EP2644829A1 - Turbine blade - Google Patents
Turbine blade Download PDFInfo
- Publication number
- EP2644829A1 EP2644829A1 EP12162372.2A EP12162372A EP2644829A1 EP 2644829 A1 EP2644829 A1 EP 2644829A1 EP 12162372 A EP12162372 A EP 12162372A EP 2644829 A1 EP2644829 A1 EP 2644829A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- turbine blade
- blade according
- elements
- platform elements
- 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.)
- Withdrawn
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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
- F01D5/22—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
- 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
- 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
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- 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.
- 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 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.
- 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 platform is hooked to the turbine blade.
- the platform or the platform elements are equipped with hooks, with which it is hooked into a groove in the region of the shaft of the turbine blade (are).
- 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 ).
- recesses 18a and 18b are introduced into the two platform elements 17a, b which, when the platform 17 is assembled, form an opening 18 through which the airfoil 11 can extend (FIG. 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 interference by the platform 17.
- For sealing is in the platform elements 17a, b at the opening 18 edge facing a circumferential sealing groove 20 is provided 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 joining 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, 29 laterally protruding lugs of the filling 30 can be provided in the locking channel be to prevent slippage of the filling 30 in the longitudinal direction of the connecting channel 29.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
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.
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
Aus der Druckschrift
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 to delimit 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 it is hooked into a groove in the region of the shaft of the turbine blade (are).
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 Plattformelementes 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; und
- Fig. 5
- in der Seitenansicht (a) und der Draufsicht von oben (b) ein Ausführungsbeispiel für eine verriegelte Plattform nach der Erfindung.
- 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; and
- Fig. 5
- in the side view (a) and the top view from above (b) an embodiment of a locked platform according to the invention.
In
Das Schaufelblatt 11 wird an seinem unteren Ende von einer Plattform 17 umschlossen, die gemäss
Die Verbindung der beiden Plattformelemente 17a und 17b kann auf unterschiedliche Weise erfolgen.
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
Als weitere Möglichkeit der Verbindung zwischen den Plattformelementen 17a,b ist in
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.
- 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 (16)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12162372.2A EP2644829A1 (en) | 2012-03-30 | 2012-03-30 | Turbine blade |
JP2015502343A JP6153599B2 (en) | 2012-03-30 | 2013-03-27 | Turbine blade |
KR20147030219A KR20150002710A (en) | 2012-03-30 | 2013-03-27 | Turbine blade |
CN201380017373.3A CN104169528B (en) | 2012-03-30 | 2013-03-27 | Turbo 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 |
US14/499,386 US9920636B2 (en) | 2012-03-30 | 2014-09-29 | Turbine blade or vane |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12162372.2A EP2644829A1 (en) | 2012-03-30 | 2012-03-30 | Turbine blade |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2644829A1 true EP2644829A1 (en) | 2013-10-02 |
Family
ID=48014009
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12162372.2A Withdrawn EP2644829A1 (en) | 2012-03-30 | 2012-03-30 | Turbine blade |
EP13712793.2A Active EP2831376B1 (en) | 2012-03-30 | 2013-03-27 | Turbine blade |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13712793.2A Active EP2831376B1 (en) | 2012-03-30 | 2013-03-27 | Turbine blade |
Country Status (6)
Country | Link |
---|---|
US (1) | US9920636B2 (en) |
EP (2) | EP2644829A1 (en) |
JP (1) | JP6153599B2 (en) |
KR (1) | KR20150002710A (en) |
CN (1) | CN104169528B (en) |
WO (1) | WO2013144254A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3028793A1 (en) * | 2014-12-04 | 2016-06-08 | Siemens Aktiengesellschaft | Method for manufacturing a rotor blade |
WO2015075227A3 (en) * | 2013-11-25 | 2016-09-15 | General Electric Technology Gmbh | Blade assembly for a turbomachine on the basis of a modular structure |
EP3139005A1 (en) * | 2015-09-01 | 2017-03-08 | United Technologies Corporation | Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine |
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JP6479328B2 (en) * | 2014-04-02 | 2019-03-06 | 三菱日立パワーシステムズ株式会社 | Rotor and rotary machine |
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US10774662B2 (en) * | 2018-07-17 | 2020-09-15 | Rolls-Royce Corporation | Separable turbine vane stage |
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KR20230081267A (en) | 2021-11-30 | 2023-06-07 | 두산에너빌리티 주식회사 | Turbine blade, turbine and gas turbine including the same |
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- 2013-03-27 JP JP2015502343A patent/JP6153599B2/en not_active Expired - Fee Related
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WO2015075227A3 (en) * | 2013-11-25 | 2016-09-15 | General Electric Technology Gmbh | Blade assembly for a turbomachine on the basis of a modular structure |
EP3028793A1 (en) * | 2014-12-04 | 2016-06-08 | Siemens Aktiengesellschaft | Method for manufacturing a rotor blade |
WO2016087140A1 (en) * | 2014-12-04 | 2016-06-09 | Siemens Aktiengesellschaft | Method for producing a rotor blade, and blade obtained by such a method |
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EP3139005A1 (en) * | 2015-09-01 | 2017-03-08 | United Technologies Corporation | Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
CN104169528A (en) | 2014-11-26 |
CN104169528B (en) | 2016-07-20 |
JP6153599B2 (en) | 2017-06-28 |
KR20150002710A (en) | 2015-01-07 |
EP2831376A1 (en) | 2015-02-04 |
US20150017007A1 (en) | 2015-01-15 |
EP2831376B1 (en) | 2018-10-24 |
WO2013144254A1 (en) | 2013-10-03 |
JP2015515571A (en) | 2015-05-28 |
US9920636B2 (en) | 2018-03-20 |
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