EP2924240A1 - Turbine rotor blade - Google Patents
Turbine rotor blade Download PDFInfo
- Publication number
- EP2924240A1 EP2924240A1 EP14161507.0A EP14161507A EP2924240A1 EP 2924240 A1 EP2924240 A1 EP 2924240A1 EP 14161507 A EP14161507 A EP 14161507A EP 2924240 A1 EP2924240 A1 EP 2924240A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- sealing web
- shroud
- rotation
- hole
- 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- Withdrawn
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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
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- Blades of turbines must withstand the centrifugal forces and thermal stresses that occur during operation of the turbine. These stresses can lead to material fatigue and / or creep damage to the parts. Typically, the life of the blades of the first stages of a gas turbine is limited by the material fatigue and that of the downstream blades by creep.
- Blades may also be freestanding or designed as a so-called shroud blades. The latter then have a comparatively small platform at their outwardly pointing tips of the blade. With turbines flowing axially, these platforms then extend in the circumferential direction of a row of rotor blades so far that the shrouds contact adjacent blades.
- Fig. 1 shows such a turbine blade tip with a shroud and with an outwardly facing sealing bar. This can cut into an opposite sealing surface during operation.
- the object of the invention is to provide a shroud blade having a prolonged life.
- Fig. 2 shows a first embodiment of a turbine blade according to the invention, as indicated in claim 2.
- This blade offers the particular advantage that in comparison to the known solutions relatively much mass can be removed from the shroud, without the sealing effect or even the stability of the shroud is impaired.
- Fig. 3 shows a second and a third embodiment of a turbine blade according to the invention, as defined in claim 5.
- Fig. 4 schematically shows a fourth embodiment, wherein the holes are shown too large.
Abstract
Die Erfindung betrifft die Bereitstellung einer Deckband-Laufschaufel, die eine verlängerte Lebensdauer aufweist.The invention relates to the provision of a shroud blade having a prolonged life.
Description
Laufschaufeln von Turbinen müssen den Zentrifugalkräften und den thermischen Belastungen, die während des Betriebs der Turbine auftreten, standhalten. Diese Belastungen können zu einer Materialermüdung und/oder zu Kriechbeschädigungen der Teile führen. Typischerweise ist die Lebensdauer der Schaufeln der ersten Stufen einer Gasturbine durch die Materialermüdung und die der stromab angeordneten Laufschaufeln durch Kriechen begrenzt.Blades of turbines must withstand the centrifugal forces and thermal stresses that occur during operation of the turbine. These stresses can lead to material fatigue and / or creep damage to the parts. Typically, the life of the blades of the first stages of a gas turbine is limited by the material fatigue and that of the downstream blades by creep.
Laufschaufeln können zudem freistehend oder auch als so genannte Deckbandschaufeln ausgestaltet sein. Letztere weisen dann an ihren nach außen weisenden Spitzen des Schaufelblatts eine vergleichsweise kleine Plattform auf. Bei axial durchströmten Turbinen erstecken sich diese Plattformen in Umfangsrichtung einer Reihe von Laufschaufeln dann so weit, dass die Deckbänder einander benachbarten Laufschaufeln sich berühren.Blades may also be freestanding or designed as a so-called shroud blades. The latter then have a comparatively small platform at their outwardly pointing tips of the blade. With turbines flowing axially, these platforms then extend in the circumferential direction of a row of rotor blades so far that the shrouds contact adjacent blades.
Aufgrund der Masse der Deckbänder, die sich auf einem vergleichsweise großen Radius befindet, ist diese besonders der zeit- und temperaturabhängigen plastischen Verformung unter Last (Kriechen) ausgesetzt.Due to the mass of the shrouds, which is located on a relatively large radius, this is particularly exposed to the time and temperature-dependent plastic deformation under load (creep).
In der Vergangenheit wurde das Deckband weitestgehend minimiert, um die Spannungen in dem Deckband möglichst klein zu halten.In the past, the shroud has been minimized as much as possible in order to keep the stresses in the shroud as small as possible.
Aufgabe der Erfindung ist die Bereitstellung einer Deckband-Laufschaufel, die eine verlängerte Lebensdauer aufweist.The object of the invention is to provide a shroud blade having a prolonged life.
Diese Aufgabe wird gelöst mit einer Turbinenlaufschaufel gemäß den Merkmalen des Anspruchs 1. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.This object is achieved with a turbine blade according to the features of claim 1. Advantageous embodiments are specified in the subclaims.
Allen Lösungen liegt die Idee zugrunde, die Masse des Deckbands weiter zu reduzieren. Dazu werden mehrere Ausgestaltungen in den abhängigen Ansprüchen vorgeschlagen.All solutions are based on the idea to further reduce the mass of the shroud. For this purpose, several embodiments are proposed in the dependent claims.
Positive Wirkungen sind:
- Reduzierung der Masse an der Turbinenlaufschaufelspitze
- reduzierte Spannungen
- reduzierte Schaufelblattverformungen während des Betriebs einer mit den erfindungsgemäßen Laufschaufeln ausgestatteten Turbine
- vergrößerte Kriech-Lebensdauer
- geringere Ausschussrate wegen Kriechens.
- Reduction of the mass at the turbine blade tip
- reduced voltages
- reduced airfoil deflections during operation of a turbine equipped with the blades of the present invention
- increased creep life
- lower reject rate due to creep.
Claims (5)
welche entlang einer Längsachse aufeinanderfolgend
dadurch gekennzeichnet,
dass im Deckband und/oder im Dichtsteg zumindest ein Loch zur Gewichtsreduzierung vorgesehen ist.Turbine blade for a thermal turbomachine,
which succeed each other along a longitudinal axis
characterized,
that in the shroud and / or in the sealing web at least one hole is provided for weight reduction.
bei der das zumindest eine Loch als Durchgangsloch ausgestaltet und in einem Übergangsbereich des Deckbands zur Dichtspitze angeordnet ist und sich hauptsächlich in eine Richtung erstreckt, welche bei bestimmungsgemäßer Verwendung der Turbinenlaufschaufeln der Drehrichtung entspricht.Turbine blade according to claim 1,
in which the at least one hole is designed as a through hole and is arranged in a transition region of the cover strip to the sealing tip and extends mainly in a direction which corresponds to the direction of rotation when the turbine blades are used as intended.
bei der das zumindest eine Loch als Sacklock ausgebildet ist.Turbine blade according to claim 1,
in which the at least one hole is formed as a baglock.
bei der mehrere Sacklöcher im Dichtsteg entlang der Drehrichtung verteilt sind und deren Öffnungen an einer radial nach außen weisenden Fläche des Dichtstegs angeordnet sind.Turbine blade according to claim 3,
in which a plurality of blind holes in the sealing web are distributed along the direction of rotation and their openings are arranged on a radially outwardly facing surface of the sealing web.
bei der mehrere Sacklöcher in dem Dichtsteg entlang der Rotationsrichtung verteilt sind und deren Öffnungen an zumindest einer der beiden zu den unterschiedlichen Drücken weisenden Flächen des Dichtstegs angeordnet sind.Turbine blade according to claim 3,
in which a plurality of blind holes are distributed in the sealing web along the direction of rotation and their openings are arranged on at least one of the two faces of the sealing web pointing to the different pressures.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14161507.0A EP2924240A1 (en) | 2014-03-25 | 2014-03-25 | Turbine rotor blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14161507.0A EP2924240A1 (en) | 2014-03-25 | 2014-03-25 | Turbine rotor blade |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2924240A1 true EP2924240A1 (en) | 2015-09-30 |
Family
ID=50343711
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14161507.0A Withdrawn EP2924240A1 (en) | 2014-03-25 | 2014-03-25 | Turbine rotor blade |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2924240A1 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040136831A1 (en) * | 2003-01-09 | 2004-07-15 | Barb Kevin J. | Weight reduced steam turbine blade |
US6962484B2 (en) * | 2002-04-16 | 2005-11-08 | Alstom Technology Ltd | Moving blade for a turbomachine |
WO2011138112A1 (en) * | 2010-05-05 | 2011-11-10 | Alstom Technology Ltd | Light weight shroud fin for a rotor blade |
EP2639406A1 (en) * | 2012-03-15 | 2013-09-18 | General Electric Company | Turbomachine blade with improved stiffness to weight ratio |
-
2014
- 2014-03-25 EP EP14161507.0A patent/EP2924240A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6962484B2 (en) * | 2002-04-16 | 2005-11-08 | Alstom Technology Ltd | Moving blade for a turbomachine |
US20040136831A1 (en) * | 2003-01-09 | 2004-07-15 | Barb Kevin J. | Weight reduced steam turbine blade |
WO2011138112A1 (en) * | 2010-05-05 | 2011-11-10 | Alstom Technology Ltd | Light weight shroud fin for a rotor blade |
EP2639406A1 (en) * | 2012-03-15 | 2013-09-18 | General Electric Company | Turbomachine blade with improved stiffness to weight ratio |
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Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
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Extension state: BA ME |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20160331 |