plane (19) and which, in assembled state, form an opening (18) adapted to the profile of the turbine blade (11) for the turbine blade (11) extending through the platform (17).
  5. Turbine blade according to claim 4, characterised in that the platform (17) is sealed against the turbine blade (11).
  6. Turbine blade according to claim 5, characterised in that for sealing against the turbine blade (11) along the opening (18), a peripheral sealing groove (20) which receives a corresponding seal (21) is made in the platform elements (17a, b).
  7. Turbine blade according to any of claims 3 to 6, characterised in that the two platform elements (17a, b) are sealed against each other in the separating plane (19).
  8. Turbine blade according to claim 7, characterised in that for sealing in the separating plane (19), a sealing groove (24) which receives a corresponding seal (25) is provided.
  9. Turbine blade according to any of claims 3 to 8, characterised in that the two platform elements (17a, b) are releasably connected together.
  10. Turbine blade according to claim 9, characterised in that the two platform elements (17a, b) are bolted (26) or riveted together.
  11. Turbine blade according to claim 10, characterised in that on the two platform elements (17a, b), flange portions (27a, b) are formed which are oriented parallel to the separating plane and abut each other in the separating plane (19), and through which the two platform elements (17a, b) are bolted (26) or riveted together.
  12. Turbine blade according to any of claims 3 to 8, characterised in that the two platform elements (17a, b) are locked together by locking means (29, 30).
  13. Turbine blade according to claim 12, characterised in that in assembled state, the platform elements (17a, b) overlap each other with overlapping portions (28a, b), that a locking channel (29) is formed between the overlapping portions (28a, b) in the overlap region, and that the locking channel (29) is filled with a cast filling (30).
  14. Turbine blade according to any of the preceding claims, characterised in that the filling (30) is a castable metal which assumes a solid aggregate state under the conditions of proper use of the turbine blade.
  15. Turbine blade according to any of the preceding claims, characterised in that laterally protruding tabs of the filling (30) are provided in the locking channel (29).
EP13712793.2A 2012-03-30 2013-03-27 Turbine blade Active EP2831376B1 (en)

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EP12162372.2A EP2644829A1 (en) 2012-03-30 2012-03-30 Turbine blade
PCT/EP2013/056610 WO2013144254A1 (en) 2012-03-30 2013-03-27 Turbine blade
EP13712793.2A EP2831376B1 (en) 2012-03-30 2013-03-27 Turbine blade

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KR20150002710A (en) 2015-01-07
US9920636B2 (en) 2018-03-20
EP2831376A1 (en) 2015-02-04
JP6153599B2 (en) 2017-06-28
EP2644829A1 (en) 2013-10-02
CN104169528A (en) 2014-11-26
US20150017007A1 (en) 2015-01-15
CN104169528B (en) 2016-07-20
JP2015515571A (en) 2015-05-28

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