EP2404037B1 - Integrally bladed rotor for a turbomachine - Google Patents

Integrally bladed rotor for a turbomachine Download PDF

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Publication number
EP2404037B1
EP2404037B1 EP10713552.7A EP10713552A EP2404037B1 EP 2404037 B1 EP2404037 B1 EP 2404037B1 EP 10713552 A EP10713552 A EP 10713552A EP 2404037 B1 EP2404037 B1 EP 2404037B1
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EP
European Patent Office
Prior art keywords
rotor according
rotor
sealing elements
blade
inspection
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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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EP10713552.7A
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German (de)
French (fr)
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EP2404037A1 (en
Inventor
Frank Stiehler
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP2404037A1 publication Critical patent/EP2404037A1/en
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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
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing

Definitions

  • the invention relates to an integrally bladed rotor for a turbomachine, in particular for a gas turbine, wherein cavities are provided in the region of the blade necks between adjacent blades, which are formed by recesses in opposite sides of adjacent blade necks.
  • Rotors with integral blading are referred to as a blisk or bling, depending on whether there is a disk-shaped rotor or rotor with a cross-section in cross-section (referred to below as the rotor body).
  • Blisk is the short form of Bladed Disk and Bling of Bladed Ring.
  • an integrally bladed rotor according to the invention for a turbomachine, in particular for a gas turbine.
  • cavities are provided between adjacent blades which are formed by recesses in opposite sides of adjacent blade necks. From each cavity extends an inspection opening radially inwardly, which is accessible from the outside and allows an examination of the cavity from the outside. In this way, an inspection of the cavity is made possible, while the cavity is sealed as well as possible in the axial directions and in the radially outward direction.
  • the inspection openings are closed by sealing elements. After an inspection of the cavities, for example, after the Manufacture of the rotor or maintenance intervals has been performed, the inspection openings can thus be closed.
  • the sealing elements can be cylindrical. This allows a simple geometry of the sealing elements and the inspection opening to be sealed.
  • the sealing elements are made of a nickel-based material. This allows a temperature-resistant design of the sealing elements.
  • the sealing elements can be coated.
  • the surface properties of the sealing elements are improved and adapted in particular to the materials used of the blades.
  • the sealing elements are separately manufactured parts that are attached to the blade necks by press-fitting, positive locking and / or welding. In this way, a good seal of the inspection openings is ensured by the sealing elements and prevents slippage of the sealing elements.
  • the sealing elements are removably attached to the blade necks. This allows for inspection of the cavities at any one time.
  • the sealing elements extend for example over the entire axial length of the associated blade neck. Thus, a positioning of the sealing element in the axial direction is simplified.
  • each inspection opening opens into a channel extending in the axial direction. This channel allows easy access to the inspection opening.
  • the axially extending channel may be a cooling fluid channel. This provides improved cooling of the boundary between the rotor body and the blade necks.
  • a cover plate is arranged in the axial direction upstream and / or downstream of the channel.
  • the cover plate or the cover plates can cover the channel in whole or in part, whereby, for example, an axial movement of the sealing elements is prevented or limited.
  • the cover plate may form a guide for the cooling fluid. This allows, for example, a deflection of the cooling fluid flow from the axial direction of the channel in a radial direction.
  • the channels and the openings are coordinated so that it can be seen from the outside into the cavities. This allows easy inspection of the cavities with the eye or a device.
  • Each blade may be welded to the rotor body via an adapter made of a different material, and the channels may be provided at least between adjacent spacers.
  • the intermediate pieces it is possible to simplify the joining of the blades to the rotor base body, in particular if the blades and the rotor base body are made of different materials, for example in monocrystalline blades and polycrystalline rotor base body or in different alloys in which a fusion welding process is not applicable.
  • adjacent blade necks are separated by a narrow axial and radial gap and the inspection opening is formed by a local enlargement of the gap.
  • This may also be the case, for example, with monocrystalline vanes in which the vanes can not be joined by fusion welding.
  • the blade necks preferably have extensions which together form a cover strip extending in the circumferential direction, wherein the cover strip with adjacent rotors and shrouds forms a circumferential space which is traversed by cooling fluid.
  • a cooling of the rotors is possible.
  • An axially intermediate space and a rear space may be provided, wherein the axially extending channels connect the front space with the rear space. In this way, a flow of cooling fluid from the front gap results in the rear gap.
  • FIGS. 1 to 5 show a sector of an integrally bladed rotor 10.
  • the rotor 10 has a rotor body 12, which in the embodiment shown is a rotor disk.
  • the rotor base body 12 may, however, also be annular, for example.
  • the integrally bladed rotor 10 is designed for a gas turbine and may be located in the turbine section or in the compressor section.
  • the invention can also be applied to integrally bladed rotors of other turbomachines.
  • a plurality of blades 14 are provided, which are e.g. are connected via separate intermediate pieces 16 with the rotor body 12.
  • the blades 14 are made, for example, from single-crystalline nickel-based materials that do not allow fusion welding.
  • a blade 14 is first connected to an intermediate piece 16 by friction welding, in particular linear friction welding.
  • the intermediate piece 16 is made of a material other than the blade 14, for example of a polycrystalline material.
  • the blade 14 can then be attached to the rotor body 12 via the intermediate piece 16 by various methods.
  • a blade 14 is constructed as follows: radially inwardly a blade neck 18 is provided, from the blade neck 18, the blade 20 extends radially outward, at the outer end of the blade 20, an outer shroud 22 is provided.
  • the construction of the blade neck 18 is in the FIGS. 3 and 4 better to recognize.
  • a lightweight construction for the blade neck 18 is provided in the blade necks 18 .
  • recesses 24 are provided on the sides lying in the circumferential direction. Between adjacent blade necks 18 18 cavities 26 are formed by the recesses 24 in opposite sides of the blade necks (see FIG. 2 ). From each cavity 26, an inspection opening 28 extends radially inwardly and opens into a channel 30 extending in the axial direction. Each inspection opening 28 is assigned a channel 30.
  • the channels 30 are provided substantially between adjacent spacers 16.
  • the blade necks 18 each have a front and rear extension 32 in the axial direction.
  • the extensions 32 together form a running in the circumferential direction inner shroud 34.
  • the inner shroud 34 forms with adjacent rotors and optionally axial shrouds extending in the circumferential direction gap.
  • Such a space is formed in the axial direction in front of and behind the rotor base body 12, wherein this front and rear space is traversed by cooling fluid in order to cool the rotor 10 and in particular the rotor base body 12.
  • the channels 30 connect the front gap to the rear gap, thus allowing a flow of cooling fluid between the two spaces.
  • a cover plate 36 is arranged and fixed to the rotor base body 12.
  • the cover plate 36 forms a guide for the cooling fluid, wherein the cooling fluid is deflected in the present embodiment after flowing through the axially extending channels 30 in the radial direction to the outside.
  • a cover plate 36 is provided on the rear side of the rotor body 12.
  • a cover plate 36 may also be provided on the front side of the rotor main body or on both sides.
  • the gaps 38 are as narrow as possible in order not to reduce the efficiency of the turbomachine. The gaps 38 therefore do not provide access to the cavity 26 through which inspection of the cavity 26 would be possible.
  • the radially inwardly extending gap 38 may have a local enlargement, which forms the inspection opening 28.
  • the inspection opening 28 is increased relative to the gap 38 with respect to its width by a factor of at least three.
  • FIG. 2 shown detail view of the blade neck portion of the rotor 10 shows the cavity 26 and the inspection opening 28 enlarged.
  • the inspection opening 28 and the channel 30 are arranged and dimensioned so that it can be seen from the outside into the cavities 26 and thus a visual inspection can be performed.
  • inspection tools such as a lamp, light pipe or camera, may be routed through the channels 30 and the inspection openings 28 into the cavities 26.
  • the inspection openings 28 are closed by sealing elements 40.
  • the sealing elements 40 are cylindrical and made of a nickel-based material, they can also be coated, for example with a powder coating.
  • the sealing elements 40 fit against the blade necks 18 in a form-fitting manner and close off the inspection opening 28.
  • they are e.g. attached to the blade necks 18 by a press connection, positive connection, material connection or fastening means.
  • This press connection is releasable, so that the sealing elements 40 are removable from the blade necks 18, in particular to allow access to the inspection opening 28.
  • the sealing elements 40 extend over the entire axial length of the blade neck 18 and the adjacent intermediate pieces 16.
  • the arrangement of the sealing elements 40 and the cover plate 36 is coordinated so that a movement of the sealing elements 40 in the axial direction is limited by the cover plate 36.
  • the manufacture of the integrally bladed rotor 10 takes place, for example, according to the method described below.
  • the blades 14 are made in one piece, for example by a casting process.
  • the intermediate pieces 16 are connected to the blades 14 by linear friction welding, for example.
  • the blades 14 are now joined together to form a blade ring, wherein the recesses 24 each form a cavity 26 in opposite sides of adjacent blade necks 18.
  • the recesses 24 are designed so that from the radially inner side of an inspection opening 28 is formed in the cavity 26.
  • the vane ring is now connected to the rotor body 12, and the channels 30 are formed.
  • the cavities 26 of the integrally bladed rotor 10 are evaluated after the connection of the rotor base body 12 and blades 14 or blade ring via the inspection openings 28. After inspection, the sealing elements 40 are attached to the blade necks 18 and close the inspection openings 28th
  • the seal members 40 are removably attached.
  • the cover plate 36 is mounted to guide a flow of cooling fluid through the channels 30 and restrict axial movement of the seal member 40.

Description

Die Erfindung betrifft einen integral beschaufelten Rotor für eine Strömungsmaschine, insbesondere für eine Gasturbine, wobei Hohlräume im Bereich der Schaufelhälse zwischen benachbarten Schaufeln vorgesehen sind, die durch Ausnehmungen in gegenüberliegenden Seiten benachbarter Schaufelhälse gebildet sind.The invention relates to an integrally bladed rotor for a turbomachine, in particular for a gas turbine, wherein cavities are provided in the region of the blade necks between adjacent blades, which are formed by recesses in opposite sides of adjacent blade necks.

Rotoren mit integraler Beschaufelung bezeichnet man abhängig davon, ob ein im Querschnitt scheibenförmiger oder ein im Querschnitt ringförmiger Rotor bzw. Rotorträger (im Folgenden Rotorgrundkörper genannt) vorhanden ist, als Blisk bzw. Bling. Blisk ist die Kurzform von Bladed Disk und Bling von Bladed Ring.Rotors with integral blading are referred to as a blisk or bling, depending on whether there is a disk-shaped rotor or rotor with a cross-section in cross-section (referred to below as the rotor body). Blisk is the short form of Bladed Disk and Bling of Bladed Ring.

Aus dem Stand der Technik ist es bekannt, bei Rotoren mit integraler Beschaufelung Rotorgrundkörper und Schaufeln separat herzustellen und anschließend durch Reibschweißen miteinander zu verbinden. Um das Gewicht der Rotoren zu verringern, sind Leichtbauweisen mit Hohlräumen im Bereich der Schaufelhälse vorgesehen. In separat hergestellten Schaufeln sind Ausnehmungen in den in Umfangsrichtung weisenden Seiten vorgesehen. Bei der Herstellung des Rotors werden die vorgefertigten Schaufeln zu einem Schaufelkranz angeordnet, wobei die Ausnehmungen in den Schaufelhälsen benachbarter Schaufeln gegenüber liegen und somit zwischen benachbarten Schaufeln einen Hohlraum ausbilden, der mit dem Anschweißen des Rotorgrundkörpers an die Schaufeln verschlossen und unzugänglich ist. Ein solcher Rotor ist aus dem Dokument DE-A-10 361 882 bekannt. Aufgabe der Erfindung ist es, einen integral beschaufelten Rotor für eine Strömungsmaschine zu schaffen, der eine verbesserte Kontrollmöglichkeit bei Wartungsarbeiten ermöglicht.From the prior art, it is known to produce rotors with integral blading rotor body and blades separately and then to join together by friction welding. In order to reduce the weight of the rotors, lightweight structures with cavities in the area of the blade necks are provided. In separately manufactured blades recesses are provided in the circumferentially facing sides. In the manufacture of the rotor, the prefabricated blades are arranged to a blade ring, wherein the recesses in the blade necks of adjacent blades are opposite and thus form a cavity between adjacent blades, which is closed with the welding of the rotor body to the blades and inaccessible. Such a rotor is from the document DE-A-10 361 882 known. The object of the invention is to provide an integrally bladed rotor for a turbomachine, which allows improved control during maintenance.

Die Aufgabe wird durch einen erfindungsgemäßen integral beschaufelten Rotor für eine Strömungsmaschine, insbesondere für eine Gasturbine, gelöst. Im Bereich der Schaufelhälse sind Hohlräume zwischen benachbarten Schaufeln vorgesehen, die durch Ausnehmungen in gegenüberliegenden Seiten benachbarter Schaufelhälse gebildet sind. Von jedem Hohlraum verläuft eine Inspektionsöffnung radial nach innen, die von außen zugänglich ist und eine Untersuchung des Hohlraums von außen ermöglicht. Auf diese Weise wird eine Inspektion des Hohlraums ermöglicht, während der Hohlraum in den axialen Richtungen und in der radial nach außen verlaufenden Richtung möglichst gut abgedichtet ist.The object is achieved by an integrally bladed rotor according to the invention for a turbomachine, in particular for a gas turbine. In the area of the blade necks, cavities are provided between adjacent blades which are formed by recesses in opposite sides of adjacent blade necks. From each cavity extends an inspection opening radially inwardly, which is accessible from the outside and allows an examination of the cavity from the outside. In this way, an inspection of the cavity is made possible, while the cavity is sealed as well as possible in the axial directions and in the radially outward direction.

Gemäß einer bevorzugten Ausführungsform sind die Inspektionsöffnungen durch Dichtungselemente verschlossen. Nachdem eine Inspektion der Hohlräume, beispielsweise nach der Herstellung des Rotors oder in Wartungsintervallen, durchgeführt wurde, können die Inspektionsöffnungen somit verschlossen werden.According to a preferred embodiment, the inspection openings are closed by sealing elements. After an inspection of the cavities, for example, after the Manufacture of the rotor or maintenance intervals has been performed, the inspection openings can thus be closed.

Die Dichtungselemente können zylinderförmig sein. Dies ermöglicht eine einfache Geometrie der Dichtungselemente und der abzudichtenden Inspektionsöffnung.The sealing elements can be cylindrical. This allows a simple geometry of the sealing elements and the inspection opening to be sealed.

Vorzugsweise sind die Dichtungselemente aus einem Nickel-Basis-Werkstoff gefertigt. Dies ermöglicht eine temperaturbeständige Ausführung der Dichtungselemente.Preferably, the sealing elements are made of a nickel-based material. This allows a temperature-resistant design of the sealing elements.

Die Dichtungselemente können beschichtet sein. Somit werden die Oberflächeneigenschaften der Dichtungselemente verbessert und insbesondere auf die verwendeten Werkstoffe der Schaufeln angepasst.The sealing elements can be coated. Thus, the surface properties of the sealing elements are improved and adapted in particular to the materials used of the blades.

Vorzugsweise sind die Dichtungselemente separat hergestellte Teile, die durch Pressverbindung, Formschluss und/oder Schweißen an den Schaufelhälsen angebracht sind. Auf diese Weise wird eine gute Abdichtung der Inspektionsöffnungen durch die Dichtungselemente sichergestellt und einem Verrutschen der Dichtungselemente vorgebeugt.Preferably, the sealing elements are separately manufactured parts that are attached to the blade necks by press-fitting, positive locking and / or welding. In this way, a good seal of the inspection openings is ensured by the sealing elements and prevents slippage of the sealing elements.

Gemäß einer bevorzugten Ausführungsform sind die Dichtungselemente entfernbar an den Schaufelhälsen angebracht. Dies ermöglicht eine Inspektion der Hohlräume zu einem beliebigen Zeitpunkt.According to a preferred embodiment, the sealing elements are removably attached to the blade necks. This allows for inspection of the cavities at any one time.

Die Dichtungselemente erstrecken sich beispielsweise über die gesamte axiale Länge des zugeordneten Schaufelhalses. Somit wird eine Positionierung des Dichtungselements in axialer Richtung vereinfacht.The sealing elements extend for example over the entire axial length of the associated blade neck. Thus, a positioning of the sealing element in the axial direction is simplified.

Gemäß einer bevorzugten Ausführungsform mündet jede Inspektionsöffnung in einen in axialer Richtung verlaufenden Kanal. Dieser Kanal ermöglicht einen einfachen Zugang zur Inspektionsöffnung.According to a preferred embodiment, each inspection opening opens into a channel extending in the axial direction. This channel allows easy access to the inspection opening.

Der in axialer Richtung verlaufende Kanal kann ein Kühlfluidkanal sein. Dies schafft eine verbesserte Kühlung des Grenzbereichs zwischen Rotorgrundkörper und den Schaufelhälsen.The axially extending channel may be a cooling fluid channel. This provides improved cooling of the boundary between the rotor body and the blade necks.

Gemäß einer bevorzugten Ausführungsform ist eine Abdeckplatte in axialer Richtung stromauf- und/oder stromabwärts des Kanals angeordnet. Die Abdeckplatte oder die Abdeckplatten können den Kanal ganz oder teilweise abdecken, wodurch beispielsweise eine axiale Bewegung der Dichtungselemente verhindert oder eingeschränkt wird.According to a preferred embodiment, a cover plate is arranged in the axial direction upstream and / or downstream of the channel. The cover plate or the cover plates can cover the channel in whole or in part, whereby, for example, an axial movement of the sealing elements is prevented or limited.

Die Abdeckplatte kann eine Führung für das Kühlfluid bilden. Dies ermöglicht beispielsweise eine Umlenkung des Kühlfluidstroms aus der axialen Richtung des Kanals in eine radiale Richtung.The cover plate may form a guide for the cooling fluid. This allows, for example, a deflection of the cooling fluid flow from the axial direction of the channel in a radial direction.

Vorzugsweise sind die Kanäle und die Öffnungen so aufeinander abgestimmt, dass von außen in die Hohlräume hineingesehen werden kann. Dies ermöglicht eine einfache Inspektion der Hohlräume mit dem Auge oder einem Gerät.Preferably, the channels and the openings are coordinated so that it can be seen from the outside into the cavities. This allows easy inspection of the cavities with the eye or a device.

Jede Schaufel kann über ein aus einem anderen Material hergestelltes Zwischenstück an dem Rotorgrundkörper angeschweißt sein, und die Kanäle können zumindest zwischen benachbarten Zwischenstücken vorgesehen sein. Durch die Zwischenstücke lässt sich das Fügen der Schaufeln an den Rotorgrundkörper vereinfachen, insbesondere wenn die Schaufeln und der Rotorgrundkörper aus unterschiedlichen Materialien gefertigt sind, beispielsweise bei einkristallinen Schaufeln und polykristallinem Rotorgrundkörper oder bei unterschiedlichen Legierungen, bei denen ein Schmelzschweißverfahren nicht anwendbar ist.Each blade may be welded to the rotor body via an adapter made of a different material, and the channels may be provided at least between adjacent spacers. By means of the intermediate pieces, it is possible to simplify the joining of the blades to the rotor base body, in particular if the blades and the rotor base body are made of different materials, for example in monocrystalline blades and polycrystalline rotor base body or in different alloys in which a fusion welding process is not applicable.

Gemäß einer weiteren Ausführungsform sind benachbarte Schaufelhälse durch einen schmalen axial und radial verlaufenden Spalt voneinander getrennt und die Inspektionsöffnung durch eine lokale Vergrößerung des Spaltes gebildet. Dies kann beispielsweise auch bei einkristallinen Schaufeln der Fall sein, bei denen die Schaufeln nicht durch Schmelzschweißverfahren verbunden werden können.According to a further embodiment, adjacent blade necks are separated by a narrow axial and radial gap and the inspection opening is formed by a local enlargement of the gap. This may also be the case, for example, with monocrystalline vanes in which the vanes can not be joined by fusion welding.

Vorzugsweise weisen die Schaufelhälse Fortsätze auf, die gemeinsam ein in Umlaufrichtung verlaufendes Deckband bilden, wobei das Deckband mit benachbarten Rotoren und Deckbändern einen in Umfangsrichtung verlaufenden Zwischenraum bildet, welcher mit Kühlfluid durchströmt wird. Somit wird eine Kühlung der Rotoren ermöglicht.The blade necks preferably have extensions which together form a cover strip extending in the circumferential direction, wherein the cover strip with adjacent rotors and shrouds forms a circumferential space which is traversed by cooling fluid. Thus, a cooling of the rotors is possible.

Ein in axialer Richtung vorderer Zwischenraum und ein hinterer Zwischenraum können vorgesehen sein, wobei die in axialer Richtung verlaufenden Kanäle den vorderen Zwischenraum mit dem hinteren Zwischenraum verbinden. Auf diese Weise ergibt sich eine Strömung von Kühlfluid vom vorderen Zwischenraum in den hinteren Zwischenraum.An axially intermediate space and a rear space may be provided, wherein the axially extending channels connect the front space with the rear space. In this way, a flow of cooling fluid from the front gap results in the rear gap.

Weitere Merkmale und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung und aus den Zeichnungen, auf die Bezug genommen wird. In den Zeichnungen zeigen:

  • Figur 1 einen Sektor eines erfindungsgemäßen, integral beschaufelten Rotors mit Inspektionsöffnungen;
  • Figur 2 eine Detailansicht des in Figur 1 gezeigten Rotors;
  • Figur 3 den Sektor des Rotors aus Figur 1 in einer veränderten Perspektive;
  • Figur 4 den Sektor des Rotors gemäß Figur 3 mit eingesetzten Dichtungselementen; und
  • Figur 5 den Sektor des Rotors gemäß Figur 1 mit eingesetzten Dichtungselementen.
Further features and advantages of the invention will become apparent from the following description and from the drawings, to which reference is made. In the drawings show:
  • FIG. 1 a sector of an integrally bladed rotor according to the invention with inspection openings;
  • FIG. 2 a detailed view of the in FIG. 1 shown rotor;
  • FIG. 3 the sector of the rotor FIG. 1 in a changed perspective;
  • FIG. 4 the sector of the rotor according to FIG. 3 with inserted sealing elements; and
  • FIG. 5 the sector of the rotor according to FIG. 1 with inserted sealing elements.

Die Figuren 1 bis 5 zeigen einen Sektor eines integral beschaufelten Rotors 10. Der Rotor 10 weist einen Rotorgrundkörper 12 auf, der in der gezeigten Ausführungsform eine Rotorscheibe ist. Der Rotorgrundkörper 12 kann aber beispielsweise auch ringförmig sein.The FIGS. 1 to 5 show a sector of an integrally bladed rotor 10. The rotor 10 has a rotor body 12, which in the embodiment shown is a rotor disk. The rotor base body 12 may, however, also be annular, for example.

Der integral beschaufelte Rotor 10 ist für eine Gasturbine ausgelegt, wobei er im Turbinenabschnitt oder im Verdichterabschnitt angeordnet sein kann. Die Erfindung lässt sich natürlich auch auf integral beschaufelte Rotoren anderer Strömungsmaschinen anwenden.The integrally bladed rotor 10 is designed for a gas turbine and may be located in the turbine section or in the compressor section. Of course, the invention can also be applied to integrally bladed rotors of other turbomachines.

Am Außenradius des Rotorgrundkörpers 12 sind mehrere Schaufeln 14 vorgesehen, die z.B. über separate Zwischenstücke 16 mit dem Rotorgrundkörper 12 verbunden sind.At the outer radius of the rotor base body 12 a plurality of blades 14 are provided, which are e.g. are connected via separate intermediate pieces 16 with the rotor body 12.

Die Schaufeln 14 sind beispielsweise aus einkristallinen Nickel-Basis-Werkstoffen gefertigt, die keine Schmelzschweißverfahren erlauben. Eine Schaufel 14 wird zuerst durch Reibschweißen, insbesondere Linearreibschweißen, mit einem Zwischenstück 16 verbunden. Das Zwischenstück 16 ist dabei aus einem anderen Material als die Schaufel 14 gefertigt, beispielsweise aus einem polykristallinen Material. Die Schaufel 14 kann dann über das Zwischenstück 16 mit verschiedenen Verfahren am Rotorgrundkörper 12 befestigt werden.The blades 14 are made, for example, from single-crystalline nickel-based materials that do not allow fusion welding. A blade 14 is first connected to an intermediate piece 16 by friction welding, in particular linear friction welding. The intermediate piece 16 is made of a material other than the blade 14, for example of a polycrystalline material. The blade 14 can then be attached to the rotor body 12 via the intermediate piece 16 by various methods.

Eine Schaufel 14 ist wie folgt aufgebaut: radial innen liegend ist ein Schaufelhals 18 vorgesehen, vom Schaufelhals 18 erstreckt sich das Schaufelblatt 20 radial nach außen, am äußeren Ende des Schaufelblatts 20 ist ein äußeres Deckband 22 vorgesehen.A blade 14 is constructed as follows: radially inwardly a blade neck 18 is provided, from the blade neck 18, the blade 20 extends radially outward, at the outer end of the blade 20, an outer shroud 22 is provided.

Der Aufbau des Schaufelhalses 18 ist in den Figuren 3 und 4 besser zu erkennen. Um das Gewicht des Rotors 10 möglichst gering zu halten, ist eine Leichtbauweise für den Schaufelhals 18 vorgesehen. In den Schaufelhälsen 18 sind dabei auf den in Umfangsrichtung liegenden Seiten Ausnehmungen 24 vorgesehen. Zwischen benachbarten Schaufelhälsen 18 werden durch die Ausnehmungen 24 in gegenüberliegenden Seiten der Schaufelhälse 18 Hohlräume 26 gebildet (siehe Figur 2). Von jedem Hohlraum 26 verläuft eine Inspektionsöffnung 28 radial nach innen und mündet in einen in axialer Richtung verlaufenden Kanal 30. Jeder Inspektionsöffnung 28 ist dabei ein Kanal 30 zugeordnet. Die Kanäle 30 sind im Wesentlichen zwischen benachbarten Zwischenstücken 16 vorgesehen.The construction of the blade neck 18 is in the FIGS. 3 and 4 better to recognize. In order to keep the weight of the rotor 10 as low as possible, a lightweight construction for the blade neck 18 is provided. In the blade necks 18 recesses 24 are provided on the sides lying in the circumferential direction. Between adjacent blade necks 18 18 cavities 26 are formed by the recesses 24 in opposite sides of the blade necks (see FIG. 2 ). From each cavity 26, an inspection opening 28 extends radially inwardly and opens into a channel 30 extending in the axial direction. Each inspection opening 28 is assigned a channel 30. The channels 30 are provided substantially between adjacent spacers 16.

Die Schaufelhälse 18 weisen jeweils einen in axialer Richtung vorderen und hinteren Fortsatz 32 auf. Die Fortsätze 32 bilden gemeinsam ein in Umlaufrichtung verlaufendes inneres Deckband 34. Das innere Deckband 34 bildet mit benachbarten Rotoren und gegebenenfalls axialen Deckbändern einen in Umfangsrichtung verlaufenden Zwischenraum. Ein solcher Zwischenraum bildet sich in axialer Richtung vor und hinter dem Rotorgrundkörper 12 aus, wobei dieser vordere und hintere Zwischenraum mit Kühlfluid durchströmt wird, um den Rotor 10 und insbesondere den Rotorgrundkörper 12 zu kühlen.The blade necks 18 each have a front and rear extension 32 in the axial direction. The extensions 32 together form a running in the circumferential direction inner shroud 34. The inner shroud 34 forms with adjacent rotors and optionally axial shrouds extending in the circumferential direction gap. Such a space is formed in the axial direction in front of and behind the rotor base body 12, wherein this front and rear space is traversed by cooling fluid in order to cool the rotor 10 and in particular the rotor base body 12.

Die Kanäle 30 verbinden den vorderen Zwischenraum mit dem hinteren Zwischenraum und ermöglichen somit einen Fluss von Kühlfluid zwischen den beiden Zwischenräumen. Auf der in axialer Richtung hinteren (stromabwärtigen) Seite des Rotors 10 ist eine Abdeckplatte 36 angeordnet und am Rotorgrundkörper 12 befestigt. Die Abdeckplatte 36 bildet eine Führung für das Kühlfluid, wobei das Kühlfluid in der vorliegenden Ausführungsform nach dem Durchströmen der in axialer Richtung verlaufenden Kanäle 30 in radialer Richtung nach außen umgelenkt wird. In der gezeigten Ausführungsform ist eine Abdeckplatte 36 auf der hinteren Seite des Rotorgrundkörpers 12 vorgesehen. Eine Abdeckplatte 36 kann natürlich auch auf der vorderen Seite des Rotorgrundkörpers oder auf beiden Seiten vorgesehen sein.The channels 30 connect the front gap to the rear gap, thus allowing a flow of cooling fluid between the two spaces. On the axially rearward (downstream) side of the rotor 10, a cover plate 36 is arranged and fixed to the rotor base body 12. The cover plate 36 forms a guide for the cooling fluid, wherein the cooling fluid is deflected in the present embodiment after flowing through the axially extending channels 30 in the radial direction to the outside. In the embodiment shown, a cover plate 36 is provided on the rear side of the rotor body 12. Of course, a cover plate 36 may also be provided on the front side of the rotor main body or on both sides.

Aufgrund der Konstruktion der Schaufeln 14 und des Rotors 10 ist es möglich, dass zwischen benachbarten Schaufelhälsen 18 schmale axial und radial verlaufende Spalte 38 (siehe Figur 2) vorkommen. Die Spalte 38 sind möglichst schmal ausgebildet, um die Leistungsfähigkeit der Strömungsmaschine nicht zu verringern. Die Spalte 38 bilden daher keinen Zugang zum Hohlraum 26, durch den eine Inspektion des Hohlraums 26 möglich wäre.Due to the construction of the blades 14 and the rotor 10, it is possible for narrow axial and radial gaps 38 (see FIG. 4) between adjacent blade necks 18 FIG. 2 ) occurrence. The gaps 38 are as narrow as possible in order not to reduce the efficiency of the turbomachine. The gaps 38 therefore do not provide access to the cavity 26 through which inspection of the cavity 26 would be possible.

Der radial innen verlaufende Spalt 38 kann eine lokale Vergrößerung aufweisen, die die Inspektionsöffnung 28 bildet. Die Inspektionsöffnung 28 ist gegenüber dem Spalt 38 bezüglich ihrer Breite um einen Faktor von mindestens drei vergrößert.The radially inwardly extending gap 38 may have a local enlargement, which forms the inspection opening 28. The inspection opening 28 is increased relative to the gap 38 with respect to its width by a factor of at least three.

Die in Figur 2 gezeigte Detailansicht des Schaufelhalsabschnitts des Rotors 10 zeigt den Hohlraum 26 und die Inspektionsöffnung 28 vergrößert. Die Inspektionsöffnung 28 und der Kanal 30 sind dabei so angeordnet und dimensioniert, dass von außen in die Hohlräume 26 hineingesehen werden kann und somit eine visuelle Inspektion durchgeführt werden kann. Alternativ können Inspektionswerkzeuge, beispielsweise eine Lampe, Lichtleiter oder eine Kamera, durch die Kanäle 30 und die Inspektionsöffnungen 28 in die Hohlräume 26 geführt werden.In the FIG. 2 shown detail view of the blade neck portion of the rotor 10 shows the cavity 26 and the inspection opening 28 enlarged. The inspection opening 28 and the channel 30 are arranged and dimensioned so that it can be seen from the outside into the cavities 26 and thus a visual inspection can be performed. Alternatively, inspection tools, such as a lamp, light pipe or camera, may be routed through the channels 30 and the inspection openings 28 into the cavities 26.

In den Figuren 4 und 5 sind die Inspektionsöffnungen 28 durch Dichtungselemente 40 verschlossen. Die Dichtungselemente 40 sind zylinderförmig und aus einem Nickel-Basis-Werkstoff gefertigt, sie können auch beschichtet sein, beispielsweise mit einer Pulverbeschichtung.In the FIGS. 4 and 5 the inspection openings 28 are closed by sealing elements 40. The sealing elements 40 are cylindrical and made of a nickel-based material, they can also be coated, for example with a powder coating.

Die Dichtungselemente 40 liegen formschlüssig an den Schaufelhälsen 18 an und verschließen die Inspektionsöffnung 28. Um ein Verrutschen der Dichtungselemente 40 zu verhindern, sind sie z.B. durch eine Pressverbindung, Formschluss, Stoffschluss oder Befestigungsmittel an den Schaufelhälsen 18 befestigt. Diese Pressverbindung ist lösbar, sodass die Dichtungselemente 40 von den Schaufelhälsen 18 entfernbar sind, insbesondere um einen Zugang zur Inspektionsöffnung 28 zu ermöglichen.The sealing elements 40 fit against the blade necks 18 in a form-fitting manner and close off the inspection opening 28. In order to prevent the sealing elements 40 from slipping, they are e.g. attached to the blade necks 18 by a press connection, positive connection, material connection or fastening means. This press connection is releasable, so that the sealing elements 40 are removable from the blade necks 18, in particular to allow access to the inspection opening 28.

Die Dichtungselemente 40 erstrecken sich über die gesamte axiale Länge des Schaufelhalses 18 und der angrenzenden Zwischenstücke 16. Die Anordnung der Dichtungselemente 40 und der Abdeckplatte 36 ist so aufeinander abgestimmt, dass eine Bewegung der Dichtungselemente 40 in axialer Richtung durch die Abdeckplatte 36 beschränkt wird.The sealing elements 40 extend over the entire axial length of the blade neck 18 and the adjacent intermediate pieces 16. The arrangement of the sealing elements 40 and the cover plate 36 is coordinated so that a movement of the sealing elements 40 in the axial direction is limited by the cover plate 36.

Die Herstellung des integral beschaufelten Rotors 10 erfolgt beispielsweise nach dem im Folgenden beschriebenen Verfahren. Die Schaufeln 14 werden einstückig hergestellt, beispielsweise durch ein Gussverfahren. Die Zwischenstücke 16 werden beispielsweise durch Linearreibschweißen mit den Schaufeln 14 verbunden. Die Schaufeln 14 werden nun zu einem Schaufelkranz zusammengefügt, wobei die Ausnehmungen 24 in gegenüberliegenden Seiten benachbarter Schaufelhälse 18 jeweils einen Hohlraum 26 bilden. Die Ausnehmungen 24 sind dabei so ausgeführt, dass aus der radial innen liegenden Seite eine Inspektionsöffnung 28 in den Hohlraum 26 gebildet wird. Der Schaufelkranz wird nun mit dem Rotorgrundkörper 12 verbunden, und die Kanäle 30 werden ausgebildet.The manufacture of the integrally bladed rotor 10 takes place, for example, according to the method described below. The blades 14 are made in one piece, for example by a casting process. The intermediate pieces 16 are connected to the blades 14 by linear friction welding, for example. The blades 14 are now joined together to form a blade ring, wherein the recesses 24 each form a cavity 26 in opposite sides of adjacent blade necks 18. The recesses 24 are designed so that from the radially inner side of an inspection opening 28 is formed in the cavity 26. The vane ring is now connected to the rotor body 12, and the channels 30 are formed.

Die Hohlräume 26 des integral beschaufelten Rotors 10 werden nach der Verbindung von Rotorgrundkörper 12 und Schaufeln 14 bzw. Schaufelkranz über die Inspektionsöffnungen 28 befundet. Nach erfolgter Inspektion werden die Dichtungselemente 40 an den Schaufelhälsen 18 angebracht und verschließen die Inspektionsöffnungen 28.The cavities 26 of the integrally bladed rotor 10 are evaluated after the connection of the rotor base body 12 and blades 14 or blade ring via the inspection openings 28. After inspection, the sealing elements 40 are attached to the blade necks 18 and close the inspection openings 28th

Falls weitere Inspektionen der Hohlräume 26 zu späteren Zeitpunkten möglich sein sollen, so werden die Dichtungselemente 40 entfernbar angebracht.If further inspections of the cavities 26 are to be possible at later times, the seal members 40 are removably attached.

Die Abdeckplatte 36 wird zur Führung eines Kühlfluidstroms durch die Kanäle 30 und zur Beschränkung einer axialen Bewegung des Dichtungselements 40 montiert.The cover plate 36 is mounted to guide a flow of cooling fluid through the channels 30 and restrict axial movement of the seal member 40.

Claims (16)

  1. Integrally bladed rotor (10) for a fluid-flow machine, in particular for a gas turbine, wherein cavities (26) have been provided in the region of the blade necks (18) between adjacent blades (14), which have been formed by recesses (24) in opposite sides of adjacent blade necks (18), wherein an inspection aperture (28) extends radially inwards from each cavity (26), said aperture being accessible from outside and enabling an examination of the cavity (26) from outside, and wherein the inspection apertures (28) have been closed by sealing elements (40).
  2. Rotor according to Claim 1, characterised in that the sealing elements (40) are cylindrical.
  3. Rotor according to Claim 1 or 2, characterised in that the sealing elements (40) have been manufactured from a nickel-based material.
  4. Rotor according to one of Claims 1 to 3, characterised in that the sealing elements (40) has been coated.
  5. Rotor according to one of Claims 1 to 4, characterised in that the sealing elements (40) are separately produced parts which have been attached to the blade necks (18) by press connection, form closure and/or welding.
  6. Rotor according to one of Claims 1 to 5, characterised in that the sealing elements (40) have been removably attached to the blade necks (18).
  7. Rotor according to one of Claims 1 to 6, characterised in that the sealing elements (40) extend over the entire axial length of the assigned blade neck (18).
  8. Rotor according to one of the preceding claims, characterised in that each inspection aperture (28) leads into a duct (30) extending axially.
  9. Rotor according to Claim 8, characterised in that the duct (30) extending in the axial direction is a cooling-fluid duct.
  10. Rotor according to Claim 8 or 9, characterised in that a cover plate (36) has been arranged in the axial direction upstream and/or downstream of the duct (30).
  11. Rotor according to Claims 9 and 10, characterised in that the cover plate (36) forms a guide for the cooling fluid.
  12. Rotor according to one of Claims 8 to 11, characterised in that the ducts (30) and the inspection apertures (28) have been matched to one another in such a way that it is possible to see into the cavities (26) from outside.
  13. Rotor according to one of Claims 8 to 12, characterised in that each blade (14) has been welded to the rotor body (12) via an intermediate piece (16) produced from a different material and in that the ducts (30) have been provided at least between adjacent intermediate pieces (16).
  14. Rotor according to one of the preceding claims, characterised in that the blade necks (18) exhibit extensions (32) which jointly form a shroud band extending in the direction of revolution, whereby the shroud band forms with adjacent rotors and shroud bands an interspace extending in the circumferential direction, which is flowed through by cooling fluid.
  15. Rotor according to one of Claims 8 to 13 and according to Claim 15, characterised in that an anterior interspace in the axial direction and a posterior interspace have been provided, whereby the ducts (30) extending in the axial direction connect the anterior interspace to the posterior interspace.
  16. Rotor according to one of the preceding claims, characterised in that adjacent blade necks (18) have been separated from one another by a narrow gap (38) extending axially and radially, and the inspection aperture (28) forms a local enlargement of the gap (38).
EP10713552.7A 2009-03-05 2010-02-27 Integrally bladed rotor for a turbomachine Not-in-force EP2404037B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200910011965 DE102009011965A1 (en) 2009-03-05 2009-03-05 Integrally bladed rotor for a turbomachine
PCT/DE2010/000222 WO2010099783A1 (en) 2009-03-05 2010-02-27 Integrally bladed rotor for a turbomachine

Publications (2)

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EP2404037A1 EP2404037A1 (en) 2012-01-11
EP2404037B1 true EP2404037B1 (en) 2014-12-10

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Application Number Title Priority Date Filing Date
EP10713552.7A Not-in-force EP2404037B1 (en) 2009-03-05 2010-02-27 Integrally bladed rotor for a turbomachine

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EP (1) EP2404037B1 (en)
DE (1) DE102009011965A1 (en)
WO (1) WO2010099783A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2514923A1 (en) 2011-04-18 2012-10-24 MTU Aero Engines GmbH Screen device, integrated bladed rotor base body, method and fluid flow engine
EP2520768A1 (en) * 2011-05-02 2012-11-07 MTU Aero Engines AG Sealing device for an integrated bladed rotor base body of a turbomachine
EP2586969B1 (en) * 2011-10-28 2020-03-25 United Technologies Corporation Spoked Rotor for a Gas Turbine Engine
US9938831B2 (en) 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2831958A (en) * 1955-12-01 1958-04-22 Gen Electric Bladed rotor
US3262674A (en) * 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
IT1025260B (en) * 1973-11-16 1978-08-10 Mtu Muenchen Gmbh TURBINE WITH INTERNAL COOLING OF THE CROWN AND WITH PRESCRIBED POSITIONS OF BREAKAGE
DE19801804C2 (en) * 1998-01-19 1999-10-28 Siemens Ag Turbine blade and method for inspecting and / or cleaning a turbine blade
DE10361882B4 (en) * 2003-12-19 2013-08-22 Rolls-Royce Deutschland Ltd & Co Kg Rotor for the high-pressure turbine of an aircraft engine
US7758311B2 (en) * 2006-10-12 2010-07-20 General Electric Company Part span shrouded fan blisk
US7887299B2 (en) * 2007-06-07 2011-02-15 Honeywell International Inc. Rotary body for turbo machinery with mistuned blades
DE102007037208B4 (en) * 2007-08-07 2013-06-20 Mtu Aero Engines Gmbh Turbine blade with at least one insert sleeve for cooling the turbine blade
US9133720B2 (en) * 2007-12-28 2015-09-15 United Technologies Corporation Integrally bladed rotor with slotted outer rim

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EP2404037A1 (en) 2012-01-11
WO2010099783A1 (en) 2010-09-10
DE102009011965A1 (en) 2010-09-09

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