EP1266129B1 - Fastening of the blades of a compression machine - Google Patents

Fastening of the blades of a compression machine Download PDF

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Publication number
EP1266129B1
EP1266129B1 EP01914106A EP01914106A EP1266129B1 EP 1266129 B1 EP1266129 B1 EP 1266129B1 EP 01914106 A EP01914106 A EP 01914106A EP 01914106 A EP01914106 A EP 01914106A EP 1266129 B1 EP1266129 B1 EP 1266129B1
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EP
European Patent Office
Prior art keywords
blades
blade
root
rotor
fastening
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.)
Expired - Lifetime
Application number
EP01914106A
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German (de)
French (fr)
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EP1266129A1 (en
Inventor
Eduard GÖTZFRIED
Helmut Wendler
Heinz May
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General Electric Technology GmbH
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Alstom Technology AG
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Publication date
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Publication of EP1266129A1 publication Critical patent/EP1266129A1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an attachment or anchoring of Blade of a turbomachine by means of blade feet on the rotor or Stator of the turbomachine.
  • Such blade attachments are usually found in the rotors of Compressors or thermal turbo machines. They are state of the art Technology well known.
  • the blades are in a groove with the blade root, which is at the Rotor is inserted.
  • the blade root is used for power and Torque transmission to the rotor.
  • Cover plates at the top of the are often used to dampen vibrations Airfoil or support wings attached within the airfoil.
  • Austrian patent specification AT 254.227 also discloses a cover plate a turbine or compressor blade ring in which the cover plates a force is pressed against each other.
  • the arrangement leads to an elastic prestressing of the airfoil.
  • This Torsional prestressing of the airfoil takes place between the cover plate and the blade root instead, which leads to an additional load on the Blade root and the rotor leads. Because the emerging forces are not only from the airfoil, but also from the airfoil and the rotor must be included, they are correspondingly more massive executed.
  • a disadvantage of such prior art is that the load is always transferred to the rotor via the blade root. This applies especially for the torsional moments mentioned above.
  • the more massive Execution of the rotor and the blade feet has negative Effects in particular on the width of the bucket and the Blade root and the wheel disc and thus over the entire length of the rotor. Due to the higher foot load had to be cheaper Foot designs (e.g. hammer head foot, rider blade foot) are omitted and instead, on more stable, more expensive foot shapes (e.g. plug-in foot) be used.
  • the aim of the invention is to avoid the disadvantages mentioned.
  • the invention is based on the object of a fastening for blades To create turbomachine on a rotor or stator, with which the Torsional moments increased from the blade root or the base plate of the Bucket can be added while relieving the load on the Rotor / stator and the blade root.
  • the total length of the Shortened the rotor / stator or, with the same length, the number of Row of blades increased and / or the use of inexpensive Foot connections are made possible.
  • the object is achieved by fastening blades according to the preamble of claim 1 solved in that according to the Installation of all blades, the blades on the rotor or stator on the base plate and / or on the blade root without play or with one Adjacent bias and so against each other Support torsional moments, which on the footplates and / or on the Bucket feet acting torsional moments the torsional moments which act on the cover plate or on the support wing, are opposite.
  • An advantage of this embodiment is that torsional moments are no longer or only marginally absorbed by the rotor, but through the adjoining foot plates and / or shovel feet, because a rotation of these two components is prevented.
  • the blade root and also the rotor (or stator) can be used as a measure. can be dimensioned correspondingly smaller because of the rotor at the contact surface (Stator) / blade root no greater forces can be absorbed have to. Overall, the length of the rotor can thus be reduced. It is the number of rows of blades with the same length of the rotor (stator) and thus also increasing the efficiency.
  • the base plate and possibly also the blade root have one Bevel, which is advantageously connected to a bevel adjoins the adjacent blade and so torsional moments at this point mutually accepted.
  • the scoop 1 at which can be a moving or guide vane consists of a blade root 4, from a adjoining the blade root 4 Base plate 3, from a cover plate 2 or a support wing or one Support plate, and one between the base plate 3 and the cover plate 2 located blade 5.
  • the blade root 4 is in Figure 1 as single-pronged plug-in foot 4a. It is used to attach the bucket 1 on the rotor 6, not shown in FIG. 1, or on a stator. Both the foot 3 and the cover plate 2 of the blade 1 are with a Bevel 9 equipped.
  • the bevel 9 is on one side the top 2 or foot plate 3, i.e.
  • the bevel 9 is with regard to the To understand the top view of both plates 2, 3, as is also the case in FIG. 3 and 4 becomes clear. It is also possible that also on the blade root 4 a bevel 9 is attached.
  • the bucket 1 can also be trade a shovel with a multi-pronged plug foot.
  • the cover plate 2 can be attached to the airfoil 5 be attached between the blade tip 14 and the base plate 3. This generally applies to all usable blade types.
  • Holes 11 are additionally present in the blade root 4, 4a, for this purpose serve to fasten the foot to the rotor or stator with bolts.
  • FIG. 4 shows a section through a row of blades, the base plates 3 of the blades 1 1 , 1 2 , 1 3 , 1 n being visible in this figure.
  • adjacent foot plates 3 meet directly and without play at the contact points 7.
  • the contact points 7 between adjacent plates 3 are in the area of the bevels 9.
  • a gap 10 is formed in the other part of the foot plates 3.
  • the torsional moments 12 acting on the foot plates 3 are opposite to the torsional moments 13 shown in FIG Bevels 9 are arranged at a corresponding other end of the respective plate 2, 3.
  • the contact point 7 can also refer overall to the adjacent foot plates 3 without a gap 10 being formed.
  • the bevels 9, as already shown in FIG. 1, can also relate to areas of the blade root 4. However, this is not shown in detail in FIG. 4.
  • the single-pronged plug-in foot which is shown in FIG. 1, is only for example chosen.
  • a blade root 4 can be different from the State of the art types known per se, for example a hammer foot or rider's foot.
  • blade feet 4 are now also available can be used, which so far have been difficult or difficult Conditions were applicable. This is due to the decreased Power transmission from the blade root 4 to the rotor 6 or to the stator possible. Because the blade roots 4 and also the rotor 6 or the stator are smaller can be dimensioned (e.g. in width), the total length of the Shortened rotor 6 or the same length of the rotor 6 (stator) Efficiency of the turbomachine through additional rows of blades increase. Existing rotors 6 (stators) can also easily on the new type of attachment of the blades 1 to be converted. This is a Advantage, since simpler blades 1, which are manufactured more cost-effectively can be used. For example, in the Figure 1 shown plug-in foot or a hammer foot in a simple manner Known milling processes are manufactured.

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

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die Erfindung bezieht sich auf eine Befestigung oder Verankerung von Schaufeln einer Strömungsmaschine mittels Schaufelfüssen am Rotor oder Stator der Strömungsmaschine.The invention relates to an attachment or anchoring of Blade of a turbomachine by means of blade feet on the rotor or Stator of the turbomachine.

STAND DER TECHNIKSTATE OF THE ART

Derartige Schaufelbefestigungen befinden sich in der Regel bei Rotoren von Verdichtern oder thermischen Turbomaschinen. Sie sind aus dem Stand der Technik zahlreich bekannt.Such blade attachments are usually found in the rotors of Compressors or thermal turbo machines. They are state of the art Technology well known.

Die Schaufeln werden mit dem Schaufelfuss in eine Nut, welche sich am Rotor befindet, eingebracht. Der Schaufelfuss dient dabei zur Kraft- und Momentenübertragung auf den Rotor.The blades are in a groove with the blade root, which is at the Rotor is inserted. The blade root is used for power and Torque transmission to the rotor.

Zur Schwingungsdämpfung sind häufig Deckplatten an der Spitze des Schaufelblattes oder Stützflügeln innerhalb des Schaufelblattes angebracht. Cover plates at the top of the are often used to dampen vibrations Airfoil or support wings attached within the airfoil.

Dies ist zum Beispiel in der deutschen Patentschrift DE 1,159,965 beschrieben.This is for example in the German patent DE 1,159,965 described.

Auch die Österreichische Patentschrift AT 254,227 offenbart eine Deckplatte eines Turbinen- oder Verdichterschaufelkranzes in dem die Deckplatten durch eine Krafteinwirkung gegeneinander gepresst werden. Die Anordnung führt zu einer elastischen Vorspannung des Schaufelblattes. Diese Torsionsvorspannung des Schaufelblattes findet zwischen der Deckplatte und dem Schaufelfuss statt, was aber zu einer zusätzlichen Belastung des Schaufelfusses und des Rotors führt. Da die entstehenden Kräfte nicht nur vom Schaufelblatt, sondern auch vom Schaufelfuss und vom Rotor aufgenommen werden müssen, sind diese entsprechend massiver ausgeführt.Austrian patent specification AT 254.227 also discloses a cover plate a turbine or compressor blade ring in which the cover plates a force is pressed against each other. The arrangement leads to an elastic prestressing of the airfoil. This Torsional prestressing of the airfoil takes place between the cover plate and the blade root instead, which leads to an additional load on the Blade root and the rotor leads. Because the emerging forces are not only from the airfoil, but also from the airfoil and the rotor must be included, they are correspondingly more massive executed.

Häufig sind Abstandshalter zwischen den einzelnen Schaufelfüssen der Turbinenschaufeln angeordnet, welche die Kräfte aufnehmen und auch zur Schwingungsdämpfung dienen sollen. Dies ist zum Beispiel aus den Patenten US 2,916,257 oder auch aus US 3,734,645 bekannt. Eine andere Laufschaufelbefestigung ist auch aus der Europäischen Offenlegungsschrift EP-A1-520,258 bekannt. Zur Begrenzung von Umfangskräften in der Folge von Wärmedehnungen sind zwischen den Laufschaufein Längsstege vorgesehen.Spacers between the individual blade feet are often the Turbine blades arranged, which absorb the forces and also for Vibration damping should serve. This is for example from the patents US 2,916,257 or also known from US 3,734,645. Another Blade attachment is also from the European published application EP-A1-520,258 known. To limit circumferential forces in the sequence of thermal expansion are between the rotor blades in longitudinal webs intended.

Nachteilig bei solchem Stand der Technik ist allerdings, dass die Last grundsätzlich über den Schaufelfuss auf den Rotor übertragen wird. Dies gilt insbesondere für die oben genannten Torsionsmomente. Die massivere Ausführung von Rotor und den Schaufelfüssen hat aber negative Auswirkungen insbesondere auf die Breite der Schaufel und des Schaufelfusses und der Radscheibe und damit auch auf die gesamte Länge des Rotors. Aufgrund der höheren Fußbelastung musste auf preisgünstigere Fußausführungen (z.B Hammerkopffuß, Reiterschaufelfuß) verzichtet und statt dessen auf stabilere, teurere Fußformen (wie z.B. Steckfuß) zurückgegriffen werden. A disadvantage of such prior art is that the load is always transferred to the rotor via the blade root. this applies especially for the torsional moments mentioned above. The more massive Execution of the rotor and the blade feet has negative Effects in particular on the width of the bucket and the Blade root and the wheel disc and thus over the entire length of the rotor. Due to the higher foot load had to be cheaper Foot designs (e.g. hammer head foot, rider blade foot) are omitted and instead, on more stable, more expensive foot shapes (e.g. plug-in foot) be used.

Ziel der Erfindung ist es, die genannten Nachteile zu vermeiden. Der Erfindung liegt die Aufgabe zu Grunde, eine Befestigung für Schaufeln einer Strömungsmaschine an einem Rotor oder Stator zu schaffen, mit welcher die Torsionsmomente vermehrt vom Schaufelfuss oder der Fussplatte der Schaufel aufgenommen werden kann bei gleichzeitiger Entlastung des Rotors/Stators und des Schaufelfusses. Zudem soll die Gesamtlänge des Rotors/Stators verkürzt bzw. bei gleicher Länge die Anzahl der Schaufelreihen erhöht und/oder der Einsatz von preisgünstigen Fußverbindungen ermöglicht werden.The aim of the invention is to avoid the disadvantages mentioned. The The invention is based on the object of a fastening for blades To create turbomachine on a rotor or stator, with which the Torsional moments increased from the blade root or the base plate of the Bucket can be added while relieving the load on the Rotor / stator and the blade root. In addition, the total length of the Shortened the rotor / stator or, with the same length, the number of Row of blades increased and / or the use of inexpensive Foot connections are made possible.

Erfindungsgemäss wird die Aufgabe durch eine Befestigung von Schaufeln gemäss dem Oberbegriff des Anspruchs 1 dadurch gelöst, dass nach dem Einbau aller Schaufeln die Schaufeln am Rotor oder Stator an der Fussplatte und/oder am Schaufelfuss ohne Spiel oder mit einer Vorspannung aneinandergrenzen und sich so gegenseitig gegenüber Torsionsmomenten abstützen, wobei die an den Fussplatten und/oder an den Schaufelfüssen wirkenden Torsionsmomente den Torsionsmomenten, welche an der Deckplatte oder an dem Stützflügel wirken, entgegengesetzt sind.According to the invention, the object is achieved by fastening blades according to the preamble of claim 1 solved in that according to the Installation of all blades, the blades on the rotor or stator on the base plate and / or on the blade root without play or with one Adjacent bias and so against each other Support torsional moments, which on the footplates and / or on the Bucket feet acting torsional moments the torsional moments which act on the cover plate or on the support wing, are opposite.

Vorteilhaft an dieser Ausführungsform ist, dass Torsionsmomente nicht mehr oder nur noch marginal durch den Rotor aufgenommen werden, sondern durch die aneinandergrenzenden Fussplatten und/oder Schaufelfüsse, da eine Verdrehung dieser beiden Bauelemente verhindert wird. Durch diese Massnahme kann der Schaufelfuss und auch der Rotor (oder Stator) entsprechend kleiner dimensioniert werden, da an der Kontaktfläche Rotor (Stator)/Schaufelfuss keine grösseren Kräfte mehr aufgenommen werden müssen. Insgesamt kann also die Länge des Rotors verkleinert werden. Es ist die Anzahl der Schaufelreihen bei gleicher Länge des Rotors (Stators) und damit auch den Wirkungsgrad zu erhöhen.An advantage of this embodiment is that torsional moments are no longer or only marginally absorbed by the rotor, but through the adjoining foot plates and / or shovel feet, because a rotation of these two components is prevented. Through this The blade root and also the rotor (or stator) can be used as a measure. can be dimensioned correspondingly smaller because of the rotor at the contact surface (Stator) / blade root no greater forces can be absorbed have to. Overall, the length of the rotor can thus be reduced. It is the number of rows of blades with the same length of the rotor (stator) and thus also increasing the efficiency.

Ausserdem ist es möglich, andere Fussverbindungen einzusetzen, die mit der bisherigen Technik nicht zu verwenden gewesen wären. Zum Beispiel kann ein einzinkiger Steckfuss, ein Hammerkopffuss oder ein gleichwertiger, einfacher Schaufelfuss vorteilhaft eingesetzt werden. Solche Schaufelfüsse können einfach und ohne grosse Schwierigkeiten durch bekannte Fräsverfahren gefertigt werden.It is also possible to use other foot connections that are connected to the previous technology could not have been used. For example a single-pronged plug-in foot, a hammer head foot or an equivalent, simple blade root can be used advantageously. Such shovel feet can easily and without great difficulty by known Milling processes are manufactured.

Die Fussplatte und möglicherweise auch der Schaufelfuss weisen eine Abschrägung auf, welche in vorteilhafter Weise an eine Abschrägung einer benachbarten Laufschaufel grenzt und so Torsionsmomente an dieser Stelle gegenseitig aufgenommen werden.The base plate and possibly also the blade root have one Bevel, which is advantageously connected to a bevel adjoins the adjacent blade and so torsional moments at this point mutually accepted.

KURZE BESCHREIBUNG DER ZEICHNUNGBRIEF DESCRIPTION OF THE DRAWING

Es zeigen

Fig.1
eine Turbinenschaufel einer Dampfturbine mit einem einzinkigen Schaufelfuss und Deckplatte/Stützflügel,
Fig. 2
eine Turbinenschaufel einer Dampfturbine mit einer Stützplatte (Stützflügel) innerhalb des Schaufelblattes,
Fig. 3
einen Draufsicht auf ein erfindungsgemässes Ausführungsbeispiel mit den Deckplatten der Turbinenschaufeln und
Fig. 4
einen Schnitt durch ein erfindungsgemässes Ausführungsbeispiel von Turbinenschaufeln, welche in einer Nut an dem Rotor oder Stator der Strömungsmaschine angeordnet sind, wobei die Fussplatten sichtbar sind.
Show it
Fig.1
a turbine blade of a steam turbine with a single-pronged blade root and cover plate / support wing,
Fig. 2
a turbine blade of a steam turbine with a support plate (support wing) inside the blade,
Fig. 3
a plan view of an embodiment according to the invention with the cover plates of the turbine blades and
Fig. 4
a section through an embodiment of turbine blades according to the invention, which are arranged in a groove on the rotor or stator of the turbomachine, wherein the base plates are visible.

Es werden nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente werden in unterschiedlichen Figuren mit gleichen Bezugszeichen versehen.Only the elements essential to the invention are shown. The same elements are the same in different figures Provide reference numerals.

WEG ZUR AUSFÜHRUNG DER ERFINDUNGWAY OF CARRYING OUT THE INVENTION

Die Figur 1 zeigt eine Schaufel 1 einer Strömungsmaschine, also beispielsweise einer Dampfturbine oder eines Verdichters. Die Schaufel 1 bei welcher es sich um eine Lauf- oder Leitschaufel handeln kann, besteht aus einem Schaufelfuss 4, aus einer sich an den Schaufelfuss 4 anschliessenden Fussplatte 3, aus einer Deckplatte 2 bzw. einem Stützflügel oder einer Stützplatte, und aus einem sich zwischen der Fussplatte 3 und der Deckplatte 2 befindenden Schaufelblatt 5. Der Schaufelfuss 4 ist in der Figur 1 als einzinkiger Steckfuss 4a ausgeführt. Er dient zur Befestigung der Schaufel 1 an dem in der Figur 1 nicht dargestellten Rotor 6 oder an einem Stator. Sowohl die Fuss- 3 als auch die Deckplatte 2 der Schaufel 1 sind mit einer Abschrägung 9 ausgestattet. Die Abschrägung 9 befindet sich an einer Seite der Deck- 2 bzw. Fussplatte 3, d.h. die Abschrägung 9 ist im Hinblick auf die Draufsicht auf beiden Platten 2, 3 zu verstehen, wie dies auch in der Figur 3 und 4 deutlich wird. Es ist auch möglich, dass am Schaufelfuss 4 ebenfalls eine Abschrägung 9 angebracht ist. Bei der Schaufel 1 kann es sich auch um eine Schaufel mit mehrzinkigem Steckfuss handeln.1 shows a blade 1 of a turbomachine, that is for example a steam turbine or a compressor. The scoop 1 at which can be a moving or guide vane consists of a blade root 4, from a adjoining the blade root 4 Base plate 3, from a cover plate 2 or a support wing or one Support plate, and one between the base plate 3 and the cover plate 2 located blade 5. The blade root 4 is in Figure 1 as single-pronged plug-in foot 4a. It is used to attach the bucket 1 on the rotor 6, not shown in FIG. 1, or on a stator. Both the foot 3 and the cover plate 2 of the blade 1 are with a Bevel 9 equipped. The bevel 9 is on one side the top 2 or foot plate 3, i.e. the bevel 9 is with regard to the To understand the top view of both plates 2, 3, as is also the case in FIG. 3 and 4 becomes clear. It is also possible that also on the blade root 4 a bevel 9 is attached. The bucket 1 can also be trade a shovel with a multi-pronged plug foot.

Wie aus der Figur 2 ersichtlich, kann die Deckplatte 2 an dem Schaufelblatt 5 zwischen der Schaufelspitze 14 und der Fussplatte 3 angebracht sein. Dies gilt allgemein für alle verwendbaren Schaufeltypen.As can be seen from FIG. 2, the cover plate 2 can be attached to the airfoil 5 be attached between the blade tip 14 and the base plate 3. This generally applies to all usable blade types.

Bei den Schaufeln, weiche in der Figur 1 bzw. in der Figur 2 gezeigt sind, sind in dem Schaufelfuss 4,4a zusätzlich Löcher 11 vorhanden, welche dazu dienen, den Fuss am Rotor oder Stator durch Bolzen zu befestigen.With the blades, which are shown in FIG. 1 and in FIG. 2, respectively Holes 11 are additionally present in the blade root 4, 4a, for this purpose serve to fasten the foot to the rotor or stator with bolts.

Bei dem Einbau der Schaufeln 11,12,13,1n in einer Nut 8 am Rotor 6 oder auch an einem Stator werden an der Deckplatte 2 Torsionsmomente 13 angewendet, welche in Richtung der Abschrägung 9 wirken. Dabei entsteht die Kontaktstelle 7, an welcher die Torsionsmomente 13 aufgenommen werden. Dies ist in der Schaufelreihe der Figur 3 dargestellt, welche eine Draufsicht auf die verschiedenen Schaufeln 11,12,13,1n zeigt. Auf diese Weise bekommen die Schaufeln 11,12,13,1n eine gewisse Vorspannung. Zwischen dem anderen Teil der Deckplatte 2, an dem die Deckplatten 2 nicht aneinandergrenzen, entsteht auf diese Weise ein Spalt 10. Weiter sind in der Figur 3 die Schaufelblätter 5 sichtbar, welche unterhalb der Deckplatte 2 sein können. Im Falle einer intermediären Anordnung der Deckplatte 2 an dem Schaufelblatt 5, wie dies in der Figur 2 dargestellt ist, ist dies ober- und unterhalb der Deckplatte 2. When the blades 1 1 , 1 2 , 1 3 , 1 n are installed in a groove 8 on the rotor 6 or also on a stator, 2 torsional moments 13 are applied to the cover plate, which act in the direction of the bevel 9. This creates the contact point 7 at which the torsional moments 13 are absorbed. This is shown in the row of blades in FIG. 3, which shows a top view of the different blades 1 1 , 1 2 , 1 3 , 1 n . In this way, the blades 1 1 , 1 2 , 1 3 , 1 n get a certain preload. In this way, a gap 10 is formed between the other part of the cover plate 2, on which the cover plates 2 do not adjoin one another. In FIG. 3, the blades 5 can also be seen, which can be below the cover plate 2. In the case of an intermediate arrangement of the cover plate 2 on the airfoil 5, as shown in FIG. 2, this is above and below the cover plate 2.

Die Figur 4 zeigt einen Schnitt durch eine Schaufelreihe, wobei in dieser Figur die Fussplatten 3 der Schaufeln 11,12,13,1n sichtbar sind.
Wiederum stossen benachbarte Fussplatten 3 direkt und spielfrei an den Kontaktstellen 7 aneinander. Die Kontaktstellen 7 zwischen benachbarten Platten 3 sind im Bereich der Abschrägungen 9. In dem anderen Teil der Fussplatten 3 entsteht ein Spalt 10. Die auf die Fussplatten 3 wirkenden Torsionsmomente 12 sind aber den in der Figur 3 gezeigten Torsionsmomenten 13 entgegengesetzt, so dass auch die Abschrägungen 9 an einem entsprechend anderen Ende der jeweiligen Platte 2,3 angeordnet sind. Erfindungsgemäss ist es auch möglich, zwischen den einzelnen Fussplatten 3 eine Vorspannung vorzusehen. Die Kontaktstelle 7 kann sich auch insgesamt auf die angrenzenden Fussplatten 3 beziehen, ohne dass sich ein Spalt 10 bildet. Die Abschrägungen 9, wie es in der Figur 1 bereits dargestellt ist, können sich auch auf Bereiche des Schaufelfusses 4 beziehen. Dies ist aber in der Figur 4 nicht näher dargestellt.FIG. 4 shows a section through a row of blades, the base plates 3 of the blades 1 1 , 1 2 , 1 3 , 1 n being visible in this figure.
Again, adjacent foot plates 3 meet directly and without play at the contact points 7. The contact points 7 between adjacent plates 3 are in the area of the bevels 9. In the other part of the foot plates 3, a gap 10 is formed. However, the torsional moments 12 acting on the foot plates 3 are opposite to the torsional moments 13 shown in FIG Bevels 9 are arranged at a corresponding other end of the respective plate 2, 3. According to the invention, it is also possible to provide a prestress between the individual foot plates 3. The contact point 7 can also refer overall to the adjacent foot plates 3 without a gap 10 being formed. The bevels 9, as already shown in FIG. 1, can also relate to areas of the blade root 4. However, this is not shown in detail in FIG. 4.

Da benachbarte Laufschaufeln 11,12,13,1n an der Abschrägung 9 aneinander grenzen, und das Torsionsmoment 12 in diese Richtung wirkt, stützen sich die Laufschaufeln 11,12,13,1n gegenseitig. Ein Verdrehen findet nicht oder nur in sehr geringen Masse statt, so dass die Kraft durch die Laufschaufeln 11,12,13,1n selber und nicht mehr durch den Rotor 6 (oder den Stator) bzw. durch die Nut 8 aufgenommen werden mass. Durch diese Art der Anordnung der Laufschaufeln 11,12,13,1n wird die Belastung des Rotors 6 vorteilhaft reduziert. Dies geschieht in der ersten Linie durch die spielfreie oder vorgespannte Lagerung an den Fussplatten 3 und/oder an den Schaufelfüssen 4. Die Abschrägung 9 muss dann selbstverständlich auch am Schaufelfuss 4 vorliegen, um dem vorliegenden Effekt Rechnung zu tragen.Since adjacent blades 1 1 , 1 2 , 1 3 , 1 n adjoin each other at the bevel 9, and the torsional moment 12 acts in this direction, the blades 1 1 , 1 2 , 1 3 , 1 n support each other. Twisting does not take place, or only to a very small extent, so that the force is absorbed by the rotor blades 1 1 , 1 2 , 1 3 , 1 n itself and no longer by the rotor 6 (or the stator) or by the groove 8 be measured This type of arrangement of the blades 1 1 , 1 2 , 1 3 , 1 n advantageously reduces the load on the rotor 6. This takes place in the first line through the play-free or preloaded mounting on the base plates 3 and / or on the blade feet 4. The bevel 9 must of course then also be present on the blade base 4 in order to take account of the present effect.

Der einzinkige Steckfuss, welcher in der Figur 1 dargestellt ist, ist jedoch nur beispielsweise gewählt. Als Schaufelfuss 4 können verschiedene, aus dem Stand der Technik an sich bekannte Arten, so zum Beispiel ein Hammerfuss oder Reiterfuß, verwendet werden. The single-pronged plug-in foot, which is shown in FIG. 1, is only for example chosen. As a blade root 4 can be different from the State of the art types known per se, for example a hammer foot or rider's foot.

Besonders bemerkenswert ist allerdings, dass nun auch Schaufelfüsse 4 verwendet werden können, die bislang nicht oder nur unter erschwerten Bedingungen einsetzbar waren. Dies ist durch die verringerte Kraftübertragung vom Schaufelfuss 4 auf den Rotor 6 oder auf den Stator möglich. Da die Schaufelfüsse 4 und auch der Rotor 6 oder der Stator kleiner dimensioniert werden können (z.B. in der Breite), kann die Gesamtlänge des Rotors 6 verkürzt oder bei gleicher Länge des Rotors 6 (Stators) der Wirkungsgrad der Strömungsmaschine durch zusätzliche, Schaufelreihen erhöht werden. Vorhandene Rotoren 6 (Statoren) können auch leicht auf die neue Art der Befestigung der Laufschaufeln 1 umgerüstet werden. Dies ist ein Vorteil, da nun einfachere Schaufeln 1, welche kostengünstiger gefertigt werden können, eingesetzt werden können. Beispielsweise kann der in der Figur 1 gezeigte Steckfuss oder auch ein Hammerfuss auf einfache Weise mit bekannten Fräsverfahren hergestellt werden.It is particularly noteworthy, however, that blade feet 4 are now also available can be used, which so far have been difficult or difficult Conditions were applicable. This is due to the decreased Power transmission from the blade root 4 to the rotor 6 or to the stator possible. Because the blade roots 4 and also the rotor 6 or the stator are smaller can be dimensioned (e.g. in width), the total length of the Shortened rotor 6 or the same length of the rotor 6 (stator) Efficiency of the turbomachine through additional rows of blades increase. Existing rotors 6 (stators) can also easily on the new type of attachment of the blades 1 to be converted. This is a Advantage, since simpler blades 1, which are manufactured more cost-effectively can be used. For example, in the Figure 1 shown plug-in foot or a hammer foot in a simple manner Known milling processes are manufactured.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1,11,12,13,1n 1.1 1 , 1 2 , 1 3 , 1 n
Schaufelshovel
22
Deckplattecover plate
33
Fussplattefootplate
44
Schaufelfussblade root
4a4a
einzinkiger Schaufelfusssingle-pronged blade root
55
Schaufelblattairfoil
66
Rotorrotor
77
Kontaktstellecontact point
88th
Nutgroove
99
Abschrägungbevel
1010
Spaltgap
1111
Lochhole
1212
Torsionsmoment an Fussplatte 3Torsional moment on base plate 3
1313
Torsionsmoment an Deckplatte 2Torsional moment on cover plate 2
1414
TurbinenschaufelspitzeTurbine blade tip

Claims (6)

  1. Fastening of blades (1, 11, 12, 13, 1n) of a turbomachine to a rotor (6) or stator, the blades (1, 11, 12, 13, 1n) being fastened to the rotor (6) or stator by means of blade roots (4), and the blades (1, 11, 12, 13, 1n) having a root plate (3), a cover plate (2) or supporting wing above the blade root (4) and a blade leaf (5), and a torsional moment (13) acting on the cover plate (2) or on the supporting wing as a result of the installation of the blades (1, 11, 12, 13, 1n), characterized in that, after the installation of all the blades (1, 11, 12, 13, 1n), the blades (1, 11, 12, 13, 1n) are contiguous to one another on the rotor (6) or stator at the root plate (3) and/or at the blade root (4) without play or with a prestress and are therefore supported relative to one another with respect to torsional moments (12), the torsional moments (12) which act at the root plates (3) and/or at the blade roots (4) being opposite to the torsional moments (13) which act at the cover plate (2) or at the supporting wing.
  2. Fastening of blades (1, 11, 12, 13, 1n) according to Claim 1, characterized in that both the root plate (3) and/or the blade root (4) and the cover plate (2) or the supporting wing have a bevel (9) which is arranged at the point at which the applied torsional moments (12, 13) act and at which the blades (1, 11, 12, 13, 1n) are supported relative to one another.
  3. Fastening of blades (1, 11, 12, 13, 1n) according to Claim 1 or 2, characterized in that the cover plate (2) or the supporting wing is arranged on the blade leaf (5) between the root plate (3) and the blade tip (14).
  4. Fastening of blades (1, 11, 12, 13, 1n) according to Claim 1, 2 or 3, characterized in that a single-prong (4a) or multi-prong insertion root or a hammerhead root is used as the blade root (4).
  5. Fastening of blades (1, 11, 12, 13, 1n) according to Claim 4, characterized in that in the blade root (4) there are additionally holes (11) through which the blade root (4) can be fastened to the rotor (6) or stator by means of bolts.
  6. Fastening of blades (1, 11, 12, 13, 1n) according to Claim 4 or 5, characterized in that the blades (1, 11, 12, 13, 1n) are guide vanes or moving blades of a turbine or compressor.
EP01914106A 2000-03-23 2001-03-22 Fastening of the blades of a compression machine Expired - Lifetime EP1266129B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10014189 2000-03-23
DE10014189A DE10014189A1 (en) 2000-03-23 2000-03-23 Blade fastening for rotating machinery has blades fitted in slots without play or with pretensioning so that torsional moments acting on inner platform or blade roots oppose torsional moments acting upon outer platform or support wing
PCT/IB2001/000441 WO2001071165A1 (en) 2000-03-23 2001-03-22 Fastening of the blades of a compression machine

Publications (2)

Publication Number Publication Date
EP1266129A1 EP1266129A1 (en) 2002-12-18
EP1266129B1 true EP1266129B1 (en) 2004-12-22

Family

ID=7635889

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01914106A Expired - Lifetime EP1266129B1 (en) 2000-03-23 2001-03-22 Fastening of the blades of a compression machine

Country Status (11)

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US (1) US6830435B2 (en)
EP (1) EP1266129B1 (en)
CN (1) CN1313708C (en)
AU (1) AU3948501A (en)
CZ (1) CZ298200B6 (en)
DE (2) DE10014189A1 (en)
EE (1) EE04689B1 (en)
PL (1) PL199066B1 (en)
RU (1) RU2311537C2 (en)
UA (1) UA73765C2 (en)
WO (1) WO2001071165A1 (en)

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US8262359B2 (en) 2007-01-12 2012-09-11 Alstom Technology Ltd. Diaphragm for turbomachines and method of manufacture
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Also Published As

Publication number Publication date
RU2311537C2 (en) 2007-11-27
EP1266129A1 (en) 2002-12-18
DE10014189A1 (en) 2001-09-27
CZ298200B6 (en) 2007-07-18
CZ20023152A3 (en) 2003-06-18
WO2001071165A1 (en) 2001-09-27
AU3948501A (en) 2001-10-03
US6830435B2 (en) 2004-12-14
UA73765C2 (en) 2005-09-15
US20030143077A1 (en) 2003-07-31
CN1313708C (en) 2007-05-02
PL357310A1 (en) 2004-07-26
PL199066B1 (en) 2008-08-29
DE50104883D1 (en) 2005-01-27
EE200200542A (en) 2004-04-15
EE04689B1 (en) 2006-08-15
CN1423725A (en) 2003-06-11

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