EP2394026B1 - Gas turbine blade for a turbomachine - Google Patents
Gas turbine blade for a turbomachine Download PDFInfo
- Publication number
- EP2394026B1 EP2394026B1 EP10798489.0A EP10798489A EP2394026B1 EP 2394026 B1 EP2394026 B1 EP 2394026B1 EP 10798489 A EP10798489 A EP 10798489A EP 2394026 B1 EP2394026 B1 EP 2394026B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine blade
- turbomachine
- blade
- connecting element
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Not-in-force
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- 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
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
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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
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
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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
- 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
Definitions
- the invention relates to a gas turbine blade, in particular a compressor and / or turbine blade, for a turbomachine.
- each gas turbine blades When joining gas turbine blades and rotor disks or rings during assembly, repair or maintenance, each gas turbine blades must be positioned, displaced or rotated relative to adjacent gas turbine blades and thereby provided with a bias (so-called pre-twist).
- pre-twist a bias
- the US 3,328,867 describes an opening on a turbine blade tip over which a mechanical load can be introduced by means of a tool.
- the EP 1 939 401 A2 describes a method and apparatus for load transfer in rotor assemblies.
- the US Pat. No. 3,572,968 A describes a turbine having at least one stage of radial blades and a conversion assembly extending in a circle around the tips of the blades.
- the DE 10 2005 030516 A1 describes a rotor for a turbine, which is provided for receiving one or more rows of blades with a corresponding number of grooves which are each arranged in a direction perpendicular to the longitudinal axis of the rotor extending radial plane.
- the JP 2004 108290 A describes turbine rotor blades of a steam turbine which, for safe operation, prevents stop switches located between fixed blades and adjacent rotor blades from becoming loose or damaged.
- the US 5,393,200 describes a steam turbine blade having a blade profile according to given tables.
- a disadvantage of the known fasteners is the fact that they are relatively expensive, do not allow optimum load transfer into the gas turbine blade and even damage the gas turbine blade in the load application.
- the object of the present invention is to enable an improved possibility for load introduction into a gas turbine blade.
- the gas turbine blade comprises at least one receptacle for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade.
- a geometry of the gas turbine blade according to the invention is designed such that the gas turbine blade has a receptacle which forms an integral interface for the form-fitting arrangement of a corresponding connecting element. Due to the integrated receptacle, the gas turbine blade and the connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
- the connecting element which is designed as a tool, pin or mandrel is in this way easily and without affecting the other gas turbine blade areas form fit introduced or inserted into the receptacle and can be solved if necessary correspondingly easy again from the gas turbine blade. Mechanical loads can thereby be introduced easily, flexibly and without damaging the gas turbine blade.
- the gas turbine blade can be formed weight neutral or even reduced weight and allows due to the simple structural design a short tolerance chain with a correspondingly high repeatability.
- the respective geometry of the receptacle for example its arrangement, form-fitting depth or boundary, may be selected depending on the geometry or the intended use of the respective gas turbine blade.
- a radially inner end region of the gas turbine blade for connecting the gas turbine blade to a rotor disk or a rotor ring of the turbomachine and / or a radially outer end region of the gas turbine blade is designed as a shroud segment.
- the gas turbine blade can be designed as a compressor and / or turbine blade.
- a radially outer end region designed as a shroud segment serves for damping blade vibrations and is particularly suitable when using the gas turbine blades in a rear turbine stage.
- the shroud segment reduces the flow around the gas turbine blade tip and thereby increases the efficiency of the associated turbomachine.
- the shroud segment can in principle be formed in one piece or in several parts with the gas turbine blade.
- the receptacle is formed on the radially outer end region of the gas turbine blade.
- the receptacle is particularly accessible.
- a corresponding connecting element for example a tool, can be correspondingly easily introduced into the receptacle in order to apply a mechanical load to the gas turbine blade.
- a weight optimization of the gas turbine blade is made possible in that it is designed as a hollow blade and at least one cavity.
- the receptacle is formed as a core exit region of the cavity. This allows a particularly space-saving arrangement of the recording without affecting the other gas turbine blade areas.
- gas turbine blade being integrally formed with the receptacle and / or as a cast part.
- the gas turbine blade mechanically particularly stable, inexpensive and easy to manufacture.
- the actual geometry of the gas turbine blade can be approximated completely or at least largely to a desired geometry.
- electrochemical Drilling methods PECM drilling
- a further aspect of the invention relates to a shroud segment for arrangement on a gas turbine shovel, in particular a gas turbine blade according to one of the preceding embodiments, wherein an improved possibility for load introduction into a gas turbine blade according to the invention is made possible by the shroud segment a receptacle for the positive arrangement of a connecting element, by means of which a mechanical load can be introduced into the shroud segment comprises.
- the resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade are to be regarded as advantageous embodiments of the shroud segment and vice versa.
- the shroud segment can in principle be formed in one piece with the gas turbine blade or initially manufactured as a single part and then connected to the gas turbine blade.
- the shroud segment has two oppositely arranged and in longitudinal section substantially Z-shaped contact surface for attaching corresponding contact surfaces of two further shroud segments.
- connection system with a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, and with a connecting element, by means of which a mechanical load in the gas turbine blade can be introduced, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the gas turbine blade comprises a correspondingly formed with the connecting element receptacle for the positive arrangement of the connecting element. Due to the integrated receptacle, the gas turbine blade and the corresponding connecting element can interlock positively, so that mechanical Loads normal, that is, can be transmitted at right angles to the surfaces of the two connection partners.
- the gas turbine blade can be provided, for example, before connecting to a shaft of the turbomachine particularly simple and damage-free with a so-called pre-twist.
- the gas turbine blade can be provided in the context of a repair or overhaul with a so-called re-twist, so that the gas turbine blade can be readjusted.
- the receptacle are formed as a polygon socket, in particular as a hexagon socket, and the connecting element as a polygonal key, in particular as a hexagon key, for acting on the gas turbine blade with a torque.
- the connecting element as a polygonal key, in particular as a hexagon key, for acting on the gas turbine blade with a torque.
- the receptacle and the connecting element may alternatively or in addition to an Allen-like configuration basically also slot, Pozidriv, Torx, Tri-Wing, Torq set or tensioner-like design.
- Another aspect of the invention relates to a method for connecting a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the connecting element is arranged positively in a correspondingly formed with the connecting element receptacle of the gas turbine blade.
- the gas turbine blade and the corresponding connecting element can be arranged in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
- a further aspect of the invention relates to a rotor for a turbomachine with a rotor disk joined with a blade ring or with a rotor ring joined with a blade ring, wherein according to the invention it is provided that the blade ring has at least one gas turbine blade which comprises at least one exception for the form-fitting arrangement of a connecting element , wherein by means of the connecting element, a mechanical load in the gas turbine blade can be introduced.
- the rotor is designed as a blisk ("bladed disk”) or as a bling ("bladed ring”) for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine. As a result, a particularly high structural freedom is given.
- Fig. 1 shows a schematic perspective view of three gas turbine blades 10 according to the invention, which are arranged on a rotor disk 12.
- an integrally bladed rotor (so-called blisk or "bladed disk”) can be produced for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine.
- a rotor ring (not shown) may also be used, whereby a so-called bling (“bladed ring”) can be produced.
- a radially outer end portion 14a is formed as a shroud segment 16 (see FIG. Fig. 2 ).
- each gas turbine blade 10 also has an integral receptacle 18, in which a connecting element (not shown) can be arranged in a form-fitting manner.
- the receptacles 18 are each formed at the radially outer end portion 14a of the gas turbine blades 10 in the shroud segments 16 as mecanicsechskantworkn.
- connection region hexagonal key-shaped connecting element can be easily inserted into the respective receptacle 18 releasably to pressurize the gas turbine blade 10 in question with a torque.
- each gas turbine blade 10 can be easily, without damage and provided without the need for special tool with a so-called pre-twist.
- Fig. 2 shows an enlarged view of the in Fig. 1
- each shroud segment 16 has two contact surfaces which are arranged opposite one another and are substantially Z-shaped in longitudinal section (so-called Z-Shroud) for attaching corresponding contact surfaces 20 of the adjacent shroud segments 16 having.
- each shroud segment 16 comprises two opposing sealing fins 22 which, in particular during a rotation of the rotor 12 in a abradable region, rub against a sealing structure of an associated turbomachine.
- FIG. 3 shows for further clarification a schematic side view of one of in Fig. 1 shown gas turbine blades 10.
- Fig. 3 is described below in synopsis with 4 and FIG. 5 be explained.
- Fig. 4 shows here a schematic bottom view of in Fig. 3 shown gas turbine blade 10, while in Fig. 5 a schematic sectional side view of the gas turbine blade 10 along in in Fig. 4 shown section line VV is shown. It is especially in Fig. 5 recognizable that the gas turbine blade 10 in the present case is designed as a hollow blade and at least one cavity 24 includes.
- the receptacle 18 is in turn formed as a core exit region of the cavity 24. Furthermore, in Fig.
- a Tannenbaum für 26 formed on a radially inner end portion 14b of the gas turbine blade for joining the gas turbine blade 10 with the rotor disk 12 recognizable.
- the geometry and form-fitting depth of the receptacle 18 can be formed as a function of the shroud segment geometry, wherein, for example, the core exit region of the cavity 24, the arrangement of the contact surfaces 20 and / or a geometry of the sealing fins 22 can be taken into account.
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- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die Erfindung betrifft eine Gasturbinenschaufel, insbesondere eine Verdichter- und/oder Turbinenschaufel, für eine Strömungsmaschine..The invention relates to a gas turbine blade, in particular a compressor and / or turbine blade, for a turbomachine.
Beim Fügen von Gasturbinenschaufeln und Rotorscheiben oder -ringen während der Montage, Reparatur oder Instandhaltung muss jede Gasturbinenschaufeln positioniert, verschoben oder gegenüber benachbarten Gasturbinenschaufeln verdreht und hierdurch mit einer Vorspannung (sog. Pre-Twist) versehen werden können. Zu diesem Zweck existieren verschiedene Verbindungselemente bzw. Spezialwerkzeuge, mittels welchen eine entsprechende mechanische Last in die betreffende Gasturbinenschaufel einleitbar ist.When joining gas turbine blades and rotor disks or rings during assembly, repair or maintenance, each gas turbine blades must be positioned, displaced or rotated relative to adjacent gas turbine blades and thereby provided with a bias (so-called pre-twist). For this purpose, there are various connecting elements or special tools, by means of which a corresponding mechanical load in the gas turbine blade in question can be introduced.
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Als nachteilig an den bekannten Verbindungselementen ist dabei der Umstand anzusehen, dass diese vergleichsweise teuer sind, keine optimale Lasteinleitung in die Gasturbinenschaufel ermöglichen und die Gasturbinenschaufel bei der Lasteinleitung sogar beschädigen können.A disadvantage of the known fasteners is the fact that they are relatively expensive, do not allow optimum load transfer into the gas turbine blade and even damage the gas turbine blade in the load application.
Aufgabe der vorliegenden Erfindung ist es, eine verbesserte Möglichkeit zur Lasteinleitung in eine Gasturbinenschaufel zu ermöglichen.The object of the present invention is to enable an improved possibility for load introduction into a gas turbine blade.
Die Aufgabe wird erfindungsgemäß durch eine Gasturbinenschaufel mit den Merkmalen des Patentanspruchs 1 gelöst. Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Hunteransprüchen angegeben.The object is achieved by a gas turbine blade with the features of claim 1. Advantageous embodiments of the invention are specified in the respective Hunter claims.
Eine verbesserte Möglichkeit zur Lasteinleitung in eine Gasturbinenschaufel ist erfindungsgemäß dadurch ermöglicht, dass die Gasturbinenschaufel mindestens eine Aufnahme zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, umfasst. Mit anderen Worten ist eine Geometrie der erfindungsgemäßen Gasturbinenschaufel derart ausgebildet, dass die Gasturbinenschaufel eine Aufnahme aufweist, welche eine integrale Schnittstelle zur formschlüssigen Anordnung eines korrespondierenden Verbindungselements bildet. Durch die integrierte Aufnahme können die Gasturbinenschaufel und das Verbindungselement formschlüssig ineinander greifen, so dass mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Das Verbindungselement, welches als Werkzeug, Zapfen oder Dorn ausgebildet ist, ist auf diese Weise einfach und ohne Beeinträchtigung der übrigen Gasturbinenschaufelbereiche formschlüssig in die Aufnahme einbringbar bzw. einsteckbar und kann bei Bedarf entsprechend einfach wieder von der Gasturbinenschaufel gelöst werden. Mechanische Lasten können hierdurch einfach, flexibel und ohne Beschädigung der Gasturbinenschaufel in diese eingeleitet werden. Zudem kann die Gasturbinenschaufel gewichtsneutral oder sogar gewichtsreduziert ausgebildet sein und ermöglicht aufgrund des einfachen konstruktiven Aufbaus eine kurze Toleranzkette mit entsprechend hoher Wiederholgenauigkeit. Die jeweilige Geometrie der Aufnahme, beispielsweise ihre Anordnung, Formschlusstiefe oder Berandung, kann in Abhängigkeit der Geometrie oder des Einsatzzwecks der jeweiligen Gasturbinenschaufel gewählt sein.An improved possibility for load introduction into a gas turbine blade is made possible according to the invention in that the gas turbine blade comprises at least one receptacle for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade. In other words, a geometry of the gas turbine blade according to the invention is designed such that the gas turbine blade has a receptacle which forms an integral interface for the form-fitting arrangement of a corresponding connecting element. Due to the integrated receptacle, the gas turbine blade and the connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners. The connecting element, which is designed as a tool, pin or mandrel is in this way easily and without affecting the other gas turbine blade areas form fit introduced or inserted into the receptacle and can be solved if necessary correspondingly easy again from the gas turbine blade. Mechanical loads can thereby be introduced easily, flexibly and without damaging the gas turbine blade. In addition, the gas turbine blade can be formed weight neutral or even reduced weight and allows due to the simple structural design a short tolerance chain with a correspondingly high repeatability. The respective geometry of the receptacle, for example its arrangement, form-fitting depth or boundary, may be selected depending on the geometry or the intended use of the respective gas turbine blade.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass ein radial innerer Endbereich der Gasturbinenschaufel zur Verbindung der Gasturbinenschaufel mit einer Rotorscheibe oder einem Rotorring der Strömungsmaschine und/oder ein radial äußerer Endbereich der Gasturbinenschaufel als Deckbandsegment ausgebildet ist. Mit Hilfe eines derartigen radial inneren Endbereichs wird ein einfaches Fügen von Gasturbinenschaufel und Rotorscheibe bzw. Rotorring ermöglicht. Die Gasturbinenschaufel kann dabei als Verdichter- und/oder Turbinenschaufel ausgebildet sein. Ein als Deckbandsegment ausgebildeter radial äußerer Endbereich dient zur Dämpfung von Schaufelschwingungen und eignet sich insbesondere bei einer Verwendung der Gasturbinenschaufeln in einer hinteren Turbinenstufe. Weiterhin vermindert das Deckbandsegment die Umströmung der Gasturbinenschaufelspitze und erhöht hierdurch den Wirkungsgrad der zugeordneten Strömungsmaschine. Das Deckbandsegment kann dabei grundsätzlich einteilig oder mehrteilig mit der Gasturbinenschaufel ausgebildet sein.In an advantageous embodiment of the invention, it is provided that a radially inner end region of the gas turbine blade for connecting the gas turbine blade to a rotor disk or a rotor ring of the turbomachine and / or a radially outer end region of the gas turbine blade is designed as a shroud segment. With the aid of such a radially inner end region, a simple joining of gas turbine blade and rotor disk or rotor ring is made possible. The gas turbine blade can be designed as a compressor and / or turbine blade. A radially outer end region designed as a shroud segment serves for damping blade vibrations and is particularly suitable when using the gas turbine blades in a rear turbine stage. Furthermore, the shroud segment reduces the flow around the gas turbine blade tip and thereby increases the efficiency of the associated turbomachine. The shroud segment can in principle be formed in one piece or in several parts with the gas turbine blade.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Aufnahme am radial äußeren Endbereich der Gasturbinenschaufel ausgebildet ist. Indem die Aufnahme am radial äußeren Endbereich der Gasturbinenschaufel ausgebildet ist, ist die Aufnahme besonders gut zugänglich. Hierdurch kann ein korrespondierendes Verbindungselement, beispielsweise ein Werkzeug, entsprechend einfach in die Aufnahme eingebracht werden, um die Gasturbinenschaufel mit einer mechanischen Last zu beaufschlagen.In a further advantageous embodiment of the invention it is provided that the receptacle is formed on the radially outer end region of the gas turbine blade. By the receptacle at the radially outer end portion of the gas turbine blade is formed, the receptacle is particularly accessible. In this way, a corresponding connecting element, for example a tool, can be correspondingly easily introduced into the receptacle in order to apply a mechanical load to the gas turbine blade.
Eine Gewichtsoptimierung der Gasturbinenschaufel ist dadurch ermöglicht, dass diese als Hohlschaufel ausgebildet ist und zumindest einen Hohlraum umfasst.A weight optimization of the gas turbine blade is made possible in that it is designed as a hollow blade and at least one cavity.
Dabei hat es sich weiterhin als vorteilhaft gezeigt, dass die Aufnahme als Kernaustrittsbereich des Hohlraums ausgebildet ist. Dies ermöglicht eine besonders bauraumsparende Anordnung der Aufnahme ohne Beeinträchtigung der übrigen Gasturbinenschaufelbereiche.It has also been shown to be advantageous that the receptacle is formed as a core exit region of the cavity. This allows a particularly space-saving arrangement of the recording without affecting the other gas turbine blade areas.
Weitere Vorteile ergeben sich, indem die Gasturbinenschaufel einteilig mit der Aufnahme und/oder als Gussteil ausgebildet ist. Hierdurch kann die Gasturbinenschaufel mechanisch besonders stabil, kostengünstig und einfach hergestellt werden.Further advantages result from the gas turbine blade being integrally formed with the receptacle and / or as a cast part. As a result, the gas turbine blade mechanically particularly stable, inexpensive and easy to manufacture.
Indem zumindest ein Oberflächenbereich der Gasturbinenschaufel feinbearbeitet ist, kann die Ist-Geometrie der Gasturbinenschaufel vollständig oder zumindest weitgehend an eine Soll-Geometrie angenähert werden. Zum Feinbearbeiten können beispielsweise elektrochemische Bohrverfabren (PECM-Bohren) verwendet werden. Alternativ oder zusätzlich können jedoch auch weitere mechanische und/oder elektrochemische Abtrag- und/oder Auftragverfahren zur Feinbearbeitung vorgesehen sein.By at least one surface area of the gas turbine blade is finished, the actual geometry of the gas turbine blade can be approximated completely or at least largely to a desired geometry. For fine machining, for example, electrochemical Drilling methods (PECM drilling) can be used. Alternatively or additionally, however, it is also possible to provide further mechanical and / or electrochemical removal and / or application methods for fine machining.
Ein weiterer Aspekt der Erfindung betrifft ein Deckbandsegment zur Anordnung an einer Gasturbinenschaüfel, insbesondere einer Gasturbinenschaufel nach einem der vorhergehenden Ausführungsbeispiele, wobei eine verbesserte Möglichkeit zur Lasteinleitung in eine Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass das Deckbandsegment eine Aufnahme zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanische Last in das Deckbandsegment einleitbar ist, umfasst. Die sich hieraus ergebenden Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel als vorteilhafte Ausgestaltungen des Deckbandsegments und umgekehrt anzusehen sind. Das Deckbandsegment kann grundsätzlich einteilig mit der Gasturbinenschaufel ausgebildet oder zunächst als Einzelteil hergestellt und anschließend mit der Gasturbinenschaufel verbunden sein.A further aspect of the invention relates to a shroud segment for arrangement on a gas turbine shovel, in particular a gas turbine blade according to one of the preceding embodiments, wherein an improved possibility for load introduction into a gas turbine blade according to the invention is made possible by the shroud segment a receptacle for the positive arrangement of a connecting element, by means of which a mechanical load can be introduced into the shroud segment comprises. The resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade are to be regarded as advantageous embodiments of the shroud segment and vice versa. The shroud segment can in principle be formed in one piece with the gas turbine blade or initially manufactured as a single part and then connected to the gas turbine blade.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass das Deckbandsegment zwei einander gegenüberliegend angeordnete und im Längsschnitt im Wesentlichen Z-förmige Kontaktfläche zur Anlagerung korrespondierender Kontaktflächen zweier weiterer Deckbandsegmente aufweist. Hierdurch können sich benachbarte Gasturbinenschaufeln, die jeweils mit einem derartigen Deckbandsegment versehen sind, während des Betriebs einer zugeordneten Strömungsmaschine bzw. eines mit diesen Gasturbinenschaufeln versehenen Rotors paarweise aneinander abstützen, wodurch ein mechanisch besonders stabiles Deckband geschaffen wird. Ein unerwünschtes Verbiegen oder Verdrehen der Gasturbinenschaufel während des Betriebs wird hierdurch ebenfalls minimiert.In an advantageous embodiment of the invention, it is provided that the shroud segment has two oppositely arranged and in longitudinal section substantially Z-shaped contact surface for attaching corresponding contact surfaces of two further shroud segments. As a result, adjacent gas turbine blades, which are each provided with such a shroud segment, during operation of an associated turbomachine or a rotor provided with these gas turbine blades pairs abut each other, creating a mechanically particularly stable shroud is created. Undesirable bending or twisting of the gas turbine blade during operation is also minimized thereby.
Ein weiterer Aspekt der Erfindung begriff ein Verbindungssystem mit einer Gasturbinenschaufel, insbesondere einer Verdichter- und/oder Turbinenschaufel für eine Strömungsmaschine, und mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, wobei eine verbesserte Möglichkeit zur Lasteinleitung in die Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass die Gasturbinenschaufel eine korrespondierend mit dem Verbindungselement ausgebildete Aufnahme zum formschlüssigen Anordnen des Verbindungselements umfasst. Durch die integrierte Aufnahme können die Gasturbinenschaufel und das korrespondierende Verbindungselement formschlüssig ineinander greifen, so dass mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Somit ist eine einfache, lösbare und beschädigungsfreie Lastein- und/oder -ausleitung in bzw. aus der Gasturbinenschaufel möglich. Auf diese Weise kann die Gasturbinenschaufel beispielsweise vor dem Verbinden mit einer Welle der Strömungsmaschine besonders einfach und beschädigungsfrei mit einem sogenannten Pre-Twist versehen werden. Entsprechend einfach und beschädigungsfrei kann die Gasturbinenschaufel im Rahmen einer Reparatur oder Überholung mit einem sogenannten Re-Twist versehen werden, so dass die Gasturbinenschaufel nachgestellt werden kann. Weitere Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel bzw. des Deckbandelsegments als vorteilhafte Ausgestaltungen des Verbindungssystems und umgekehrt anzusehen sind.Another aspect of the invention involved a connection system with a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, and with a connecting element, by means of which a mechanical load in the gas turbine blade can be introduced, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the gas turbine blade comprises a correspondingly formed with the connecting element receptacle for the positive arrangement of the connecting element. Due to the integrated receptacle, the gas turbine blade and the corresponding connecting element can interlock positively, so that mechanical Loads normal, that is, can be transmitted at right angles to the surfaces of the two connection partners. Thus, a simple, releasable and damage-free load input and / or -ausleitung in or out of the gas turbine blade is possible. In this way, the gas turbine blade can be provided, for example, before connecting to a shaft of the turbomachine particularly simple and damage-free with a so-called pre-twist. Correspondingly simple and free of damage, the gas turbine blade can be provided in the context of a repair or overhaul with a so-called re-twist, so that the gas turbine blade can be readjusted. Further advantages can be found in the preceding descriptions, wherein advantageous embodiments of the gas turbine blade or of the shroud segment are to be regarded as advantageous embodiments of the connection system and vice versa.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Aufnahme als Innenmehrkantaufnahme, insbesondere als Innensechskantaufnahme, und das Verbindungselement als Mehrkantschlüssel, insbesondere als Sechskantschlüssel, zum Beaufschlagen der GasturbinenSchaufel mit einem Drehmoment ausgebildet sind. Hierdurch kann auf besonders einfache und kostengünstige Weise eine Lasteinleitung in die Gasturbinenschaufel erfolgen, ohne dass teures Spezialwerkzeug erforderlich ist. Dies erhöht zudem die Wartungsfreundlichkeit der Gasturbinenschaufel bzw. einer mit dieser versehenen Strömungsmaschine. Dabei können die Aufnahme und das Verbindungselement alternativ oder zusätzlich zu einer Inbus-artigen Ausgestaltung grundsätzlich auch Schlitz-, Pozidriv-, Torx-, Tri-Wing-, Torq-Set- oder Spanner-artig ausgebildet sein.In an advantageous embodiment of the invention it is provided that the receptacle are formed as a polygon socket, in particular as a hexagon socket, and the connecting element as a polygonal key, in particular as a hexagon key, for acting on the gas turbine blade with a torque. As a result, a load introduction into the gas turbine blade can be carried out in a particularly simple and cost-effective manner, without the need for expensive special tools. This also increases the ease of maintenance of the gas turbine blade or a turbomachine provided with this. In this case, the receptacle and the connecting element may alternatively or in addition to an Allen-like configuration basically also slot, Pozidriv, Torx, Tri-Wing, Torq set or tensioner-like design.
Ein weiterer Aspekt der Erfindung betrifft ein Verfahren zum Verbinden einer Gasturbinenschaufel, insbesondere einer Verdichter- und/oder Turbinenschaufel für eine Strömungsmaschine, mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, wobei eine verbesserte Möglichkeit zur Lasteinleitung in die Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass das Verbindungselement formschlüssig in einer korrespondierend mit dem Verbindungselement ausgebildeten Aufnahme der Gasturbinenschaufel angeordnet wird. Durch die integrierte Aufnahme können die Gasturbinenschaufel und das korrespondierende Verbindungselement formschlüssig ineinander angeordnet werden, so das mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Somit ist eine einfache, lösbare und beschädigungsfreie Lastein - und/oder -ausleitung in bzw. aus der Gasturbinenschaufel möglich. Weitere Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel, des Deckbandelsegments und/oder des Verbindungssystems als vorteilhafte Ausgestaltungen des Verfahrens und umgekehrt anzusehen sind.Another aspect of the invention relates to a method for connecting a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the connecting element is arranged positively in a correspondingly formed with the connecting element receptacle of the gas turbine blade. As a result of the integrated receptacle, the gas turbine blade and the corresponding connecting element can be arranged in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners. Thus, a simple, removable and damage-free load input and / or discharge into or out of the gas turbine blade is possible. Further advantages can be found in the preceding descriptions, wherein advantageous embodiments of the gas turbine blade, the Deckbandelsegments and / or the connection system are to be regarded as advantageous embodiments of the method and vice versa.
Ein weiterer Aspekt der Erfindung betrifft einen Rotor für eine Strömungsmaschine mit einer mit einem Schaufelkranz gefügten Rotorscheibe oder mit einem mit einem Schaufelkranz gefügten Rotorring, wobei erfindungsgemäß vorgesehen ist, dass der Schaufelkranz wenigstens eine Gasturbinenschaufel aufweist, die mindestens eine Ausnahme zum formschlüssigen Anordnen eines Verbindungselements umfasst, wobei mittels des Verbindungselements eine mechanische Last in die Gasturbinenschaufel einleitbar ist. Die sich hieraus ergebenden Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel, des Deckbandelsegments, des Verbindungssystems und/oder des Verfahrens zum Verbinden einer Gasturbinenschaufel mit einem Verbindungselement als vorteilhafte Ausgestaltungen des Rotors und umgekehrt anzusehen sind.A further aspect of the invention relates to a rotor for a turbomachine with a rotor disk joined with a blade ring or with a rotor ring joined with a blade ring, wherein according to the invention it is provided that the blade ring has at least one gas turbine blade which comprises at least one exception for the form-fitting arrangement of a connecting element , wherein by means of the connecting element, a mechanical load in the gas turbine blade can be introduced. The resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade, the Deckbandelsegments, the connection system and / or the method for connecting a gas turbine blade with a connecting element are to be regarded as advantageous embodiments of the rotor and vice versa.
Dabei hat es sich als vorteilhaft gezeigt, wenn der Rotor als Blisk ("Bladed Disk") oder als Bling ("Bladed Ring") für einen Verdichter und/oder für eine Turbine einer Strömungsmaschine, insbesondere einer thermischen Gasturbine, ausgebildet ist. Hierdurch ist eine besonders hohe konstruktive Freiheit gegeben.It has proven to be advantageous if the rotor is designed as a blisk ("bladed disk") or as a bling ("bladed ring") for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine. As a result, a particularly high structural freedom is given.
Weitere Merkmale der Erfindung ergeben sich aus den Ansprüche, den Ausführungsbeispielen sowie anhand der Zeichnungen. Die vorstehend in der Beschreibung genannten Merkmale und Merkmalskombinationen sowie die nachfolgend in den Ausführungsbeispielen genannten Merkmale und Merkmalskombinationen sind nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen oder in Alleinstellung verwendbar, ohne den Rahmen der Erfindung zu verlassen. Dabei zeigen:
- Fig. 1
- eine schematische Perspektivansicht von drei erfindungsgemäßen Gasturbinenschaufeln, die auf einer Rotorscheibe angeordnet sind;
- Fig. 2
- eine vergrößerte Aufsicht des in
Fig. 1 gezeigten Details II; - Fig. 3
- eine schematische Seitenansicht einer in
Fig 1 gezeigten Gasturbinenschaufel; - Fig. 4
- eine schematische Unteransicht der in
Fig. 3 gezeigten Gasturbinenschaufel; und - Fig. 5
- eine schematische seitliche Schnittansicht der Gasturbinenschaufel entlang der in
Fig. 4 gezeigten Schnittlinie V-V.
- Fig. 1
- a schematic perspective view of three gas turbine blades according to the invention, which are arranged on a rotor disk;
- Fig. 2
- an enlarged view of the in
Fig. 1 shown details II; - Fig. 3
- a schematic side view of an in
Fig. 1 shown gas turbine blade; - Fig. 4
- a schematic bottom view of in
Fig. 3 shown gas turbine blade; and - Fig. 5
- a schematic sectional side view of the gas turbine blade along in
Fig. 4 shown section line VV.
Claims (5)
- A gas turbine blade (10), in particular a compressor and/or turbine blade, for a turbomachine, wherein the gas turbine blade (10) comprises at least one receiver (18) for the form-closing arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade (10), wherein the gas turbine blade (10) is formed as a hollow blade and comprises at least one hollow space (24), and wherein the receiver (18) is formed as a core outlet region of the hollow space (24), characterised in that the receiver (18) is configured in order to receive the connecting element, configured as a tool, pin or mandrel, for form-closing insertion and/or plugging-in into the receiver (18) for the introduction of mechanical loads into the gas turbine blade.
- A gas turbine blade (10) according to claim 1, characterised in that a radially inner end region (14b) of the gas turbine blade (10) is formed for the connection of the gas turbine blade (10) to a rotor disk (12) or a rotor ring of the turbomachine, and/or a radially outer end region (14a) of the gas turbine blade (10) is formed as a shroud-band segment (16).
- A gas turbine blade (10) according to claim 1 or 2, characterised in that the receiver (18) is formed on the radially outer end region (14a) of the gas turbine blade (10).
- A gas turbine blade (10) according to one of claims 1 to 3, characterised in that it is formed in one piece with the receiver (18) and/or as a cast portion.
- A gas turbine blade (10) according to one of claims 1 to 4, characterised in that at least one surface region of the gas turbine blade (10) is finely machined.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009052881A DE102009052881A1 (en) | 2009-11-13 | 2009-11-13 | Gas turbine blade for a turbomachine |
PCT/DE2010/001334 WO2011057622A2 (en) | 2009-11-13 | 2010-11-12 | Gas turbine blade for a turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2394026A2 EP2394026A2 (en) | 2011-12-14 |
EP2394026B1 true EP2394026B1 (en) | 2013-07-17 |
Family
ID=43901923
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10798489.0A Not-in-force EP2394026B1 (en) | 2009-11-13 | 2010-11-12 | Gas turbine blade for a turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US8622704B2 (en) |
EP (1) | EP2394026B1 (en) |
DE (1) | DE102009052881A1 (en) |
WO (1) | WO2011057622A2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10428660B2 (en) * | 2017-01-31 | 2019-10-01 | United Technologies Corporation | Hybrid airfoil cooling |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE634692A (en) | 1962-07-11 | 1963-11-18 | ||
US3572968A (en) * | 1969-04-11 | 1971-03-30 | Gen Electric | Turbine bucket cover |
US3626568A (en) * | 1969-04-23 | 1971-12-14 | Avco Corp | Method for bonding pins into holes in a hollow turbine blade |
US4136516A (en) * | 1977-06-03 | 1979-01-30 | General Electric Company | Gas turbine with secondary cooling means |
US5393200A (en) * | 1994-04-04 | 1995-02-28 | General Electric Co. | Bucket for the last stage of turbine |
US6158104A (en) * | 1999-08-11 | 2000-12-12 | General Electric Co. | Assembly jig for use with integrally covered bucket blades |
JP2004108290A (en) | 2002-09-19 | 2004-04-08 | Toshiba Corp | Turbine rotor blade |
US6883700B2 (en) * | 2002-09-26 | 2005-04-26 | Siemens Westinghouse Power Corporation | Turbine blade closure system |
DE10250779A1 (en) * | 2002-10-30 | 2004-05-19 | Alstom (Switzerland) Ltd. | Emergency cooling system for a heat-stressed component |
DE102005030516A1 (en) | 2005-06-28 | 2007-01-04 | Man Turbo Ag | Rotor for a turbine and method and apparatus for producing the rotor |
US20080145227A1 (en) | 2006-12-19 | 2008-06-19 | Mark Stefan Maier | Methods and apparatus for load transfer in rotor assemblies |
SG155788A1 (en) * | 2008-03-18 | 2009-10-29 | Turbine Overhaul Services Pte | Methods and apparatuses for correcting twist angle in a gas turbine engine blade |
-
2009
- 2009-11-13 DE DE102009052881A patent/DE102009052881A1/en not_active Withdrawn
-
2010
- 2010-11-12 WO PCT/DE2010/001334 patent/WO2011057622A2/en active Application Filing
- 2010-11-12 EP EP10798489.0A patent/EP2394026B1/en not_active Not-in-force
- 2010-11-12 US US13/508,875 patent/US8622704B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
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WO2011057622A3 (en) | 2011-10-13 |
US20120230825A1 (en) | 2012-09-13 |
EP2394026A2 (en) | 2011-12-14 |
WO2011057622A2 (en) | 2011-05-19 |
DE102009052881A1 (en) | 2011-05-26 |
US8622704B2 (en) | 2014-01-07 |
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