EP1898050B1 - Attenuation and sealing system for turbine blades - Google Patents

Attenuation and sealing system for turbine blades Download PDF

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Publication number
EP1898050B1
EP1898050B1 EP07112566A EP07112566A EP1898050B1 EP 1898050 B1 EP1898050 B1 EP 1898050B1 EP 07112566 A EP07112566 A EP 07112566A EP 07112566 A EP07112566 A EP 07112566A EP 1898050 B1 EP1898050 B1 EP 1898050B1
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EP
European Patent Office
Prior art keywords
sealing
damping
damping element
platform
sealing system
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 - Fee Related
Application number
EP07112566A
Other languages
German (de)
French (fr)
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EP1898050A3 (en
EP1898050A2 (en
Inventor
Richard Whitton
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1898050A2 publication Critical patent/EP1898050A2/en
Publication of EP1898050A3 publication Critical patent/EP1898050A3/en
Application granted granted Critical
Publication of EP1898050B1 publication Critical patent/EP1898050B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to a turbine blade damping and sealing system comprising a centrifugal force held between opposing surfaces of adjacent platforms of the gas turbine engine blades mounted on the rotor, a straight three-sided prism having equal sized side faces forming a sealing and damping element.
  • Gas turbine engines have rotor disks with circumferentially mounted, radially extending blades consisting of a blade root, a platform, and an airfoil.
  • rotor disks with circumferentially mounted, radially extending blades consisting of a blade root, a platform, and an airfoil.
  • sealing elements are known, which are formed in cross-section specifically to the shape of the remaining space between the platforms and must be used in a special orientation in this room. Accordingly consuming the assembly and incorrect alignment of the sealing element limits its sealing and damping effect considerably.
  • the precisely matched form of sealing element and platform gap requires a considerable manufacturing effort.
  • sealing and damping elements with circular cross-sectional area, which invest in any orientation under the action of centrifugal force on the side edges of the two adjacent platforms.
  • round sealing and damping elements wear relatively quickly, so that the sealing and damping effect wears off and the sealing and damping elements must be replaced with considerable effort.
  • the invention has for its object to provide a sealing and damping system for turbine blades, which has a high sealing and damping effect and requires little installation and repair.
  • the core of the invention is the formation of a trained as a three-sided prism sealing and damping element with convex side surfaces, which allow a slight pivoting movement of the sealing element during operation and thus act as an enlarged friction surfaces.
  • the resulting increased friction results in improved vibration damping.
  • the friction-related wear leads to a mutual adaptation of the mutually connected contact surfaces.
  • manufacturing tolerances are compensated and achieved a further improved vibration damping and sealing effect. Due to the automatic mutual adaptation of the sealing or friction surfaces manufacturing inaccuracies are compensated.
  • the friction occurring due to wear can be considered constructively.
  • the manufacturing and repair costs are therefore low.
  • the opposite sealing surface of the adjacent blade platforms form an acute-angled gap into which the sealing and damping element is automatically pressed under the action of centrifugal force and rests with two curved friction surfaces on the gap surfaces.
  • Fig. 1 is between two spaced in the direction of flow stator blades 1, a rotor 2 with attached to the circumference of a rotor disk 3 turbine blades 4, consisting of a blade root 5, a blade platform 6 and an airfoil 7, respectively.
  • a rotor 2 with attached to the circumference of a rotor disk 3 turbine blades 4, consisting of a blade root 5, a blade platform 6 and an airfoil 7, respectively.
  • two adjacent platforms 6a, 6b of adjacent turbine blades 4 can be seen.
  • the right in the drawing platform 6a has a recess 8 in which a sealing and damping element 9 is held loose.
  • the open side of the recess 8 is - leaving a very narrow gap 10 a flat, substantially vertical platform edge 11 of the other platform 6b opposite and prevents falling out of the sealing and damping element 9 from the recess 8.
  • the recess 8 has an obliquely top extending sealing surface 12.
  • the sealing and damping element 9 is a straight component with the cross section of an equilateral triangle, but with rounded longitudinal edges 13 and with between the longitudinal edges 13 convexly curved - convex - friction surfaces 14 (sealing and damping surfaces, side surfaces).
  • sealing and damping element 9 applies due to the centrifugal force during rotation of the rotor 2 with its convex curved surfaces 14 to the vertical platform edge 11 and the inclined sealing surface 12 at. A rotation of the sealing and damping element 9 about its longitudinal axis is therefore not possible.

Landscapes

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

Description

Die Erfindung betrifft ein Dämpfungs- und Dichtungssystem für Turbinenschaufeln, mit einem zwischen gegenüberliegenden Flächen benachbarter Plattformen der am Rotor angebrachten Schaufeln eines Gasturbinentriebwerks unter Fliehkraftwirkung gehaltenen, ein gerades dreiseitiges Prisma mit gleich großen Seitenflächen bildenden Dichtungs- und Dämpfungselement.The invention relates to a turbine blade damping and sealing system comprising a centrifugal force held between opposing surfaces of adjacent platforms of the gas turbine engine blades mounted on the rotor, a straight three-sided prism having equal sized side faces forming a sealing and damping element.

Gasturbinentriebwerke haben Rotorscheiben mit an deren Umfang montierten, sich radial erstreckenden Schaufeln, bestehend aus einem Schaufelfuß, einer Plattform und einem Schaufelblatt. Es besteht einerseits die Notwendigkeit, den zwischen aneinander grenzenden Kanten benachbarter Plattformen verbleibenden schmalen Spalt abzudichten, um den Gasaustausch zwischen Heißgas und Kühlluft zu minimieren, und andererseits die Vibrationen zwischen der Rotorscheibe und den Schaufeln sowie zwischen den Schaufeln selbst zu dämpfen.Gas turbine engines have rotor disks with circumferentially mounted, radially extending blades consisting of a blade root, a platform, and an airfoil. On the one hand, there is a need to seal the narrow gap remaining between adjacent edges of adjacent platforms to minimize gas exchange between hot gas and cooling air and, on the other hand, to dampen vibrations between the rotor disk and the blades and between the blades themselves.

Seit langem sind bereits zwischen den Schaufelplattformen angeordnete Dichtungselemente bekannt, die im Querschnitt speziell auf die Form des zwischen den Plattformen verbleibenden Raumes ausgebildet sind und in einer speziellen Ausrichtung in diesen Raum eingesetzt werden müssen. Dementsprechend aufwendig ist die Montage und eine falsche Ausrichtung des Dichtungselements schränkt dessen Dichtungs- und Dämpfungswirkung erheblich ein. Außerdem erfordert die genau aufeinander abgestimmte Form von Dichtungselement und Plattformspalt einen erheblichen Fertigungsaufwand.For a long time already arranged between the blade platforms sealing elements are known, which are formed in cross-section specifically to the shape of the remaining space between the platforms and must be used in a special orientation in this room. Accordingly consuming the assembly and incorrect alignment of the sealing element limits its sealing and damping effect considerably. In addition, the precisely matched form of sealing element and platform gap requires a considerable manufacturing effort.

Zur Lösung dieses Problems wird in der US 4 872 812 ein Dichtungs- und Dämpfungselement mit sich um seine Längsachse erstreckenden ebenen Seitenflächen vorgeschlagen, dessen Querschnittsfläche die Form eines gleichschenkligen Dreieckes hat, das heißt, als dreiseitiges Prisma mit gleich großen Seitenflächen ausgebildet ist. Aufgrund der regelmäßigen Querschnittsform kann sich das Dichtungs- und Dämpfungselement unabhängig von seiner bei der Montage erzielten Ausrichtung unter der Wirkung der Fliehkraft mit jeweils zwei Seitenflächen an die jeweiligen Seitenkanten der benachbarten Plattformen anlegen, um den Spalt abzudichten und Vibrationen der betreffenden Schaufeln zu dämpfen. Eine hohe Dichtungs- und Dämpfungswirkung setzt jedoch enge Fertigungstoleranzen und damit einen hohen Fertigungsaufwand in Bezug auf die ebene Ausbildung der beiderseitigen Berührungsflächen voraus. Die Dichtungs- und Dämpfungswirkung kann zudem durch Verschleiß an den ebenen Berührungsflächen vermindert werden.To solve this problem is in the U.S. 4,872,812 a sealing and damping element with extending around its longitudinal axis extending flat side surfaces proposed, whose cross-sectional area has the shape of an isosceles triangle, that is, is designed as a three-sided prism with equal side surfaces. Due to the regular cross-sectional shape, regardless of its alignment achieved during assembly, the sealing and damping element can apply two side faces to the respective side edges of adjacent platforms under the effect of centrifugal force to seal the gap and dampen vibrations of the respective blades. However, a high sealing and damping effect requires close manufacturing tolerances and thus a high manufacturing outlay in relation to the planar design of the mutual contact surfaces. The sealing and damping effect can also be reduced by wear on the flat contact surfaces.

Zur Senkung des Fertigungs- und Montageaufwandes wurden bereits Dichtungs- und Dämpfungselemente mit kreisförmiger Querschnittsfläche vorgeschlagen, die sich in jeder Ausrichtung unter der Wirkung der Fliehkraft an die Seitenkanten der beiden benachbarten Plattformen anlegen. Es wurde jedoch festgestellt, dass runde Dichtungs- und Dämpfungselemente relativ schnell verschleißen, so dass die Dichtungs- und Dämpfungswirkung nachlässt und die Dichtungs- und Dämpfungselemente mit erheblichem Aufwand ausgetauscht werden müssen.To reduce the manufacturing and assembly costs have already been proposed sealing and damping elements with circular cross-sectional area, which invest in any orientation under the action of centrifugal force on the side edges of the two adjacent platforms. However, it has been found that round sealing and damping elements wear relatively quickly, so that the sealing and damping effect wears off and the sealing and damping elements must be replaced with considerable effort.

Der Erfindung liegt die Aufgabe zugrunde, ein Dichtungs- und Dämpfungssystem für Turbinenschaufeln anzugeben, das eine hohe Dichtungs- und Dämpfungswirkung aufweist und eine geringen Montage- und Reparaturaufwand erfordert.The invention has for its object to provide a sealing and damping system for turbine blades, which has a high sealing and damping effect and requires little installation and repair.

Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Dichtungs- und Dämpfungssystem gelöst. Vorteilhafte Weiterbildungen der Erfindung sind Gegenstand der Unteransprüche.According to the invention the object is achieved with a trained according to the features of claim 1 sealing and damping system. Advantageous developments of the invention are the subject of the dependent claims.

Kern der Erfindung ist die Ausbildung eines als dreiseitiges Prisma ausgebildeten Dichtungs- und Dämpfungselements mit konvex gewölbten Seitenflächen, die im Betrieb eine leichte Schwenkbewegung des Dichtungselements erlauben und somit als vergrößerte Reibflächen wirken. Die dadurch verstärkte Reibung hat eine verbesserte Schwingungsdämpfung zur Folge. Der reibungsbedingte Verschleiß führt zu einer gegenseitigen Anpassung der miteinander in Verbindung stehenden Berührungsflächen. Dadurch werden Fertigungstoleranzen ausgeglichen und eine weiter verbesserte Schwingungsdämpfung und Dichtwirkung erzielt. Durch die selbsttätige gegenseitige Anpassung der Dicht- bzw. Reibflächen werden Fertigungsungenauigkeiten ausgeglichen. Der reibungsbedingt auftretende Verschleiß kann konstruktiv berücksichtigt werden. Der Fertigungs- und Reparaturaufwand ist daher gering.The core of the invention is the formation of a trained as a three-sided prism sealing and damping element with convex side surfaces, which allow a slight pivoting movement of the sealing element during operation and thus act as an enlarged friction surfaces. The resulting increased friction results in improved vibration damping. The friction-related wear leads to a mutual adaptation of the mutually connected contact surfaces. As a result, manufacturing tolerances are compensated and achieved a further improved vibration damping and sealing effect. Due to the automatic mutual adaptation of the sealing or friction surfaces manufacturing inaccuracies are compensated. The friction occurring due to wear can be considered constructively. The manufacturing and repair costs are therefore low.

Die gegenüber liegenden Dichtfläche der benachbarten Schaufelplattformen bilden einen spitzwinkligen Spalt, in den das Dichtungs- und Dämpfungselement unter der Wirkung der Fliehkraft selbsttätig gedrückt wird und mit zwei gewölbten Reibflächen an den Spaltflächen anliegt.The opposite sealing surface of the adjacent blade platforms form an acute-angled gap into which the sealing and damping element is automatically pressed under the action of centrifugal force and rests with two curved friction surfaces on the gap surfaces.

Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:

Fig. 1
eine Teilansicht einer Gasturbine mit an einer Rotorscheibe angebrachter Turbinenschaufel; und
Fig. 2
einen Schnitt AA nach Fig. 1 mit einem zwischen zwei Schaufeln angeordneten Dichtungs- und Dämpfungselement.
An embodiment of the invention will be explained in more detail with reference to the drawing. Show it:
Fig. 1
a partial view of a gas turbine with attached to a rotor disk turbine blade; and
Fig. 2
a section AA after Fig. 1 with a sealing and damping element arranged between two blades.

Gemäß Fig. 1 ist zwischen zwei in Strömungsrichtung im Abstand angeordneten Statorschaufeln 1 ein Rotor 2 mit am Umfang einer Rotorscheibe 3 angebrachten Turbinenschaufeln 4, bestehend aus einem Schaufelfuß 5, einer Schaufelplattform 6 und einem Schaufelblatt 7, angeordnet. In der in Fig. 2 wiedergegebenen detaillierten Darstellung sind zwei aneinander grenzende Plattformen 6a, 6b von benachbarten Turbinenschaufeln 4 zu erkennen. Die in der Zeichnung rechte Plattform 6a weist eine Ausnehmung 8 auf, in der ein Dichtungs- und Dämpfungselement 9 lose gehalten ist. Der offenen Seite der Ausnehmung 8 liegt - unter Freilassen eines sehr schmalen Spaltes 10 eine ebene, im Wesentlichen senkrechte Plattformkante 11 der anderen Plattform 6b gegenüber und verhindert ein Herausfallen des Dichtungs- und Dämpfungselements 9 aus der Ausnehmung 8. Die Ausnehmung 8 weist eine schräg nach oben verlaufende Dichtfläche 12 auf. Das Dichtungs- und Dämpfungselement 9 ist ein gerades Bauteil mit dem Querschnitt eines gleichseitigen Dreiecks, jedoch mit gerundeten Längskanten 13 und mit zwischen den Längskanten 13 konvex gewölbten - ballig ausgebildeten - Reibflächen 14 (Dichtungs- und Dämpfungsflächen, Seitenflächen).According to Fig. 1 is between two spaced in the direction of flow stator blades 1, a rotor 2 with attached to the circumference of a rotor disk 3 turbine blades 4, consisting of a blade root 5, a blade platform 6 and an airfoil 7, respectively. In the in Fig. 2 1, two adjacent platforms 6a, 6b of adjacent turbine blades 4 can be seen. The right in the drawing platform 6a has a recess 8 in which a sealing and damping element 9 is held loose. The open side of the recess 8 is - leaving a very narrow gap 10 a flat, substantially vertical platform edge 11 of the other platform 6b opposite and prevents falling out of the sealing and damping element 9 from the recess 8. The recess 8 has an obliquely top extending sealing surface 12. The sealing and damping element 9 is a straight component with the cross section of an equilateral triangle, but with rounded longitudinal edges 13 and with between the longitudinal edges 13 convexly curved - convex - friction surfaces 14 (sealing and damping surfaces, side surfaces).

Das im Ruhezustand lose in der Ausnehmung 8 liegende Dichtungs- und Dämpfungselement 9 legt sich aufgrund der Fliehkraft während der Rotation des Rotors 2 mit seinen konvex gewölbten Reibflächen 14 an die senkrechte Plattformkante 11 und an die schräge Dichtfläche 12 an. Eine Rotation des Dichtungs- und Dämpfungselements 9 um seine Längsachse ist daher nicht möglich. Aufgrund der Wölbung und der rotationssymmetrischen Anordnung der gewölbten Reibflächen 14 um eine Längsachse sind jedoch kleine Schwenkbewegungen des Dichtungs- und Dämpfungselements 9 um die Längsachse möglich, so dass die gewölbten Reibflächen 14 an den Berührungsflächen mit der Plattformkante 11 und der schrägen Dichtfläche 12 noch durch Verschleiß bearbeitet und geringfügig abgeflacht werden und somit zum einen der tatsächliche Reibbereich vergrößert und zum anderen an das Plattformdesign anpasst und fertigungsbedingte Unterschiede in der Geometrie ausgeglichen werden. Darüber hinaus werden auch der Reibbereich und die Reibung durch die in geringem Maß möglichen Schwenkbewegungen des Dichtungs- und Dämpfungselements erhöht. Der durch die Reibung an den gewölbten Reibflächen 14 und an den Berührungsflächen mit den beiden gegenüberliegenden Plattformen bewusst bewirkte Verschleiß ist im Voraus bestimmbar und wird bei der Schaufelkonstruktion berücksichtigt. Im Zusammenspiel der zuvor erwähnten Wirkungen wird eine optimale Reibfläche geschaffen und infolge hoher Reibung eine maximale Dämpfung und schließlich auch eine verbesserte Dichtung erreicht, jedoch ohne dass das Dichtungs- und Dämpfungselement unkontrolliert oder durch ständige Rotation vorzeitig verschleißen kann. Der Fertigungs- und der Montage- bzw. Reparaturaufwand werden verringert.The resting and loose in the recess 8 sealing and damping element 9 applies due to the centrifugal force during rotation of the rotor 2 with its convex curved surfaces 14 to the vertical platform edge 11 and the inclined sealing surface 12 at. A rotation of the sealing and damping element 9 about its longitudinal axis is therefore not possible. Due to the curvature and the rotationally symmetrical arrangement of the curved friction surfaces 14 about a longitudinal axis, however, are small Pivoting movements of the sealing and damping element 9 about the longitudinal axis possible, so that the curved friction surfaces 14 are still processed at the contact surfaces with the platform edge 11 and the oblique sealing surface 12 by wear and slightly flattened and thus increased on the one hand, the actual friction and on the other adjusts the platform design and compensates for production-related differences in geometry. In addition, the friction area and the friction are increased by the slightest possible pivoting movements of the sealing and damping element. The wear caused deliberately by the friction on the curved friction surfaces 14 and on the contact surfaces with the two opposing platforms is determinable in advance and is taken into account in the blade construction. The interaction of the aforementioned effects creates an optimum friction surface and, due to high friction, achieves maximum damping and finally improved sealing, but without the sealing and damping element being able to prematurely wear out uncontrollably or by constant rotation. The manufacturing and assembly or repair costs are reduced.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Statorschaufelstator
22
Rotorrotor
33
Rotorscheiberotor disc
44
Turbinenschaufelnturbine blades
55
Schaufelfußblade
66
Plattformplatform
6a6a
rechte Plattformright platform
6b6b
linke Plattformleft platform
77
Schaufelblattairfoil
88th
Ausnehmungrecess
99
Dichtungs- und DämpfungselementSealing and damping element
1010
Spaltgap
1111
gerade, senkrechte Plattformkantestraight, vertical platform edge
1212
schräge Dichtflächesloping sealing surface
1313
gerundete Längskantenrounded longitudinal edges
1414
Reibfläche, gewölbte SeitenflächeFriction surface, curved side surface

Claims (4)

  1. Damping and sealing system for turbine blades with a sealing and damping element (9) in the form of an upright, trilateral prism with equal sides (14) which, by centrifugal effect, is retained between opposite surfaces (11, 12) of adjacent platforms (6a, 6b) of the blades (4) fitted to the rotor of a gas-turbine engine, characterized in that the side faces of the sealing and damping element (9) are designed as convex rubbing surfaces (14) for performing a slight swiveling movement and increasing rubbing efficiency.
  2. Damping and sealing system in accordance with Claim 1, characterized in that the opposite surfaces (11, 12) form a wedge-shaped, acute-angled gap (10), in which the sealing and damping element (9) is loosely fixed.
  3. Damping and sealing system in accordance with Claim 2, characterized in that the gap (10) is formed by a straight platform edge (11) of the one platform (6b) and by an oblique sealing surface (12) in a recess (8) of the other platform (6a).
  4. Damping and sealing system in accordance with Claim 1, characterized in that the longitudinal edges of the sealing and damping element (9) are rounded.
EP07112566A 2006-09-01 2007-07-16 Attenuation and sealing system for turbine blades Expired - Fee Related EP1898050B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006041322A DE102006041322A1 (en) 2006-09-01 2006-09-01 Damping and sealing system for turbine blades

Publications (3)

Publication Number Publication Date
EP1898050A2 EP1898050A2 (en) 2008-03-12
EP1898050A3 EP1898050A3 (en) 2010-07-07
EP1898050B1 true EP1898050B1 (en) 2011-09-07

Family

ID=38969468

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07112566A Expired - Fee Related EP1898050B1 (en) 2006-09-01 2007-07-16 Attenuation and sealing system for turbine blades

Country Status (3)

Country Link
US (1) US20090136350A1 (en)
EP (1) EP1898050B1 (en)
DE (1) DE102006041322A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9045992B2 (en) 2010-06-28 2015-06-02 Herakles Turbomachine blades or vanes having complementary even/odd geometry
FR2961845B1 (en) * 2010-06-28 2013-06-28 Snecma Propulsion Solide TURBOMACHINE DAWN WITH COMPLEMENTARY PAIRE / IMPAIRE GEOMETRY AND METHOD OF MANUFACTURING THE SAME
DE102010052965B4 (en) 2010-11-30 2014-06-12 MTU Aero Engines AG Damping means for damping a blade movement of a turbomachine
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1549152A (en) * 1977-01-11 1979-08-01 Rolls Royce Rotor stage for a gas trubine engine
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
GB9609721D0 (en) * 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
US5749705A (en) * 1996-10-11 1998-05-12 General Electric Company Retention system for bar-type damper of rotor blade
JP3462695B2 (en) * 1997-03-12 2003-11-05 三菱重工業株式会社 Gas turbine blade seal plate
WO2000070192A1 (en) * 1999-05-12 2000-11-23 Siemens Aktiengesellschaft Seal for sealing a gap, in particular in a turbine, and a turbine
DE10014198A1 (en) * 2000-03-22 2001-09-27 Alstom Power Nv Blade arrangement for gas turbines etc. has damper elements located between neighboring rotor blades to engage on opposite distant blade surfaces
DE10022244A1 (en) * 2000-05-08 2001-11-15 Alstom Power Nv Blade arrangement with damping elements
US6851932B2 (en) * 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
JP2005233141A (en) * 2004-02-23 2005-09-02 Mitsubishi Heavy Ind Ltd Moving blade and gas turbine using same
US7534090B2 (en) * 2006-06-13 2009-05-19 General Electric Company Enhanced bucket vibration system

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Publication number Publication date
US20090136350A1 (en) 2009-05-28
DE102006041322A1 (en) 2008-04-24
EP1898050A3 (en) 2010-07-07
EP1898050A2 (en) 2008-03-12

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