EP1413712A1 - Shrouded turbine blade with tip sealing - Google Patents

Shrouded turbine blade with tip sealing Download PDF

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Publication number
EP1413712A1
EP1413712A1 EP02023473A EP02023473A EP1413712A1 EP 1413712 A1 EP1413712 A1 EP 1413712A1 EP 02023473 A EP02023473 A EP 02023473A EP 02023473 A EP02023473 A EP 02023473A EP 1413712 A1 EP1413712 A1 EP 1413712A1
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EP
European Patent Office
Prior art keywords
blade
shroud
sealing rib
recess
circumferential direction
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP02023473A
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German (de)
French (fr)
Inventor
Peter Tiemann
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Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP02023473A priority Critical patent/EP1413712A1/en
Publication of EP1413712A1 publication Critical patent/EP1413712A1/en
Withdrawn legal-status Critical Current

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—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 rotor blade of a turbomachine which has a rotor blade root, a platform, a wing blade and a shroud in succession along a longitudinal direction, a sealing rib running along a circumferential direction being arranged on the outer circumference of the shroud.
  • Blades for a turbine are known from DE 19,904,229 A1.
  • the blade shows a wing blade, at the tip of which a cover band is arranged.
  • the shroud is fastened in the center of the tip and cantilevered towards the two side edges of the shroud.
  • a sealing rib is arranged on the outer circumference of the cover band and runs from one freely projecting side edge to the other. It is traversed by coolant channels.
  • the centrifugal forces of the rotating rotor cause the freely projecting side edges of the shroud to move outwards. This can lead to contact between the sealing rib and the opposite guide ring, the sealing rib being deformed at its ends.
  • the outwardly striving side edges of the cover tape in the middle of the sealing rib lead to compressive stresses, which deform the sealing rib if necessary.
  • the object of the present invention is to provide a moving blade in which the above disadvantages are avoided.
  • a steam turbine and a gas turbine are to be specified in which the aforementioned disadvantages do not occur.
  • the object related to the rotor blade is achieved according to the invention by the sealing rib in Longitudinal direction of the blade has a local cross-sectional enlargement.
  • the local cross-sectional enlargement increases the load-bearing area, the cross-sectional area, in the sealing rib.
  • the sealing rib thus resists its internal compressive stresses during the operation of the turbomachine.
  • the compressive stress resulting from the centrifugal forces is almost identical in relation to a sealing rib without local cross-sectional enlargement, but this advantageously has an effect on a larger area of the sealing rib, so that deformation of the sealing rib is avoided.
  • the local cross-sectional enlargement extending over the entire extent of the sealing rib and the cover band running parallel to it represent the upper and lower crossbeams of an "I" in abstract form, and the sealing rib itself represents the vertical web of the "I".
  • Each cantilevered side of the shroud is therefore to be regarded as an I-shaped bending beam clamped on one side in relation to its fastening point on the blade.
  • the previously known shroud with the sealing rib forms a bending beam with an inverted T-shaped cross section. Because of the greater area moment of inertia of the I-shape compared to the T-shape, the design according to the invention is more rigid than the already known one. As a result, the shroud bends less during operation. This results in a reduction in the compressive stresses occurring in the sealing rib and also prevents the sealing rib from rubbing against the opposite guide ring.
  • the sealing rib is at least partially interrupted by a separating slot running transversely to the longitudinal direction.
  • the centrifugal forces occurring during the operation of the turbomachine cause a compressive stress in the sealing rib, which is in the middle of its longest dimension greatest is.
  • a separating slot arranged there reduces the build-up of the compressive stress. An inadmissible deformation of the sealing rib is prevented.
  • two or more parallel sealing ribs are arranged on the shroud, each of which has a local cross-sectional enlargement. A further increase in the bending stiffness of the freely projecting shroud is thus achieved.
  • the object related to the rotor blade is achieved according to the invention in that, in order to reduce the mass, a recess is arranged on the outer circumference of the shroud, which is delimited in the circumferential direction of the shroud by a first freely projecting side edge and by a second freely projecting side edge opposite the first side edge.
  • the shrouds of immediately adjacent rotor blades abut one another on a contact surface which adjoins these side edges.
  • This contact surface can thus continue to be generously dimensioned, which contributes to the strength and rigidity of the shroud ring formed by all shrouds of a moving blade ring. This prevents the blade ring from vibrating.
  • the mass taken out of the shroud from the center in the circumferential direction does not impair the strength of the shroud itself, since it has no load-bearing function.
  • the recess of the shroud can be easily manufactured if it has an identical depth over its extent in the circumferential direction.
  • a further advantageous development is provided if the maximum depth of the recess is arranged centrally between the first and second side edges delimiting the recess in the circumferential direction and that the depth of the recess decreases towards both sides.
  • the changing depth of the recess is a form that stiffens the shroud.
  • the characterizing features of claims 1 and 6 are applied together.
  • the combination of the features combines advantages and effects.
  • the compressive stress prevailing in the sealing ribs can be significantly reduced during operation of the gas turbine and the rubbing of the sealing rib on the guide ring can also be prevented.
  • the recess is expediently arranged in between.
  • the rotor blade can expediently be designed as a compressor rotor blade, as well as a turbine rotor blade, in which the heat resistance of the cover band and the sealing rib produced in this way is particularly useful.
  • the object related to the gas turbine is achieved in that the gas turbine is operated with a moving blade according to claims 1 to 11.
  • the object related to the steam turbine is achieved in that the steam turbine is operated with a moving blade according to claims 1 to 11.
  • the blade 1 shown in FIG. 1 has a blade root 2, a platform 3, a wing 4 and a shroud 5 in succession along a longitudinal direction L.
  • Arranged on the outer circumference of the shroud 5 are two sealing ribs 6.
  • the sealing ribs In the longitudinal direction L, the sealing ribs have a local cross-sectional enlargement 7 which extends in the circumferential direction U over their entire length.
  • the longest dimension of the sealing rib 6 extending in the circumferential direction U has a separating slot 8 in the center.
  • the recess 9 arranged between the two sealing ribs 6 is delimited in the circumferential direction U by the side edges 12a and 12b.
  • the centrifugal forces 13 occurring during the operation of the turbomachine cause compressive stresses 14 in the sealing ribs 6, which have their maximum in the middle of the longest dimension of the sealing ribs 6.
  • the separation slot 8 prevents the deforming occurrence of the compressive stress 14 and thus offers a gap which can be reduced under the influence of flying forces.
  • FIG. 2 shows a cross section through the tip of an already known rotor blade 1 with shroud 5 and sealing rib 6.
  • the compressive stresses 14 act in the sealing rib 6 due to the centrifugal forces 13.
  • the mechanical analysis of the sealing rib 6 is symbolized by the T-shaped profile 15 turned upside down.
  • the sealing rib 6 and the shroud 5 are attached to the wing blade 4 and collar in the direction of the two side edges 12a, 12b.
  • the two freely projecting areas in connection with the acting centrifugal forces 13 each behave like a cantilever clamped on one side under a linear load.
  • One-sided refers to the fastening point of the cover band 5 on the wing blade 4.
  • the compressive stresses 14 occurring from the two free ends of the clamped bending beams meet in the middle of the longest dimension of the sealing rib 6 and can act there deforming it.
  • the sealing rib 6 has a cross-sectional enlargement 7 local in the longitudinal direction L. Due to the local cross-sectional enlargement 7 of the sealing rib 6 in connection with the shroud 5, the mechanically effective profile can be symbolically represented by an I 16.
  • the compressive stresses 14, caused by the centrifugal forces 13, are lower due to the more rigid I-shaped profile 16, which has a larger moment of inertia than the T-shaped profile.
  • the arrangement of the local cross-sectional enlargement 7 of the sealing rib 6 gives the shroud 5 and the sealing rib 6 increased rigidity.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The turbine blade has a blade foot (2), a platform (3), a vane blade (4), a cover band (5) and a sealing rib running (6) in a peripheral direction arranged in succession along a longitudinal direction. The sealing rib has a local increase in cross-section (7) in the longitudinal direction (L) of the blade. The cross-section of the sealing rib combined with the cover band is I-shaped. Independent claims are also included for the following: (a) a gas turbine with an inventive turbine blade (b) and a steam turbine with an inventive turbine blade.

Description

Die vorliegende Erfindung betrifft eine Laufschaufel einer Strömungsmaschine, die entlang einer Längsrichtung aufeinanderfolgend einen Laufschaufelfuß, eine Plattform, ein Flügelblatt und ein Deckband aufweist, wobei am Außenumfang des Deckbandes eine entlang einer Umfangsrichtung verlaufende Dichtrippe angeordnet ist.The present invention relates to a rotor blade of a turbomachine which has a rotor blade root, a platform, a wing blade and a shroud in succession along a longitudinal direction, a sealing rib running along a circumferential direction being arranged on the outer circumference of the shroud.

Es sind Laufschaufeln für eine Turbine aus der DE 19,904,229 A1 bekannt. Die Laufschaufel zeigt ein Flügelblatt, an deren Spitze ein Deckband angeordnet ist. Das Deckband ist mittig an der Spitze befestigt und zu den beiden Seitenrändern des Deckbands hin frei auskragend. Eine Dichtrippe ist am Außenumfang des Deckbands angeordnet und verläuft von einem frei auskragenden Seitenrand zu dem anderen. Dabei ist sie von Kühlmittelkanälen durchzogen. Die Zentrifugalkräfte des rotierenden Rotors bedingen, dass die frei auskragenden Seitenränder des Deckbandes sich nach außen hin bewegen. Dies kann zu einem Kontakt zwischen Dichtrippe und dem gegenüberliegenden Führungsring führen, wobei die Dichtrippe dabei an ihren Enden deformiert wird. Gleichfalls führen die nach außen strebenden Seitenränder des Deckbandes in der Mitte der Dichtrippe zu Druckspannungen, die Dichtrippe gegebenenfalls verformen.Blades for a turbine are known from DE 19,904,229 A1. The blade shows a wing blade, at the tip of which a cover band is arranged. The shroud is fastened in the center of the tip and cantilevered towards the two side edges of the shroud. A sealing rib is arranged on the outer circumference of the cover band and runs from one freely projecting side edge to the other. It is traversed by coolant channels. The centrifugal forces of the rotating rotor cause the freely projecting side edges of the shroud to move outwards. This can lead to contact between the sealing rib and the opposite guide ring, the sealing rib being deformed at its ends. Likewise, the outwardly striving side edges of the cover tape in the middle of the sealing rib lead to compressive stresses, which deform the sealing rib if necessary.

Aufgabe der vorliegenden Erfindung ist es eine Laufschaufel anzugeben, bei der die vorstehenden Nachteile vermieden werden. Gleichfalls soll eine Dampfturbine und eine Gasturbine angegeben werden, bei denen die vorgenannten Nachteile nicht auftreten.The object of the present invention is to provide a moving blade in which the above disadvantages are avoided. Likewise, a steam turbine and a gas turbine are to be specified in which the aforementioned disadvantages do not occur.

Die auf die Laufschaufel bezogene Aufgabe wird erfindungsgemäß gelöst, in dem die Dichtrippe in Längsrichtung der Laufschaufel eine lokale Querschnittsvergrößerung aufweist.The object related to the rotor blade is achieved according to the invention by the sealing rib in Longitudinal direction of the blade has a local cross-sectional enlargement.

Die lokale Querschnittsvergrößerung vergrößert die tragende Fläche, die Querschnittsfläche, in der Dichtrippe. Somit widersteht die Dichtrippe ihren inneren Druckspannungen während des Betriebes der Strömungsmaschine. Die durch die Zentrifugalkräfte hervorgehende Druckspannung ist, bezogen auf eine Dichtrippe ohne lokale Querschnittsvergrößerung, nahezu identisch, wobei diese sich jedoch vorteilhafterweise auf einer größere Fläche der Dichtrippe auswirkt, so dass ein Verformen der Dichtrippe vermieden wird.The local cross-sectional enlargement increases the load-bearing area, the cross-sectional area, in the sealing rib. The sealing rib thus resists its internal compressive stresses during the operation of the turbomachine. The compressive stress resulting from the centrifugal forces is almost identical in relation to a sealing rib without local cross-sectional enlargement, but this advantageously has an effect on a larger area of the sealing rib, so that deformation of the sealing rib is avoided.

Abstrahiert stellt die über die gesamte Ausdehnung der Dichtrippe verlaufende lokale Querschnittsvergrößerung und das dazu parallel verlaufende Deckband den oberen und unteren Querbalken eines "I" dar, und die Dichtrippe selbst den vertikal verlaufenden Steg des "I". Jede frei auskragende Seite des Deckbands ist bezogen auf dessen Befestigungspunkt an der Schaufel somit wie ein einseitig eingespannter I-förmiger Biegebalken zu betrachten. Entgegen der Erfindung bildet das bisher bereits bekannte Deckband mit der Dichtrippe einen Biegebalken mit einem umgedreht T-förmigen Querschnitt. Wegen des größeren Flächenträgheitsmomentes der I-Form gegenüber der T-Form ist die erfindungsgemäße Ausführung biegesteifer als die bereits bekannte. Folglich biegt sich das Deckband während des Betriebs weniger. Somit ist eine Reduzierung der auftretenden Druckspannungen in der Dichtrippe gegeben und gleichfalls wird das Anstreifen der Dichtrippe am gegenüberliegenden Führungsring verhindert.The local cross-sectional enlargement extending over the entire extent of the sealing rib and the cover band running parallel to it represent the upper and lower crossbeams of an "I" in abstract form, and the sealing rib itself represents the vertical web of the "I". Each cantilevered side of the shroud is therefore to be regarded as an I-shaped bending beam clamped on one side in relation to its fastening point on the blade. Contrary to the invention, the previously known shroud with the sealing rib forms a bending beam with an inverted T-shaped cross section. Because of the greater area moment of inertia of the I-shape compared to the T-shape, the design according to the invention is more rigid than the already known one. As a result, the shroud bends less during operation. This results in a reduction in the compressive stresses occurring in the sealing rib and also prevents the sealing rib from rubbing against the opposite guide ring.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist die Dichtrippe durch einen quer zur Längsrichtung verlaufenden Trennschlitz mindestens teilweise unterbrochen. Die während des Betriebes der Strömungsmaschine auftretenden Zentrifugalkräfte bedingen eine Druckspannung in der Dichtrippe, die in der Mitte ihrer längsten Ausdehnung am größten ist. Ein dort angeordneter Trennschlitz vermindert das Aufbauen der Druckspannung. Eine unzulässige Deformation der Dichtrippe wird verhindert.In a further advantageous embodiment of the invention, the sealing rib is at least partially interrupted by a separating slot running transversely to the longitudinal direction. The centrifugal forces occurring during the operation of the turbomachine cause a compressive stress in the sealing rib, which is in the middle of its longest dimension greatest is. A separating slot arranged there reduces the build-up of the compressive stress. An inadmissible deformation of the sealing rib is prevented.

Vorzugsweise sind am Deckband zwei oder mehrere parallel verlaufende Dichtrippen angeordnet, die jeweils eine lokale Querschnittsvergrößerung aufweisen. Eine weitere Vergrößerung der Biegesteifigkeit des frei auskragenden Deckbandes wird somit erzielt.Preferably two or more parallel sealing ribs are arranged on the shroud, each of which has a local cross-sectional enlargement. A further increase in the bending stiffness of the freely projecting shroud is thus achieved.

Ebenso wird die auf die Laufschaufel bezogene Aufgabe erfindungsgemäß dadurch gelöst, dass zur Massenreduzierung am Außenumfang des Deckbandes eine Ausnehmung angeordnet ist, die in Umfangsrichtung des Deckbandes von einem ersten frei auskragenden Seitenrand und von einem dem ersten Seitenrand gegenüberliegenden zweiten frei auskragenden Seitenrand begrenzt wird. Die Deckbänder unmittelbar benachbarter Laufschaufeln liegen gegenseitig an einer Kontaktfläche an, die an diesen Seitenrändern angrenzt. Diese Kontaktfläche kann somit weiterhin großzügig dimensioniert ausfallen, welches zur Festigkeit und Steifigkeit des von allen Deckbändern geformten Deckbandringes eines Laufschaufelrings beiträgt. Ein sich Aufschwingung des Laufschaufelrings wird somit verhindert. Die aus in Umfangsrichtung betrachtet mittig aus dem Deckband herausgenommene Masse beeinträchtig nicht Festigkeit des Deckbandes selber, da diese keine tragende Funktion aufweist.Likewise, the object related to the rotor blade is achieved according to the invention in that, in order to reduce the mass, a recess is arranged on the outer circumference of the shroud, which is delimited in the circumferential direction of the shroud by a first freely projecting side edge and by a second freely projecting side edge opposite the first side edge. The shrouds of immediately adjacent rotor blades abut one another on a contact surface which adjoins these side edges. This contact surface can thus continue to be generously dimensioned, which contributes to the strength and rigidity of the shroud ring formed by all shrouds of a moving blade ring. This prevents the blade ring from vibrating. The mass taken out of the shroud from the center in the circumferential direction does not impair the strength of the shroud itself, since it has no load-bearing function.

In einer weiteren Ausgestaltung ist eine einfache Herstellbarkeit der Ausnehmung des Deckbandes gegeben, wenn diese über ihre Erstreckung in Umfangsrichtung eine identische Tiefe aufweist.In a further embodiment, the recess of the shroud can be easily manufactured if it has an identical depth over its extent in the circumferential direction.

Eine weitere vorteilhafte Weiterbildung ist gegeben, wenn die maximale Tiefe der Ausnehmung mittig zwischen dem die Ausnehmung in Umfangsrichtung begrenzenden ersten und zweiten Seitenrand angeordnet ist und dass die Tiefe der Ausnehmung sich zu beiden Seitenrändern hin verringert. Die sich verändernde Tiefe der Ausnehmung ist dabei eine das Deckband versteifende Form.A further advantageous development is provided if the maximum depth of the recess is arranged centrally between the first and second side edges delimiting the recess in the circumferential direction and that the depth of the recess decreases towards both sides. The changing depth of the recess is a form that stiffens the shroud.

Vorzugsweise werden die kennzeichnenden Merkmale von Anspruch 1 und 6 gemeinsam angewendet. Das Zusammenfügen der Merkmale kombiniert Vorteile und Wirkung. Die in den Dichtrippen herrschende Druckspannung kann während des Betriebes der Gasturbine wesentlich verringert und gleichfalls das Anstreifen der Dichtrippe am Führungsring verhindert werden.Preferably, the characterizing features of claims 1 and 6 are applied together. The combination of the features combines advantages and effects. The compressive stress prevailing in the sealing ribs can be significantly reduced during operation of the gas turbine and the rubbing of the sealing rib on the guide ring can also be prevented.

Zweckmäßigerweise wird bei Vorhandensein zweier Dichtrippen die Ausnehmung dazwischen angeordnet.If two sealing ribs are present, the recess is expediently arranged in between.

Zweckmäßigerweise kann die Laufschaufel als Verdichterlaufschaufel ausgebildet sein, als auch als Turbinenlaufschaufel, bei der die so hergestellte Heißfestigkeit des Deckbandes und der Dichtrippe von besonderem Nutzen ist.The rotor blade can expediently be designed as a compressor rotor blade, as well as a turbine rotor blade, in which the heat resistance of the cover band and the sealing rib produced in this way is particularly useful.

Die auf die Gasturbine bezogene Aufgabe wird gelöst, indem die Gasturbine mit einer Laufschaufel gemäß den Ansprüchen 1 bis 11 betrieben wird.The object related to the gas turbine is achieved in that the gas turbine is operated with a moving blade according to claims 1 to 11.

Die auf die Dampfturbine bezogene Aufgabe wird gelöst, indem die Dampfturbine mit einer Laufschaufel gemäß den Ansprüchen 1 bis 11 betrieben wird.The object related to the steam turbine is achieved in that the steam turbine is operated with a moving blade according to claims 1 to 11.

Nachstehend wird die Erfindung anhand von Ausführungsbeispielen näher beschrieben, die schematisch in der Zeichnung dargestellt sind. Dabei zeigt:

Fig. 1
Laufschaufel mit einem Deckband,
Fig. 2
Deckband mit bereits bekannter Dichtrippe,
Fig. 3
Deckband mit erfindungsgemäßer Dichtrippe.
The invention is described in more detail below on the basis of exemplary embodiments which are shown schematically in the drawing. It shows:
Fig. 1
Rotor blade with a shroud,
Fig. 2
Shroud with already known sealing rib,
Fig. 3
Shroud with sealing rib according to the invention.

Die in Fig. 1 dargestellte Laufschaufel 1 weist entlang einer Längsrichtung L aufeinanderfolgend einen Laufschaufelfuß 2, eine Plattform 3, einen Flügel 4 und ein Deckband 5 auf. Am Außenumfang des Deckbandes 5 angeordnet befinden sich zwei Dichtrippen 6. In Längsrichtung L weisen dabei die Dichtrippen eine lokale Querschnittsvergrößerung 7 auf, die in Umfangsrichtung U über ihre komplette Länge verläuft. Die in Umfangsrichtung U verlaufende Dichtrippe 6 weist in ihrer längsten Ausdehnung mittig einen Trennschlitz 8 auf. Die zwischen den beiden Dichtrippen 6 angeordnete Ausnehmung 9 ist in Umfangsrichtung U von den Seitenrändern 12a und 12b begrenzt.The blade 1 shown in FIG. 1 has a blade root 2, a platform 3, a wing 4 and a shroud 5 in succession along a longitudinal direction L. Arranged on the outer circumference of the shroud 5 are two sealing ribs 6. In the longitudinal direction L, the sealing ribs have a local cross-sectional enlargement 7 which extends in the circumferential direction U over their entire length. The longest dimension of the sealing rib 6 extending in the circumferential direction U has a separating slot 8 in the center. The recess 9 arranged between the two sealing ribs 6 is delimited in the circumferential direction U by the side edges 12a and 12b.

Die Existenz der Seitenränder 12a, 12b ermöglicht zur Stabilisierung des Deckbandrings eine großzügige Dimensionierung der Kontaktflächen 10 zu den benachbarten Laufschaufeln 1. Während des Betriebes der Strömungsmaschine liegen die Kontaktflächen 10 der Deckbänder 5 benachbarter Laufschaufeln 1 formschlüssig aneinander.The existence of the side edges 12a, 12b enables a generous dimensioning of the contact surfaces 10 to the adjacent rotor blades 1 in order to stabilize the shroud ring.

Die während des Betriebes der Strömungsmaschine auftretenden Zentrifugalkräfte 13 bewirken in den Dichtrippen 6 Druckspannungen 14, die ihr Maximum in der Mitte der längsten Ausdehnung der Dichtrippen 6 haben. Der Trennschlitz 8 verhindert das deformierende Auftreten der Druckspannung 14 und bietet so einen Spalt, der sich unter Fliegkrafteinwirkung verkleinern kann.The centrifugal forces 13 occurring during the operation of the turbomachine cause compressive stresses 14 in the sealing ribs 6, which have their maximum in the middle of the longest dimension of the sealing ribs 6. The separation slot 8 prevents the deforming occurrence of the compressive stress 14 and thus offers a gap which can be reduced under the influence of flying forces.

In Fig. 2 ist ein Querschnitt durch die Spitze einer bereits bekannten Laufschaufel 1 mit Deckband 5 und Dichtrippe 6 dargestellt. Während des Betriebes der Strömungsmaschine wirken aufgrund der Zentrifugalkräfte 13 in der Dichtrippe 6 die Druckspannungen 14. Die Betrachtung der Dichtrippe 6 unter mechanischen Aspekten wird durch das auf den Kopf gedrehte T-förmige Profil 15 symbolisiert. Die Dichtrippe 6 und das Deckband 5 sind am Flügelblatt 4 befestigt und kragen in Richtung der zwei Seitenrändern 12a, 12b frei aus. Die beiden frei auskragenden Bereiche in Verbindung mit den wirkenden Zentrifugalkräften 13 verhalten sich dabei jeweils wie ein einseitig eingespannter Biegebalken unter einer Linienlast. Einseitig bezieht sich auf den Befestigungspunkt des Deckbandes 5 am Flügelblatt 4. Die von den beiden freien Enden der eingespannten Biegebalken auftretenden Druckspannungen 14 treffen sich in der Mitte der längsten Ausdehnung der Dichtrippe 6 und können dort deformierend auf diese wirken.2 shows a cross section through the tip of an already known rotor blade 1 with shroud 5 and sealing rib 6. During operation of the turbomachine, the compressive stresses 14 act in the sealing rib 6 due to the centrifugal forces 13. The mechanical analysis of the sealing rib 6 is symbolized by the T-shaped profile 15 turned upside down. The sealing rib 6 and the shroud 5 are attached to the wing blade 4 and collar in the direction of the two side edges 12a, 12b. The two freely projecting areas in connection with the acting centrifugal forces 13 each behave like a cantilever clamped on one side under a linear load. One-sided refers to the fastening point of the cover band 5 on the wing blade 4. The compressive stresses 14 occurring from the two free ends of the clamped bending beams meet in the middle of the longest dimension of the sealing rib 6 and can act there deforming it.

Fig. 3 zeigt die Spitze einer erfindungsgemäßen Laufschaufel 1. Die Dichtrippe 6 weist eine in Längsrichtung L lokale Querschnittsvergrößerung 7 auf. Durch die lokale Querschnittsvergrößerung 7 der Dichtrippe 6 in Verbindung mit dem Deckband 5 kann das mechanische wirksame Profil durch ein I 16 symbolisch dargestellt werden.3 shows the tip of a rotor blade 1 according to the invention. The sealing rib 6 has a cross-sectional enlargement 7 local in the longitudinal direction L. Due to the local cross-sectional enlargement 7 of the sealing rib 6 in connection with the shroud 5, the mechanically effective profile can be symbolically represented by an I 16.

Die Druckspannungen 14, verursacht von den Zentrifugalkräften 13, sind aufgrund des biegesteiferen I-förmigen Profils 16, welches ein größeres Flächenträgheitsmoment aufweist als das T-förmigen Profil, geringer. Durch die Anordnung der lokalen Querschnittsvergrößerung 7 der Dichtrippe 6 erhält das Deckband 5 und die Dichtrippe 6 eine erhöhte Steifigkeit.The compressive stresses 14, caused by the centrifugal forces 13, are lower due to the more rigid I-shaped profile 16, which has a larger moment of inertia than the T-shaped profile. The arrangement of the local cross-sectional enlargement 7 of the sealing rib 6 gives the shroud 5 and the sealing rib 6 increased rigidity.

Claims (13)

Laufschaufel (1) einer Strömungsmaschine,
die entlang einer Längsrichtung (L) aufeinanderfolgend einen Laufschaufelfuß (2) (2), eine Plattform (3), ein Flügelblatt (4) und ein Deckband (5) aufweist, wobei am Außenumfang des Deckbands (5) eine entlang einer Umfangsrichtung (U) verlaufende Dichtrippe (6) angeordnet ist,
dadurch gekennzeichnet,
dass die Dichtrippe (6) in Längsrichtung (L) der Laufschaufel (1) eine lokale Querschnittsvergrößerung (7) aufweist.Blade (1) of a turbomachine,
which has a blade root (2) (2), a platform (3), a wing blade (4) and a shroud (5) in succession along a longitudinal direction (L), with a along a circumferential direction (U ) extending sealing rib (6) is arranged,
characterized,
that the sealing rib (6) has a local cross-sectional enlargement (7) in the longitudinal direction (L) of the rotor blade (1). Laufschaufel (1) nach Anspruch 1,
dadurch gekennzeichnet,
dass die Dichtrippe in Verbindung mit dem Deckband im Querschnitt I-förmig ist.Blade (1) according to claim 1,
characterized,
that the sealing rib in connection with the shroud is I-shaped in cross section. Laufschaufel (1) nach Anspruch 2,
dadurch gekennzeichnet,
dass die lokale Querschnittsvergrößerung (7) über die längste Ausdehnung der Dichtrippe (6) angeordnet ist.Blade (1) according to claim 2,
characterized,
that the local cross-sectional enlargement (7) is arranged over the longest dimension of the sealing rib (6). Laufschaufel (1) nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet,
dass die Dichtrippe (6) durch einen quer der Längsrichtung (L) verlaufenden Trennschlitz (8) mindestens teilweise unterbrochen ist.Blade (1) according to one of claims 1 to 3,
characterized,
that the sealing rib (6) is at least partially interrupted by a separating slot (8) running transversely to the longitudinal direction (L). Laufschaufel (1) nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet,
dass die Laufschaufel (1) am äußeren Umfang des Deckbandes (5) zwei oder mehr parallel verlaufende Dichtrippen (6) aufweist.Blade (1) according to one of claims 1 to 4,
characterized,
that the rotor blade (1) has two or more parallel sealing ribs (6) on the outer circumference of the shroud (5). Laufschaufel (1) einer Strömungsmaschine,
die entlang einer Längsrichtung (L) aufeinanderfolgend einen Laufschaufelfuß (2), eine Plattform (3), ein Flügelblatt (4) und ein entlang einer Umfangsrichtung (U) verlaufendes Deckband (5) aufweist, an der zur Massenreduzierung am Außenumfang des Deckbandes (5) eine Ausnehmung (9) angeordnet ist, die in Umfangsrichtung (U) des Deckbandes (5) von einem ersten frei auskragenden Seitenrand (12a) und von einem dem ersten Seitenrand (12a) gegenüberliegenden zweiten frei auskragenden Seitenrand (12b) begrenzt wird,
dadurch gekennzeichnet,
dass die maximale Tiefe der Ausnehmung (9) mittig zwischen dem die Ausnehmung (9) in Umfangsrichtung (U) begrenzenden ersten und zweiten Seitenrand (12a, 12b) angeordnet ist und dass die Tiefe der Ausnehmung (9) sich zu beiden Seitenrändern (12a, 12b) hin verringert.Blade (1) of a turbomachine,
which has a blade root (2), a platform (3), a wing blade (4) and a shroud (5) running along a circumferential direction (U) in succession along a longitudinal direction (L), on which to reduce mass on the outer circumference of the shroud (5 ) a recess (9) is arranged which is delimited in the circumferential direction (U) of the shroud (5) by a first freely projecting side edge (12a) and by a second freely projecting side edge (12b) opposite the first side edge (12a),
characterized,
that the maximum depth of the recess (9) is arranged centrally between the first and second side edges (12a, 12b) delimiting the recess (9) in the circumferential direction (U) and that the depth of the recess (9) is located on both side edges (12a, 12b) reduced. Laufschaufel (1) nach dem Oberbegriff des Anspruchs 6,
dadurch gekennzeichnet,
dass die Ausnehmung (9) des Deckbandes (5) über ihre Erstreckung in Umfangsrichtung (U) eine identische Tiefe aufweist.Blade (1) according to the preamble of claim 6,
characterized,
that the recess (9) of the shroud (5) has an identical depth over its extent in the circumferential direction (U). Laufschaufel (1) nach Anspruch 1 und 6.Blade (1) according to claim 1 and 6. Lauf schauf el (1) nach Anspruch 5 und 6,
dadurch gekennzeichnet,
dass die Ausnehmung (9) zwischen zwei Dichtrippen (6) angeordnet ist.Laufaufauf el (1) according to claim 5 and 6,
characterized,
that the recess (9) is arranged between two sealing ribs (6). Laufschaufel (1) nach einem der Ansprüche 1 bis 9,
dadurch gekennzeichnet,
dass die Laufschaufel (1) als Verdichterlaufschaufel ausgebildet ist.Blade (1) according to one of claims 1 to 9,
characterized,
that the rotor blade (1) is designed as a compressor rotor blade. Laufschaufel (1) nach einem der Ansprüche 1 bis 9,
dadurch gekennzeichnet,
dass die Laufschaufel (1) als Turbinenlaufschaufel ausgebildet ist.Blade (1) according to one of claims 1 to 9,
characterized,
that the rotor blade (1) is designed as a turbine rotor blade. Gasturbine mit einer Laufschaufel (1) nach einem der Ansprüche 1 bis 11.Gas turbine with a moving blade (1) according to one of claims 1 to 11. Dampfturbine mit einer Laufschaufel (1) nach einem der Ansprüche 1 bis 11.Steam turbine with a moving blade (1) according to one of claims 1 to 11.
EP02023473A 2002-10-21 2002-10-21 Shrouded turbine blade with tip sealing Withdrawn EP1413712A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
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Publications (1)

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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005061854A1 (en) * 2003-12-17 2005-07-07 Watson Cogeneration Company Gas turbine tip shroud rails
EP1591625A1 (en) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Gas turbine blade shroud
EP1873355A1 (en) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Turbine rotor blade
US7762779B2 (en) 2006-08-03 2010-07-27 General Electric Company Turbine blade tip shroud
DE102009030566A1 (en) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Shroud segment for placement on a bucket
EP2369134A1 (en) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Turbine blade with cavities for the reduction of weight and vibrations
FR2974842A1 (en) * 2011-05-05 2012-11-09 Snecma Seal i.e. labyrinth seal, for sealing between rotor and stator of turboshaft engine, has rubbing strip including ridge adjacent to crown, where crown is fixed at stator and strip is fixed at rotor and including notch with angular sectors
EP3006672A1 (en) * 2014-10-10 2016-04-13 Universität Stuttgart Device for influencing the flow in a turbomachine
WO2019243708A2 (en) 2018-06-20 2019-12-26 Safran Aircraft Engines Labyrinth sealing joint for an aircraft turbomachine
US11098609B2 (en) 2018-01-23 2021-08-24 MTU Aero Engines AG Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade
CN114922695A (en) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 Moving blade shroud for adjusting stage of industrial steam turbine and optimization method thereof
US11585225B2 (en) 2020-02-11 2023-02-21 MTU Aero Engines AG Blade for a turbomachine
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US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
US12000720B2 (en) 2018-09-10 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring
US12031094B2 (en) 2021-02-25 2024-07-09 Marathon Petroleum Company Lp Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers
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DE19904229A1 (en) 1999-02-03 2000-08-10 Asea Brown Boveri Cooled turbine blade has shroud formed by sealing rib with integrated cooling channels connected to coolant channel in blade

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005061854A1 (en) * 2003-12-17 2005-07-07 Watson Cogeneration Company Gas turbine tip shroud rails
US7255531B2 (en) 2003-12-17 2007-08-14 Watson Cogeneration Company Gas turbine tip shroud rails
EP1591625A1 (en) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Gas turbine blade shroud
WO2005106206A1 (en) * 2004-04-30 2005-11-10 Alstom Technology Ltd Gas turbine blade shroud
CN100404792C (en) * 2004-04-30 2008-07-23 阿尔斯通技术有限公司 Gas turbine blade shroud
US7628587B2 (en) 2004-04-30 2009-12-08 Alstom Technology Ltd Gas turbine blade shroud
EP1873355A1 (en) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Turbine rotor blade
US7762779B2 (en) 2006-08-03 2010-07-27 General Electric Company Turbine blade tip shroud
DE102009030566A1 (en) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Shroud segment for placement on a bucket
US9322281B2 (en) 2009-06-26 2016-04-26 Mtu Aero Engines Gmbh Shroud segment to be arranged on a blade
EP2369134A1 (en) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Turbine blade with cavities for the reduction of weight and vibrations
FR2974842A1 (en) * 2011-05-05 2012-11-09 Snecma Seal i.e. labyrinth seal, for sealing between rotor and stator of turboshaft engine, has rubbing strip including ridge adjacent to crown, where crown is fixed at stator and strip is fixed at rotor and including notch with angular sectors
WO2016055606A1 (en) * 2014-10-10 2016-04-14 Universität Stuttgart Device for influencing the flow in a turbomachine
EP3006672A1 (en) * 2014-10-10 2016-04-13 Universität Stuttgart Device for influencing the flow in a turbomachine
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11098609B2 (en) 2018-01-23 2021-08-24 MTU Aero Engines AG Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade
WO2019243708A2 (en) 2018-06-20 2019-12-26 Safran Aircraft Engines Labyrinth sealing joint for an aircraft turbomachine
FR3082879A1 (en) * 2018-06-20 2019-12-27 Safran Aircraft Engines LABYRINTH SEAL FOR AN AIRCRAFT TURBOMACHINE
WO2019243708A3 (en) * 2018-06-20 2020-02-20 Safran Aircraft Engines Labyrinth sealing joint for an aircraft turbomachine
US11692450B2 (en) 2018-06-20 2023-07-04 Safran Aircraft Engines Labyrinth sealing joint for an aircraft turbomachine
US12000720B2 (en) 2018-09-10 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring
US12031676B2 (en) 2019-03-25 2024-07-09 Marathon Petroleum Company Lp Insulation securement system and associated methods
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
US11585225B2 (en) 2020-02-11 2023-02-21 MTU Aero Engines AG Blade for a turbomachine
US11920096B2 (en) 2020-02-19 2024-03-05 Marathon Petroleum Company Lp Low sulfur fuel oil blends for paraffinic resid stability and associated methods
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
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US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11885739B2 (en) 2021-02-25 2024-01-30 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11921035B2 (en) 2021-02-25 2024-03-05 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US12031094B2 (en) 2021-02-25 2024-07-09 Marathon Petroleum Company Lp Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers
US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
CN114922695A (en) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 Moving blade shroud for adjusting stage of industrial steam turbine and optimization method thereof

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