EP2460979B1 - Blade segment of a flow engine with radial support surfaces - Google Patents

Blade segment of a flow engine with radial support surfaces Download PDF

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Publication number
EP2460979B1
EP2460979B1 EP10193687A EP10193687A EP2460979B1 EP 2460979 B1 EP2460979 B1 EP 2460979B1 EP 10193687 A EP10193687 A EP 10193687A EP 10193687 A EP10193687 A EP 10193687A EP 2460979 B1 EP2460979 B1 EP 2460979B1
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EP
European Patent Office
Prior art keywords
blade
contact surface
counter
shroud
blade segment
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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EP10193687A
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German (de)
French (fr)
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EP2460979A1 (en
Inventor
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Priority to EP10193687A priority Critical patent/EP2460979B1/en
Priority to ES10193687T priority patent/ES2401350T3/en
Priority to US13/310,939 priority patent/US20120141259A1/en
Publication of EP2460979A1 publication Critical patent/EP2460979A1/en
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Publication of EP2460979B1 publication Critical patent/EP2460979B1/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
    • F01D5/12—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

Definitions

  • the present invention relates to a blade segment and a turbomachine.
  • the object of the present invention is to provide an alternative or complementary approach, which provides a coupling between at least two blades of a blade segment in order to achieve a favorable damping behavior.
  • a vane segment for a turbomachine comprising: a first vane; a first shroud connected to the tip of the first blade and having a bearing surface; a second blade; and a second, connected to the tip of the second blade second shroud, which has a counter-contact surface for a concern of the contact surface of the first shroud in the radial direction such that a frictional engagement between the contact surface and the counter-contact surface can be generated; provided.
  • turbomachine in particular turbomachine, is provided with the blade segment according to the invention.
  • the idea underlying the present invention is to arrange the shrouds of the respective blades like a roof tile, so that the shrouds in the radial direction against each other so that at least during operation of the blade segment (or even at a standstill) formed a frictional engagement between overlapping shrouds becomes.
  • the frictional engagement ensures a coupling of the shrouds or the blades with each other, which is favorable in terms of a damping behavior.
  • circumferential direction means a direction along a circular line which has the axis of rotation of the blade segment in the turbomachine as the central axis.
  • radial refers to a direction perpendicular to the axis of rotation of the blade segment in the turbomachine.
  • axial refers to a direction along the axis of rotation of the blade segment in the turbomachine.
  • the center of gravity of the first shroud is circumferentially spaced from a central axis of the first blade so that the first blade flexes under the action of the centrifugal forces during operation of the blade segment to produce the frictional engagement between the abutment surface and the opposing abutment surface.
  • a bending moment thus arises under the action of the centrifugal forces which tends to tip the blade together with the shroud in the circumferential direction. But this tilting is prevented by means of the contact surface of the first shroud and the counter-bearing surface of the second shroud.
  • the contact surface presses in the radial direction against the counter-contact surface in such a way that frictional engagement occurs between the contact surface and the counter-contact surface.
  • central axis herein is meant the axis of the first blade positioned such that, if the center of gravity of the first shroud were coincident therewith, no or only a negligible bending moment would be introduced from the shroud into the first blade. The same applies to the central axis of the second blade.
  • the contact surface of the first shroud and / or the counter-bearing surface of the second shroud with a pressing dimension formed in the radial direction for bending the first blade about its base in the circumferential direction, thereby generating the frictional engagement between the abutment surface and the counter abutment surface.
  • a pressing dimension is meant that the contact surface and / or counter-contact surface is thickened in the radial direction, thereby generating a surface pressure and thus a frictional engagement between the contact surface and the counter-contact surface.
  • the frictional engagement is designed to generate a torsional reaction torque in one direction about the central axis of the first and the second blade. This is favorable for compensating for the tendency to unwind of radially twisted blade profiles.
  • the first and / or second blade on a basic inclination in the axial direction which is defined by a base inclination axis, wherein the contact surface and counter-bearing surface obliquely, in particular at an angle between 45 and 135 degrees, with respect Base pitch axis in the axial direction of the first and the second blade are arranged.
  • the basic inclination is also called “lean”.
  • the basic inclination usually serves to largely compensate for the gas forces which occur during operation of the turbomachine and which generate corresponding bending moments on the blades, at least in certain operating regions of the turbomachine.
  • the base inclination is usually between 0 and 2 degrees depending on the configuration of the turbomachine.
  • the oblique arrangement of contact surface and counter-bearing surface causes a torsional moment about the central axis of a respective blade is created, which can counteract a unwinding of a respective blade.
  • This torsional moment increases, the more the contact surface presses against the counter-contact surface.
  • the abutment surfaces and counter abutment surfaces on an engagement element and a receiving element which engage in one another in the circumferential direction.
  • this embodiment prevents unwinding of the blades when no frictional engagement is generated (For example, at standstill of the blade segment in the embodiment with the offset in the circumferential direction center of gravity of the shroud).
  • the first and / or second blade is torsionsvorgespannt. If the blades engage with each other by means of the above-described engaging and receiving elements, it is possible, for example, to bias the blades torsionally so that sufficient coupling between the blades is achieved even at low rotational speeds, which brings about a favorable damping behavior. The frictional engagement due to the offset of the center of gravity of a respective shroud may not be sufficient at the low speeds to achieve such sufficient coupling between the shrouds.
  • the first and second blades are designed as moving blades.
  • the first and second blades are made of a strong creeping material.
  • strong creeping materials are meant those materials that crawl more than current nickel materials.
  • FIG. 1 As seen in the axial direction, schematically shows a blade segment 1 according to an embodiment of the present invention.
  • the blade segment 1 is part of a turbomachine, in particular a turbomachine, which is generally designated 2.
  • the turbomachine is preferably an aircraft engine.
  • the blade segment 1 has two blades 3 and 3 'on the blades 3, 3' are preferably formed as blades.
  • the blades 3, 3 ' are with their respective feet 4, 4' in a rotor 5, see FIG. 4 , For example by means of a Christmas tree connection, attached.
  • the rotor 5 rotates about an axis 6, wherein the blades 3, 3 'interact with a fluid flowing through the turbomachine 2.
  • the terms "in the circumferential direction”, “in the radial direction” and “in the axial direction” refer hereinafter to the axis 6. It should be noted that the axis 6 is located in reality much further away from the blades 3, 3 ', as in FIG. 1 shown.
  • the blades 3, 3 ' are each connected to shrouds 7, 7'.
  • the shrouds 7, 7 'each have a center of gravity S, S', which has a distance D, D 'on a central axis M, M' of a respective blade 3, 3 '.
  • the central axes M, M 'each extend through the axis 6, which due to the highly schematic representation in FIG. 1 is not recognizable.
  • the central axis M extends through a center of gravity SB of the blade 3, see FIG. 2 ,
  • the center of gravity SB is the center of gravity of the profile of the blade 3. The same applies to the central axis M 'of the blade 3'.
  • a respective shroud 7, 7 ' has a contact surface 11, 11' and a counter-contact surface 12, 12 'lying opposite it.
  • the contact surfaces 11, 11 'and counter-contact surfaces 12, 12' may each be formed at the ends of the shrouds 7, 7 'in the circumferential direction U.
  • FIG. 2 shows a section A-A from FIG. 1.
  • FIG. 3 shows a section B-B from FIG. 1.
  • "Sloping" means an angle W 'other than 90 degrees and preferably between 45 and 135 Degree.
  • the base inclination axis G 'of the blade 3' may be inclined for example by 1 degree in the direction of the axis of rotation 6.
  • a contact pressure AK results between the contact surface 11 and the counter-contact surface 12 '. Due to the oblique arrangement of the contact surface 11 and the counter-contact surface 12 ', the contact force AK results in a reaction force RK1 and a reaction force RK2, which act on the blade 3. RK2 acts along the base pitch axis G 'and RK1 perpendicular thereto.
  • RK1 is also in FIG. 2 shown. Here it can be seen that RK1 generates an additional torsional moment TR about the center of gravity SB or the center axis M of the blade 3, which counteracts a winding E of the blade 3.
  • FIG. 4 1 shows the vane segment FIG. 1 in a perspective view obliquely from below.
  • the shrouds 7, 7 'at their opposite ends preferably in the region of the contact surfaces 11, 11' and counter-bearing surfaces 12, 12 'engaging elements 13, 13' and receiving elements 14, 14 'on.
  • the engagement element 13 'of the shroud 7' engages in the circumferential direction in the receiving element 14 of the shroud 7 a. This results in a form fit in the axial direction, which unwinding of the blades 3, 3 'at a standstill of the blade segment 1 or at low speeds, where the frictional engagement RF is still too low to couple the blades 3, 3' together prevented ,
  • Fig. 5 As seen in the axial direction, schematically shows a blade segment 1 according to another embodiment of the present invention.
  • the blade segment 1 differs from that according to the Fig. 1 to 4 only in the way the friction fit RF is generated. Incidentally, therefore, the comments on the Fig. 1 to 4 according to the blade segment Fig. 5 ,
  • the frictional engagement RF in the embodiment according to Fig. 5 is advantageous not or only slightly dependent on speed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die vorliegende Erfindung betrifft ein Schaufelsegment sowie eine Strömungsmaschine.The present invention relates to a blade segment and a turbomachine.

Beispielsweise ist es aus der Druckschrift JP 2007154695 A bekannt, Turbinenschaufeln torsionsvorzuspannen. Dies wirkt sich im Betrieb der Turbinenschaufeln im Hinblick auf ein Dämpfungsverhalten derselben günstig aus. Die Torsionsvorspannung wird dadurch aufrechterhalten, dass die Turbinenschaufeln an ihren Schaufelspitzen jeweils Deckbänder aufweisen, welche über eine Z-Verklinkung miteinander verspannt sind. Diese Z-Verklinkung wird auch als "Z-shroud" bezeichnet.For example, it is from the document JP 2007154695 A known to torsionally bias turbine blades. This has a favorable effect on the operation of the turbine blades with respect to a damping behavior thereof. The Torsionsvorspannung is maintained by the fact that the turbine blades each have shrouds at their blade tips, which are clamped together via a Z-latching. This Z-latching is also called "Z-shroud".

Aufgabe der vorliegenden Erfindung ist es, einen alternativen oder ergänzenden Ansatz bereitzustellen, welcher eine Kopplung zwischen wenigstens zwei Schaufeln eines Schaufelsegments vorsieht, um ein günstiges Dämpfungsverhalten zu erzielen.The object of the present invention is to provide an alternative or complementary approach, which provides a coupling between at least two blades of a blade segment in order to achieve a favorable damping behavior.

Diese Aufgabe wird gelöst durch ein Schaufelsegment mit Merkmalen des Patentanspruchs 1 sowie durch eine Strömungsmaschine mit dem Merkmal des Patentanspruchs 10.This object is achieved by a blade segment having features of patent claim 1 and by a turbomachine having the feature of claim 10.

Demgemäß wird ein Schaufelsegment für eine Strömungsmaschine, aufweisend: eine erste Schaufel; ein erstes, mit der Spitze der ersten Schaufel verbundenes Deckband, welches eine Anlagefläche aufweist; eine zweite Schaufel; und ein zweites, mit der Spitze der zweiten Schaufel verbundenes zweites Deckband, welches eine Gegenanlagefläche für ein Anliegen der Anlagefläche des ersten Deckbandes in radialer Richtung derart aufweist, dass ein Reibschluss zwischen der Anlagefläche und der Gegenanlagefläche erzeugbar ist; bereitgestellt.Accordingly, a vane segment for a turbomachine comprising: a first vane; a first shroud connected to the tip of the first blade and having a bearing surface; a second blade; and a second, connected to the tip of the second blade second shroud, which has a counter-contact surface for a concern of the contact surface of the first shroud in the radial direction such that a frictional engagement between the contact surface and the counter-contact surface can be generated; provided.

Weiterhin wird eine Strömungsmaschine, insbesondere Turbomaschine, mit dem erfindungsgemäßen Schaufelsegment bereitgestellt.Furthermore, a turbomachine, in particular turbomachine, is provided with the blade segment according to the invention.

Die der vorliegenden Erfindung zugrunde liegende Idee besteht darin, die Deckbänder der jeweiligen Schaufeln dachziegelartig anzuordnen, sodass die Deckbänder in der radialen Richtung derart gegeneinander anliegen, dass zumindest im Betrieb des Schaufelsegments (oder auch im Stillstand desselben) ein Reibschluss zwischen einander überlappenden Deckbändern gebildet wird. Der Reibschluss sorgt für ein Kopplung der Deckbänder bzw. der Schaufeln miteinander, was im Hinblick auf ein Dämpfungsverhalten günstig ist.The idea underlying the present invention is to arrange the shrouds of the respective blades like a roof tile, so that the shrouds in the radial direction against each other so that at least during operation of the blade segment (or even at a standstill) formed a frictional engagement between overlapping shrouds becomes. The frictional engagement ensures a coupling of the shrouds or the blades with each other, which is favorable in terms of a damping behavior.

Aus den Unteransprüchen ergeben sich vorteilhafte Ausgestaltungen.From the subclaims advantageous embodiments result.

Unter dem Anliegen der Anlagefläche gegen die Gegenanlagefläche in der radialen Richtung ist vorliegend zu verstehen, dass ein Vektor senkrecht auf die Ebene, in welcher die Anlagefläche und die Gegenanlagefläche gegeneinander anliegen, zumindest eine radiale Komponente auf weist.The concern of the contact surface against the counter-contact surface in the radial direction is to be understood here that a vector perpendicular to the plane in which abut the abutment surface and the counter-contact surface against each other, has at least one radial component.

"Umfangsrichtung" meint vorliegend eine Richtung entlang einer Kreislinie, welche die Drehachse des Schaufelsegments in der Strömungsmaschine als Mittelachse besitzt. "Radial" bezieht sich vorliegend auf eine Richtung senkrecht zu der Drehachse des Schaufelsegments in der Strömungsmaschine. "Axial" bezieht sich vorliegend auf eine Richtung entlang der Drehachse des Schaufelsegments in der Strömungsmaschine.In this case, "circumferential direction" means a direction along a circular line which has the axis of rotation of the blade segment in the turbomachine as the central axis. In this case, "radial" refers to a direction perpendicular to the axis of rotation of the blade segment in the turbomachine. In the present case, "axial" refers to a direction along the axis of rotation of the blade segment in the turbomachine.

Gemäß einer Ausgestaltung des erfindungsgemäßen Schaufelsegments ist der Schwerpunkt des ersten Deckbandes in Umfangsrichtung von einer Mittelachse der ersten Schaufel derart beabstandet angeordnet, dass sich die erste Schaufel unter Einwirkung der Fliehkräfte im Betrieb des Schaufelsegments für das Erzeugen des Reibschlusses zwischen der Anlagefläche und der Gegenanlagefläche verbiegt. Im Betrieb des Schaufelsegments entsteht also unter Einwirkung der wirkenden Fliehkräfte ein Biegemoment, welches dazu tendiert, die Schaufel samt dem Deckband in Umfangsrichtung zu kippen. Dieses Kippen wird aber mittels der Anlagefläche des ersten Deckbands und der Gegenanlagefläche des zweiten Deckbands verhindert. Die Anlagefläche drückt dabei in der radialen Richtung derart gegen die Gegenanlagefläche, dass es zu einem Reibschluss zwischen der Anlagefläche und der Gegenanlagefläche kommt.According to one embodiment of the blade segment according to the invention, the center of gravity of the first shroud is circumferentially spaced from a central axis of the first blade so that the first blade flexes under the action of the centrifugal forces during operation of the blade segment to produce the frictional engagement between the abutment surface and the opposing abutment surface. During operation of the blade segment, a bending moment thus arises under the action of the centrifugal forces which tends to tip the blade together with the shroud in the circumferential direction. But this tilting is prevented by means of the contact surface of the first shroud and the counter-bearing surface of the second shroud. The contact surface presses in the radial direction against the counter-contact surface in such a way that frictional engagement occurs between the contact surface and the counter-contact surface.

Mit "Mittelachse" ist vorliegend die Achse der ersten Schaufel gemeint, die derart positioniert ist, dass, wenn der Schwerpunkt des ersten Deckbands, mit dieser koinzident angeordnet wäre, kein oder nur ein unwesentliches Biegemoment aus dem Deckband in die erste Schaufel eingeleitet werden würde. Entsprechendes gilt für die Mittelachse der zweiten Schaufel.By "central axis" herein is meant the axis of the first blade positioned such that, if the center of gravity of the first shroud were coincident therewith, no or only a negligible bending moment would be introduced from the shroud into the first blade. The same applies to the central axis of the second blade.

Gemäß einer Ausgestaltung des erfindungsgemäßen Schaufelsegments ist die Anlagefläche des ersten Deckbandes und/oder die Gegenanlagefläche des zweiten Deckbandes mit einem Pressmaß in radialer Richtung für ein Verbiegen der ersten Schaufel um deren Fußpunkt in der Umfangsrichtung gebildet, um dadurch den Reibschlusses zwischen der Anlagefläche und der Gegenanlagefläche zu erzeugen. Mit einem Pressmaß ist gemeint, dass die Anlagefläche und/oder Gegenanlagefläche in der radialen Richtung aufgedickt ist, um dadurch eine Flächenpressung und damit einen Reibschluss zwischen der Anlagefläche und der Gegenanlagefläche zu erzeugen. Diese Ausgestaltung kann alternativ oder zusätzlich zu der vorhergehenden Ausgestaltung vorgesehen werden, bei welcher der Schwerpunkt des ersten Deckbandes in Umfangsrichtung von einer Mittelachse der ersten Schaufel derart beabstandet angeordnet.According to one embodiment of the blade segment according to the invention, the contact surface of the first shroud and / or the counter-bearing surface of the second shroud with a pressing dimension formed in the radial direction for bending the first blade about its base in the circumferential direction, thereby generating the frictional engagement between the abutment surface and the counter abutment surface. By a pressing dimension is meant that the contact surface and / or counter-contact surface is thickened in the radial direction, thereby generating a surface pressure and thus a frictional engagement between the contact surface and the counter-contact surface. This embodiment can be provided as an alternative or in addition to the previous embodiment, in which the center of gravity of the first shroud arranged in the circumferential direction of a central axis of the first blade so spaced.

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments ist der Reibschluss dazu ausgebildet, ein Torsionsreaktionsmoment in einer Richtung um die Mittelachse der ersten und der zweiten Schaufel zu erzeugen. Dies ist zur Kompensation der Entwindungsneigung von radial verdrehten Laufschaufelprofilen günstig.According to a further embodiment of the blade segment according to the invention, the frictional engagement is designed to generate a torsional reaction torque in one direction about the central axis of the first and the second blade. This is favorable for compensating for the tendency to unwind of radially twisted blade profiles.

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments weisen die erste und/oder zweite Schaufel eine Grundneigung in axialer Richtung auf, welche durch eine Grundneigungsachse definiert ist, wobei die Anlagefläche und Gegenanlagefläche schräg, insbesondere unter einem Winkel zwischen 45 und 135 Grad, in Bezug auf die Grundneigungsachse in axialer Richtung der ersten und der zweiten Schaufel angeordnet sind. Die Grundneigung wird auch als "lean" bezeichnet. Die Grundneigung dient üblicherweise dazu, die während des Betriebs der Strömungsmaschine auftretenden Gaskräfte, welche entsprechende Biegemomente an den Schaufeln erzeugen, zumindest in bestimmten Betriebsbereichen der Strömungsmaschine weitgehend auszugleichen. Die Grundneigung beträgt dabei in Abhängigkeit der Ausgestaltung der Strömungsmaschine üblicherweise zwischen 0 und 2 Grad. Die schräge Anordnung von Anlagefläche und Gegenanlagefläche führt dazu, dass ein Torsionsmoment um die Mittelachse einer jeweiligen Schaufel entsteht, welches einer Entwindung einer jeweiligen Schaufel entgegenwirken kann. Hier sind zwei spiegelbildliche Anordnungen möglich. Dieses Torsionsmoment nimmt zu, je stärker die Anlagefläche gegen die Gegenanlagefläche drückt.According to a further embodiment of the blade segment according to the invention, the first and / or second blade on a basic inclination in the axial direction, which is defined by a base inclination axis, wherein the contact surface and counter-bearing surface obliquely, in particular at an angle between 45 and 135 degrees, with respect Base pitch axis in the axial direction of the first and the second blade are arranged. The basic inclination is also called "lean". The basic inclination usually serves to largely compensate for the gas forces which occur during operation of the turbomachine and which generate corresponding bending moments on the blades, at least in certain operating regions of the turbomachine. The base inclination is usually between 0 and 2 degrees depending on the configuration of the turbomachine. The oblique arrangement of contact surface and counter-bearing surface causes a torsional moment about the central axis of a respective blade is created, which can counteract a unwinding of a respective blade. Here are two mirror-image arrangements possible. This torsional moment increases, the more the contact surface presses against the counter-contact surface.

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments weisen die Anlageflächen und Gegenanlageflächen ein Eingriffselement und ein Aufnahmeelement auf, welche in der Umfangsrichtung ineinander eingreifen. Dadurch werden das erste und zweite Deckband noch besser, also zusätzlich zu dem Reibschluss, aneinander abgestützt. Insbesondere verhindert diese Ausgestaltung eine Entwindung der Schaufeln dann, wenn kein Reibschluss erzeugt wird (beispielsweise im Stillstand des Schaufelsegments bei der Ausgestaltung mit dem in Umfangsrichtung versetzten Schwerpunkt des Deckbandes).According to a further embodiment of the blade segment according to the invention, the abutment surfaces and counter abutment surfaces on an engagement element and a receiving element, which engage in one another in the circumferential direction. As a result, the first and second shroud are even better, so in addition to the frictional engagement, supported each other. In particular, this embodiment prevents unwinding of the blades when no frictional engagement is generated (For example, at standstill of the blade segment in the embodiment with the offset in the circumferential direction center of gravity of the shroud).

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments ist die erste und/oder zweite Schaufel torsionsvorgespannt. Stehen die Schaufeln mittels der vorstehend beschriebenen Eingriffs- und Aufnahmeelemente miteinander in Eingriff, ist es beispielsweise möglich die Schaufeln auch torsionsvorzuspannen, sodass auch bei niedrigen Drehzahlen ein ausreichende Kopplung zwischen den Schaufeln erreicht wird, welche ein günstiges Dämpfungsverhalten bewirkt. Der Reibschluss auf Grund des Versatzes des Schwerpunktes eines jeweiligen Deckbandes mag bei den niedrigen Drehzahlen noch nicht genügen, um eine derart ausreichende Kopplung zwischen den Deckbändern zu erzielen.According to a further embodiment of the blade segment according to the invention, the first and / or second blade is torsionsvorgespannt. If the blades engage with each other by means of the above-described engaging and receiving elements, it is possible, for example, to bias the blades torsionally so that sufficient coupling between the blades is achieved even at low rotational speeds, which brings about a favorable damping behavior. The frictional engagement due to the offset of the center of gravity of a respective shroud may not be sufficient at the low speeds to achieve such sufficient coupling between the shrouds.

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments sind die erste und zweite Schaufel als Laufschaufeln ausgebildet.According to a further embodiment of the blade segment according to the invention, the first and second blades are designed as moving blades.

Gemäß einer weiteren Ausgestaltung des erfindungsgemäßen Schaufelsegments sind die erste und zweite Schaufel aus einem stark kriechenden Material. Mit "stark kriechenden Materialien" sind solche Werkstoffe gemeint, die stärker kriechen als aktuelle Nickelwerkstoffe.According to a further embodiment of the blade segment according to the invention, the first and second blades are made of a strong creeping material. By "strong creeping materials" are meant those materials that crawl more than current nickel materials.

Die Erfindung wird nachfolgend anhand von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren der Zeichnungen näher erläutert.The invention will be explained in more detail by means of embodiments with reference to the accompanying figures of the drawings.

Es zeigen:

Figur 1
in axialer Richtung gesehen, schematisch ein Schaufelsegment gemäß einem Ausführungsbeispiel der vorliegenden Erfindung;
Figur 2
einen Schnitt A-A aus Figur 1,
Figur 3
einen Schnitt B-B aus Figur 1,
Figur 4
in einer perspektivischen Ansicht von schräg unten das Schaufelsegment gemäß Figur 1; und
Figur 5
in axialer Richtung gesehen, schematisch ein Schaufelsegment gemäß einem weiteren Ausführungsbeispiel der vorliegenden Erfindung;
Show it:
FIG. 1
seen in the axial direction, schematically a vane segment according to an embodiment of the present invention;
FIG. 2
a section AA FIG. 1 .
FIG. 3
a cut BB off FIG. 1 .
FIG. 4
in a perspective view obliquely from below the blade segment according to FIG. 1 ; and
FIG. 5
seen in the axial direction, schematically a vane segment according to another embodiment of the present invention;

In den Figuren bezeichnen gleiche Bezugsziffern gleiche oder funktionsgleiche Komponenten, soweit nichts Gegenteiliges angegeben ist.In the figures, like reference numerals designate like or functionally identical components, unless indicated otherwise.

Figur 1 zeigt in axialer Richtung gesehen, schematisch ein Schaufelsegment 1 gemäß einem Ausführungsbeispiel der vorliegenden Erfindung. FIG. 1 As seen in the axial direction, schematically shows a blade segment 1 according to an embodiment of the present invention.

Das Schaufelsegment 1 ist Bestandteil einer Strömungsmaschine, insbesondere einer Turbomaschine, welche allgemein mit 2 bezeichnet ist. Bevorzugt handelt es sich bei der Turbomaschine um ein Flugtriebwerk.The blade segment 1 is part of a turbomachine, in particular a turbomachine, which is generally designated 2. The turbomachine is preferably an aircraft engine.

Das Schaufelsegment 1 weist zwei Schaufeln 3 und 3'auf Die Schaufeln 3, 3' sind bevorzugt als Laufschaufeln ausgebildet. Die Schaufeln 3, 3' sind mit ihren jeweiligen Füßen 4, 4' in einem Rotor 5, siehe Figur 4, beispielsweise mittels einer Tannenbaumverbindung, befestigt. Der Rotor 5 dreht um eine Achse 6, wobei die Schaufeln 3, 3' mit einem die Strömungsmaschine 2 durchströmenden Fluid in Wechselwirkung treten. Die Begriffe "in Umfangsrichtung", "in radialer Richtung" und "in axialer Richtung" beziehen sich nachfolgend auf die Achse 6. Es sei angemerkt, dass sich die Achse 6 in der Realität deutlich weiter von den Schaufeln 3, 3' entfernt befindet, als in Figur 1 dargestellt.The blade segment 1 has two blades 3 and 3 'on the blades 3, 3' are preferably formed as blades. The blades 3, 3 'are with their respective feet 4, 4' in a rotor 5, see FIG. 4 , For example by means of a Christmas tree connection, attached. The rotor 5 rotates about an axis 6, wherein the blades 3, 3 'interact with a fluid flowing through the turbomachine 2. The terms "in the circumferential direction", "in the radial direction" and "in the axial direction" refer hereinafter to the axis 6. It should be noted that the axis 6 is located in reality much further away from the blades 3, 3 ', as in FIG. 1 shown.

An ihren Spitzen, also radial außenseitig, sind die Schaufeln 3, 3' jeweils mit Deckbändern 7, 7' verbunden. Die Schaufeln 3, 3', samt ihrer Füße 4, 4' und Deckbänder 7, 7' sind in der Umfangsrichtung U nebeneinander angeordnet und bilden bevorzugt einen geschlossenen Ring aus, wobei in Figur 1 lediglich ein Ausschnitt mit zwei der Schaufeln 3, 3' dargestellt ist. Die Deckbänder 7, 7' sind in axialer Richtung dachziegelartig übereinander angeordnet.At their tips, so radially outside, the blades 3, 3 'are each connected to shrouds 7, 7'. The blades 3, 3 ', together with their feet 4, 4' and shrouds 7, 7 'are arranged side by side in the circumferential direction U and preferably form a closed ring, wherein in FIG. 1 only a section with two of the blades 3, 3 'is shown. The shrouds 7, 7 'are arranged one above the other like a roof tile in the axial direction.

Die Deckbänder 7, 7' weisen jeweils einen Schwerpunkt S, S' auf, welcher einen Abstand D, D' auf eine Mittelachse M, M' einer jeweiligen Schaufel 3, 3' aufweist. Die Mittelachsen M, M' verlaufen jeweils durch die Achse 6, was aufgrund der stark schematisierten Darstellung in Figur 1 nicht erkennbar ist. Die Mittelachse M verläuft dabei durch einen Schwerpunkt SB der Schaufel 3, siehe Figur 2. Der Schwerpunkt SB ist der Schwerpunkt des Profils der Schaufel 3. Entsprechendes gilt für die Mittelachse M' der Schaufel 3'.The shrouds 7, 7 'each have a center of gravity S, S', which has a distance D, D 'on a central axis M, M' of a respective blade 3, 3 '. The central axes M, M 'each extend through the axis 6, which due to the highly schematic representation in FIG. 1 is not recognizable. The central axis M extends through a center of gravity SB of the blade 3, see FIG. 2 , The center of gravity SB is the center of gravity of the profile of the blade 3. The same applies to the central axis M 'of the blade 3'.

Ein jeweiliges Deckband 7, 7' weist eine Anlagefläche 11, 11' und eine dieser gegenüberliegende Gegenanlagefläche 12, 12' auf. Die Anlageflächen 11, 11' und Gegenanlageflächen 12, 12' können jeweils an Enden der Deckbänder 7, 7' in Umfangsrichtung U ausgebildet sein.A respective shroud 7, 7 'has a contact surface 11, 11' and a counter-contact surface 12, 12 'lying opposite it. The contact surfaces 11, 11 'and counter-contact surfaces 12, 12' may each be formed at the ends of the shrouds 7, 7 'in the circumferential direction U.

Weist das Schaufelsegment 1 keine oder nur eine geringe Drehzahl auf, so wirken keine oder nahezu keine Fliehkräfte auf die Schaufeln 3, 3' samt ihrer Deckbänder 7, 7'. Die Schaufeln 3, 3' samt Deckbänder 7, 7' befinden sich dann in der in Figur 1 lediglich für die linke Schaufel 3 in gestrichelter Linie gezeichneten Stellung. Steigt die Drehzahl des Schaufelsegments 1, so nimmt ein Biegemoment des Deckbands 7 um einen Schaufelfußpunkt F zu. Dies, weil der Schwerpunkt S den Abstand D auf die Mittellinie M bzw. den Schwerpunkt SB der Schaufel 3 aufweist. Das resultierende Biegemoment ist in Figur 1 mit BM bezeichnet. Das Biegemoment BM bewirkt, dass die Schaufel 3 samt dem Deckband 7 aus ihrer gestrichelten Stellung in Figur 1 in ihre in durchgezogener Linie dargestellte Stellung kippt, d.h. sich verbiegt. Ab einer gewissen Drehzahl kommt die Anlagefläche 11 mit der Gegenanlagefläche 12' in der radialen Richtung R in Anlage, d.h., dass ein Vektor 9, siehe Fig. 3, senkrecht auf die Ebene 10, in welcher die Anlagefläche 11 und die Gegenanlagefläche 12' gegeneinander anliegen, zumindest eine Komponente in der radialen Richtung R aufweist. Dabei entsteht ein Reibschluss zwischen der Anlagefläche 11 und der Gegenanlagefläche 12'. Von diesem Zeitpunkt an ist die Schaufel 3 mit der Schaufel 3' reibschlüssig gekoppelt, was sich im Hinblick auf ein Vibrationsverhalten dieser vorteilhaft auswirkt.If the blade segment 1 has no or only a low rotational speed, no or almost no centrifugal forces act on the blades 3, 3 'together with their shrouds 7, 7'. The blades 3, 3 'together with shrouds 7, 7' are then in the in FIG. 1 only for the left blade 3 drawn in dashed line position. If the rotational speed of the blade segment 1 increases, a bending moment of the shroud 7 increases by a blade root F. This is because the center of gravity S has the distance D to the center line M or the center of gravity SB of the blade 3. The resulting bending moment is in FIG. 1 denoted by BM. The bending moment BM causes the blade 3 together with the shroud 7 from its dashed position in FIG. 1 in its position shown in a solid line tilts, ie bends. From a certain speed, the contact surface 11 comes into contact with the counter-contact surface 12 'in the radial direction R, that is to say that a vector 9, see FIG Fig. 3 , perpendicular to the plane 10, in which the contact surface 11 and the counter-bearing surface 12 'bear against each other, at least one component in the radial direction R has. This creates a frictional engagement between the contact surface 11 and the counter-contact surface 12 '. From this point on, the blade 3 is frictionally coupled to the blade 3 ', which has an advantageous effect with regard to a vibration behavior thereof.

Figur 2 zeigt einen Schnitt A-A aus Figur 1.FIG. 2 shows a section A-A from FIG. 1.

In Figur 2 ist zu erkennen, dass der Reibschluss RF zwischen der Anlagefläche 11 und der Gegenanlagefläche 12' derart ausgebildet sein kann, dass dieser ein Torsionsreaktionsmoment TM um die Mittelachse M erzeugt, was die Schaufel 3 daran hindert, dass diese um die Mittelachse in ungewünschter Weise schwingt.In FIG. 2 It can be seen that the frictional engagement RF between the abutment surface 11 and the counter-abutment surface 12 'may be formed to produce a torsional reaction torque TM about the center axis M, preventing the blade 3 from undesirably swinging about the central axis.

Figur 3 zeigt einen Schnitt B-B aus Figur 1.FIG. 3 shows a section B-B from FIG. 1.

Wie Figur 3 zu entnehmen, können die Anlagefläche 11 und die Gegenanlagefläche 12' in Bezug auf eine Grundneigungsachse G' schräg unter einem Winkel W' von bspw. 93 Grad angeordnet sein. "Schräg" meint einen Winkel W' ungleich 90 Grad und bevorzugt zwischen 45 und 135 Grad. Die Grundneigungsachse G' der Schaufel 3' kann beispielsweise um 1 Grad in Richtung der Drehachse 6 geneigt sein.As FIG. 3 can be found, the contact surface 11 and the counter-bearing surface 12 'with respect to a base inclination axis G' obliquely at an angle W 'of, for example, 93 degrees to be arranged. "Sloping" means an angle W 'other than 90 degrees and preferably between 45 and 135 Degree. The base inclination axis G 'of the blade 3' may be inclined for example by 1 degree in the direction of the axis of rotation 6.

Unter der Einwirkung der Fliehkräfte und einer entsprechenden Entwindung der Schaufel 3 ergibt sich eine Anpresskraft AK zwischen der Anlagefläche 11 und der Gegenanlagefläche 12'. Aufgrund der schrägen Anordnung der Anlagefläche 11 sowie der Gegenanlagefläche 12' resultiert die Anlagekraft AK in einer Reaktionskraft RK1 und eine Reaktionskraft RK2, welche auf die Schaufel 3 rückwirken. RK2 wirkt entlang der Grundneigungsachse G' und RK1 senkrecht zu dieser.Under the action of the centrifugal forces and a corresponding unwinding of the blade 3, a contact pressure AK results between the contact surface 11 and the counter-contact surface 12 '. Due to the oblique arrangement of the contact surface 11 and the counter-contact surface 12 ', the contact force AK results in a reaction force RK1 and a reaction force RK2, which act on the blade 3. RK2 acts along the base pitch axis G 'and RK1 perpendicular thereto.

RK1 ist auch in Figur 2 dargestellt. Hier ist zu erkennen, dass RK1 ein zusätzliches Torsionsmoment TR um den Schwerpunkt SB bzw. die Mittelachse M der Schaufel 3 erzeugt, welches einer Entwindung E der Schaufel 3 entgegenwirkt.RK1 is also in FIG. 2 shown. Here it can be seen that RK1 generates an additional torsional moment TR about the center of gravity SB or the center axis M of the blade 3, which counteracts a winding E of the blade 3.

Figur 4 zeigt das Schaufelsegment aus 1 aus Figur 1 in einer perspektivischen Ansicht von schräg unten. FIG. 4 1 shows the vane segment FIG. 1 in a perspective view obliquely from below.

Wie in Figur 4 dargestellt, weisen die Deckbänder 7, 7' an ihren gegenüberliegenden Enden bevorzugt im Bereich der Anlageflächen 11, 11' und Gegenanlageflächen 12, 12' Eingriffselemente 13, 13' und Aufnahmeelemente 14, 14' auf. Das Eingriffselement 13' des Deckbands 7' greift in der Umfangsrichtung in das Aufnahmeelement 14 des Deckbands 7 ein. Dadurch ergibt sich ein Formschluss in der axialen Richtung, welcher eine Entwindung der Schaufeln 3, 3' im Stillstand des Schaufelsegments 1 oder bei niedrigen Drehzahlen, wo der Reibschluss RF noch zu gering ist, um die Schaufeln 3, 3' miteinander zu koppeln, verhindert.As in FIG. 4 illustrated, the shrouds 7, 7 'at their opposite ends preferably in the region of the contact surfaces 11, 11' and counter-bearing surfaces 12, 12 'engaging elements 13, 13' and receiving elements 14, 14 'on. The engagement element 13 'of the shroud 7' engages in the circumferential direction in the receiving element 14 of the shroud 7 a. This results in a form fit in the axial direction, which unwinding of the blades 3, 3 'at a standstill of the blade segment 1 or at low speeds, where the frictional engagement RF is still too low to couple the blades 3, 3' together prevented ,

Fig. 5 zeigt in axialer Richtung gesehen, schematisch ein Schaufelsegment 1 gemäß einem weiteren Ausführungsbeispiel der vorliegenden Erfindung. Fig. 5 As seen in the axial direction, schematically shows a blade segment 1 according to another embodiment of the present invention.

Das Schaufelsegment 1 unterscheidet sich von dem gemäß den Fig. 1 bis 4 lediglich auf die Art und Weise, wie der Reibschluss RF erzeugt wird. Im Übrigen gelten daher die Ausführungen zu den Fig. 1 bis 4 entsprechend für das Schaufelsegment nach Fig. 5.The blade segment 1 differs from that according to the Fig. 1 to 4 only in the way the friction fit RF is generated. Incidentally, therefore, the comments on the Fig. 1 to 4 according to the blade segment Fig. 5 ,

Bei dem Schaufelsegment 1 nach Fig. 5 ist die Anlagefläche 11 des Deckbandes 7 mit einem Pressmaß P in radialer Richtung R für ein Verbiegen der ersten Schaufel 3 um deren Fußpunkt F in der Umfangsrichtung U gebildet, um dadurch den Reibschlusses RF zwischen der Anlagefläche 11 und der Gegenanlagefläche 12' zu erzeugen. Entsprechendes gilt selbstverständlich auch für die weiteren Schaufeln des Schaufelsegments.At the blade segment 1 after Fig. 5 is the contact surface 11 of the shroud 7 with a pressing dimension P in the radial direction R for bending the first blade 3 about its base F formed in the circumferential direction U, thereby generating the frictional engagement RF between the abutment surface 11 and the counter-abutment surface 12 '. Of course, the same applies to the other blades of the blade segment.

Der Reibschluss RF bei dem Ausführungsbeispiel nach Fig. 5 ist vorteilhaft nicht oder nur unwesentlich drehzahlabhängig.The frictional engagement RF in the embodiment according to Fig. 5 is advantageous not or only slightly dependent on speed.

Die Ausgestaltungen nach den Fig. 1 bis 4 und nach Fig. 5 können auch miteinander kombiniert werden.The embodiments according to the Fig. 1 to 4 and after Fig. 5 can also be combined with each other.

Obwohl die Erfindung vorliegend anhand bevorzugter Ausführungsbeispiele beschrieben wurde, ist sie darauf nicht beschränkt, sondern vielfältige Weise modifizierbar.Although the invention has been described herein with reference to preferred embodiments, it is not limited thereto, but variously modifiable.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Schaufelsegmentvane segment
22
Strömungsmaschineflow machine
33
Schaufelshovel
3'3 '
Schaufelshovel
44
Fußfoot
4'4 '
Fußfoot
55
Rotorrotor
66
Drehachseaxis of rotation
77
Deckbandshroud
7'7 '
Deckbandshroud
99
Vektorvector
1010
Ebenelevel
1111
Anlageflächecontact surface
11'11 '
Anlageflächecontact surface
1212
GegenanlageflächeAnvil surface
12'12 '
GegenanlageflächeAnvil surface
1313
Eingriffselementengaging member
13'13 '
Eingriffselementengaging member
1414
Aufnahmeelementreceiving element
14'14 '
Aufnahmeelementreceiving element
DD
Abstanddistance
FF
Fußpunktnadir
G'G'
GrundneigungsachseBasic tilt axis
MM
Mittelachsecentral axis
M'M '
Mittelachsecentral axis
RR
radiale Richtungradial direction
SS
Schwerpunktmain emphasis
S'S '
Schwerpunktmain emphasis
UU
Umfangsrichtungcircumferentially
AKAK
Anlagekraftcontact force
BMBM
BiegemomentBending moment
RFRF
Reibkraftfriction force
RK1RK1
Reaktionskraftreaction force
RK2RK2
Reaktionskraftreaction force
SBSB
SchaufelschwerpunktShovel emphasis
TMTM
TorsionsreaktionsmomentTorsionsreaktionsmoment
TRTR
Torsionsmomenttorsional
Ee
Entwindungunwinding

Claims (9)

  1. Blade segment (1) for a turbomachine (2), having:
    a first blade (3);
    a first shroud (7) connected to a tip of the first blade (3), which shroud has a contact surface (11);
    a second blade (3'), wherein the first and second blade (3, 3') are formed as rotor blades; and
    a second, second shroud (7') connected to a tip of the second blade (3'), which shroud has a counter-contact surface (12') for an abutment of the contact surface (11) of the first shroud (7) in a radial direction (R) in such a way that a friction locking (RF) can be produced between the contact surface (11) and the counter-contact surface (12'),
    characterised in that the contact surface (11) and counter-contact surface (12') are arranged obliquely in the axial direction.
  2. Blade segment according to claim 1, characterised in that the centre of mass (S) of the first shroud (7) is arranged at a distance in the circumferential direction (U) from a centre line (M) of the first blade (3) such that the first blade (3) bends under the influence of the centrifugal forces in operation of the blade segment (1) for the production of the friction locking (RF) between the contact surface (11) and the counter-contact surface (12').
  3. Blade segment according to claim 1 or 2, characterised in that the contact surface (11) of the first shroud (7) and/or the counter-contact surface (12') of the second shroud (7') are formed with a pressing dimension (P) in the radial direction (R) for a bending of the first blade (3) about its root point (F) in the circumferential direction,(U), in order thereby to produce the friction locking (RF) between the contact surface (11) and the counter-contact surface (12').
  4. Blade segment according to one of the preceding claims, characterised in that the friction locking (RF) is formed to produce a torsion reaction torque (TM) in a direction about the centre line (M) of the first and/or second blade (3).
  5. Blade segment according to one of the preceding claims, characterised in that the first and/or second blade (3') have a basic inclination in the axial direction (6), which is defined by a basic inclination axis (G'), wherein the contact surface (11) and counter-contact surface (12') are arranged obliquely, in particular at an angle (W') between 45 and 135 degrees, in relation to the basic inclination axis (G') of the first and/or second blade (3').
  6. Blade segment according to one of the preceding claims, characterised in that the contact surface (11) and counter-contact surface (12') have an engagement element (13') and a receiving element (14), which engage in one another in the circumferential direction (U).
  7. Blade segment according to one of the preceding claims, characterised in that the first and/or second blade (3, 3') is torsion-pretensioned.
  8. Blade segment according to one of the preceding claims, characterised in that the first and/or second blade (3, 3') is formed from a material that creeps more strongly than nickel materials.
  9. Turbomachine (2) with a blade segment (1) according to one of the preceding claims.
EP10193687A 2010-12-03 2010-12-03 Blade segment of a flow engine with radial support surfaces Not-in-force EP2460979B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10193687A EP2460979B1 (en) 2010-12-03 2010-12-03 Blade segment of a flow engine with radial support surfaces
ES10193687T ES2401350T3 (en) 2010-12-03 2010-12-03 Vane and turbine segment with radial seating surfaces
US13/310,939 US20120141259A1 (en) 2010-12-03 2011-12-05 Blade segment and fluid flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10193687A EP2460979B1 (en) 2010-12-03 2010-12-03 Blade segment of a flow engine with radial support surfaces

Publications (2)

Publication Number Publication Date
EP2460979A1 EP2460979A1 (en) 2012-06-06
EP2460979B1 true EP2460979B1 (en) 2013-02-13

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10193687A Not-in-force EP2460979B1 (en) 2010-12-03 2010-12-03 Blade segment of a flow engine with radial support surfaces

Country Status (3)

Country Link
US (1) US20120141259A1 (en)
EP (1) EP2460979B1 (en)
ES (1) ES2401350T3 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3137120A1 (en) * 2022-06-22 2023-12-29 Safran Aircraft Engines Bladed turbomachine assembly comprising means of limiting vibrations between platforms

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1033197A (en) * 1951-02-27 1953-07-08 Rateau Soc Vibration dampers for mobile turbo-machine blades
GB861728A (en) * 1958-09-29 1961-02-22 Parsons & Marine Eng Turbine Improvements in and relating to elastic fluid turbines
GB1194061A (en) * 1968-01-17 1970-06-10 Rolls Royce Improvements relating to Pressure Exchanger Rotors
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
JP2001248404A (en) * 2000-03-01 2001-09-14 Hitachi Ltd Moving blade of turbine
JP2002371802A (en) * 2001-06-14 2002-12-26 Mitsubishi Heavy Ind Ltd Shroud integrated type moving blade in gas turbine and split ring
US7429164B2 (en) * 2002-09-02 2008-09-30 Hitachi, Ltd. Turbine moving blade
JP4673732B2 (en) 2005-12-01 2011-04-20 株式会社東芝 Turbine blades and steam turbines
GB2436597A (en) * 2006-03-27 2007-10-03 Alstom Technology Ltd Turbine blade and diaphragm
EP1840333A1 (en) * 2006-03-31 2007-10-03 ALSTOM Technology Ltd Turbine blade with shroud portions
EP1873355A1 (en) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Turbine rotor blade
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
GB0700633D0 (en) * 2007-01-12 2007-02-21 Alstom Technology Ltd Turbomachine

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Publication number Publication date
EP2460979A1 (en) 2012-06-06
US20120141259A1 (en) 2012-06-07
ES2401350T3 (en) 2013-04-18

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