EP2505784A1 - Rotor for a turbomachine and corresponding upgrading method - Google Patents

Rotor for a turbomachine and corresponding upgrading method Download PDF

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Publication number
EP2505784A1
EP2505784A1 EP12162535A EP12162535A EP2505784A1 EP 2505784 A1 EP2505784 A1 EP 2505784A1 EP 12162535 A EP12162535 A EP 12162535A EP 12162535 A EP12162535 A EP 12162535A EP 2505784 A1 EP2505784 A1 EP 2505784A1
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EP
European Patent Office
Prior art keywords
rotor
intermediate pieces
blades
blade
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.)
Granted
Application number
EP12162535A
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German (de)
French (fr)
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EP2505784B1 (en
Inventor
Marco Micheli
Wolfgang Kappis
Luis Federico Puerta
Gabriel Dunkel
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP2505784A1 publication Critical patent/EP2505784A1/en
Application granted granted Critical
Publication of EP2505784B1 publication Critical patent/EP2505784B1/en
Priority to HRP20160587TT priority Critical patent/HRP20160587T1/en
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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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the present invention relates to a rotor for a turbomachine, in particular a compressor rotor or a turbine rotor of a turbomachine, for example a gas turbine or a steam turbine, preferably a power plant. Moreover, the present invention relates to a method for modernizing a turbomachine.
  • a rotor typically includes at least one blade row having a plurality of blades that are spaced from each other with respect to a rotational axis of the rotor in the circumferential direction.
  • the rotor blades project from the rotor into a gas path.
  • a working gas flows in this gas path.
  • such a rotor typically includes a rotor shaft having a circumferentially extending receiving groove for the respective blade row into which the blades with their blade roots are inserted.
  • a plurality of intermediate pieces may be provided, which are arranged in the receiving groove in each case between two adjacent blades.
  • the rotor blades each have an airfoil which protrudes substantially radially from the rotor blade, via which the respective rotor blades are fastened to the rotor shaft, and thus projects into the gas path.
  • a stabilization of the gas flow during operation of the turbomachine can be achieved by a special contouring on an outer side of the rotor adjacent to the blade leaf, in particular for a compressor.
  • the invention is concerned with the problem of providing an improved embodiment for a rotor of the type mentioned, which is characterized in particular in that the end wall contour is easier to produce. At the same time, a comparatively inexpensive modernization of existing turbomachines is to be made possible.
  • the respective end wall contour can have exactly two turning points in an axial section according to an advantageous embodiment and, in particular, transition tangentially into the outside of the rotor shaft at their axial ends. Additionally or alternatively, the respective end wall contour may be concavely curved. Additionally or alternatively, it is possible that in the respective end wall contour, the curvature along the gas path is arranged eccentrically, and it may be displaced in particular to a compressor to the upstream side.
  • An inventive compressor or a turbine according to the invention is equipped with a rotor of the type described above and can be used in a turbomachine, for example in a stationary turbomachine of a power plant.
  • the end wall contours on the outsides of the blade roots and the intermediate pieces may be the same.
  • the production of identical Endwandkonturen both on the blade roots and on the intermediate pieces avoids complex three-dimensional transitions, which simplifies the production of Endwandkonturen.
  • the end wall contours can be designed axially symmetrical. This means that the end wall contours are rotationally symmetrical with respect to the axis of rotation.
  • the respective Endwandkontur is profiled in a cutting plane containing the axis of rotation, in the circumferential direction constant or constant. This makes it particularly easy to attach the Endwandkonturen on the outer sides of the blade roots and on the outer sides of the spacers.
  • the intermediate pieces and the blade roots may be designed asymmetrically in the axial direction, such that the intermediate pieces can be mounted properly only in a single assembly position.
  • the above proposed design avoids faulty mounting of the intermediate pieces, which would lead to a significant impairment of the flow around the respective blades in the region of the blade root.
  • the receiving groove may have axially inwardly directed groove walls radially inwardly directed support contours, wherein the intermediate pieces have complementary support contours to the support contours of the receiving groove, which in the mounted state are supported radially on the supporting contours of the receiving groove.
  • the spacers in the receiving groove are radially outward through fixed intense positive engagement between the abutting support contours.
  • the rotor shaft may be divided in an axial plane.
  • the blade roots may have, on their inner side facing away from the gas path or facing away from their outer side, protruding shoulders in the circumferential direction, which in the assembled state are supported radially on an inner side of the respective adjacent intermediate piece facing away from the respective outer side.
  • the blade roots are thus indirectly fixed radially via the intermediate pieces on the rotor shaft.
  • the blade feet as well as the intermediate pieces may have supporting contours, which cooperate with the support contours of the receiving groove.
  • an embodiment in which the blades are fastened radially only indirectly via the intermediate pieces on the rotor shaft is preferred. This makes it particularly easy to extract the blades radially from the receiving groove for the maintenance case, if for this purpose at least one intermediate piece is removed from the receiving groove, so that all remaining intermediate pieces and blade roots are displaceable within the receiving groove in the circumferential direction.
  • FIG. 1 includes a turbomachine 1, which may be a gas turbine plant or a steam turbine plant of a power plant for power generation, a compressor 2 or a turbine 3 with a stator 4, in which a rotor 5 is rotatably mounted about a rotation axis 6.
  • the rotor 5 has at least one blade row 7, the plurality of blades 8, which are arranged adjacent to each other with respect to the rotation axis 6 in the circumferential direction.
  • the axis of rotation 6 representing dash-dotted line is not to scale, but only to suggest the orientation of the axis of rotation. 6
  • the rotor 5 further has a rotor shaft 9, in which for the respective blade row 7 in the circumferential direction annularly extending receiving groove 10 is incorporated.
  • the blades 8 each have an airfoil 11, which in the installed state in an in FIG. 1 projected by a dash-dotted line indicated gas path 12, and a blade root 13 which is inserted into the receiving groove 10.
  • the blade root 13 is structurally integrated into the rotor shaft 9.
  • the rotor 5 according to FIG. 2 a plurality of intermediate pieces 14, which are also inserted into the receiving groove 10 and in each case between two adjacent blades 8 and between two adjacent blade roots 13 are arranged. Within the respective blade row 7 or within the associated receiving groove 10 thus intermediate pieces 14 and blades 8 or blade feet 13 alternate.
  • the respective blade root 13 has, on a side 15 facing the gas path 12, which is located in the circumferential direction next to the blade 8, a curved end wall contour 16, which in FIG FIG. 1 is indicated and in FIG. 5 is reproduced.
  • the intermediate pieces 14 likewise have an outer side 17 facing the gas path 12, on which the intermediate pieces 14 likewise each have such a curved end wall contour 16.
  • the curvature of the end wall contour 16 extends along the gas path 12, that is, substantially along the axial direction, which is defined by the rotation axis 6.
  • at least the intermediate pieces 14 may also be curved in the circumferential direction, namely corresponding to a radius 34 of the rotor 5.
  • the end wall contours 16 of the outer sides 15 of the blade roots 13 on the one hand and the outer sides 17 of the intermediate pieces 14 on the other hand have the same geometric shape.
  • flush transitions on the adjoining outer sides 15, 17 of the blade roots 13 and the intermediate pieces 14 can thereby be realized.
  • the outer sides 15 of the blade roots 13 and the outer sides 17 of the intermediate pieces 14 as in FIG. 2 recognizable radially adjacent to each other in the circumferential direction.
  • the end wall contours 16 of the outer sides 15 of the blade roots 13 and the end wall contours 16 of the outer sides 17 of the intermediate pieces 14 are configured axially symmetrical.
  • the respective profile results as in the FIGS. 1 and 5 by a longitudinal section containing the axis of rotation 6.
  • the end wall contours 16 are thus designed rotationally symmetrical. Only at the respective blade 8, a three-dimensional transition from the blade root 13 to the blade 11 may be appropriate.
  • the blade roots 13 and the intermediate pieces 14 are configured symmetrically, so that it is fundamentally possible to arrange the blade roots 13 and the intermediate pieces 14 rotated by 180 ° in the receiving groove 10.
  • the rotation by 180 ° refers to a rotation about the radial direction in the FIGS. 3 and 4 is perpendicular to the plane of the drawing.
  • the blade roots have 13 in Fig. 3 a width 18 which remains constant in the flow direction 21.
  • the intermediate pieces 14 here have a width 22 which remains constant in the flow direction 21.
  • FIG. 1 has the receiving groove 10 at its mutually axially opposite groove walls 23 radially inwardly directed support contours 24.
  • the intermediate pieces 14 have according to FIG. 2 at in the axial direction 20 facing away from each other ends 25 radially outwardly directed support contours 26 which are complementary to the support contours 24 of the receiving groove 10 are formed.
  • the support contours 26 of the intermediate pieces 14 can be supported radially on the support contours 24 of the receiving groove 10.
  • FIG. 2 have the blade roots 13 on its inner side 27, which faces away from the gas path 12 and from the outer side 15 of the blade root 13, in the circumferential direction 19 projecting paragraphs 28 on.
  • each blade root 13 expediently two such paragraphs 28 are provided, which protrude at two opposite end faces in the circumferential direction 19 of the respective end face.
  • these paragraphs 28 each engage under an inner side 29 of the adjacent intermediate piece 14, which faces away from the outer side 17 of the intermediate piece 14 or from the gas path 12.
  • the paragraphs 28 are supported in the assembled state radially on the inner sides 29 of the adjacent intermediate pieces 14 from.
  • Particularly advantageous is an embodiment in which the blades 8 are anchored exclusively indirectly via the intermediate pieces 14 on the rotor shaft 9 radially.
  • the end wall contour 16 may be configured to have exactly two inflection points 30, thereby making it possible to form a concave camber 31 oriented toward the rotation axis 6 and to realize tangential transitions at the end portions 32 of the end wall contour 16.
  • the curvature 31 is recognizable offset with respect to a geometric center 33 of the end wall contour 16 with respect to the axial direction 20 arranged, that is arranged eccentrically. In particular, the curvature 31 is thereby positioned shifted with respect to the center 33 to the inflow side.

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

Abstract

The rotor has moving blades (8) that are located adjacent to one another in a circumferential direction (19) with respect to rotation axis. Several intermediate pieces (14) are provided in reception slot between two adjacent ones of moving blades. Each intermediate piece is provided with an outer face having curved end wall contour (17) with concave curvature in an axial sectional plane of rotor. The outer faces (15,17) of blade roots (13) and intermediate pieces are adjacent to one another and are aligned radially in the circumferential direction. An independent claim is included for method for modernizing rotor of turbomachine.

Description

Technisches GebietTechnical area

Die vorliegende Erfindung betrifft einen Rotor für eine Turbomaschine, insbesondere einen Verdichterrotor oder einen Turbinenrotor einer Turbomaschine, zum Beispiel eine Gasturbine oder eine Dampfturbine, vorzugsweise einer Kraftwerksanlage. Außerdem betrifft die vorliegende Erfindung ein Verfahren zum Modernisieren einer Turbomaschine.The present invention relates to a rotor for a turbomachine, in particular a compressor rotor or a turbine rotor of a turbomachine, for example a gas turbine or a steam turbine, preferably a power plant. Moreover, the present invention relates to a method for modernizing a turbomachine.

Stand der TechnikState of the art

Üblicherweise umfasst ein Rotor zumindest eine Laufschaufelreihe, die mehrere Laufschaufeln aufweist, die bezüglich einer Rotationsachse des Rotors in der Umfangsrichtung zueinander beabstandet angeordnet sind. Dabei stehen die Laufschaufeln ausgehend vom Rotor in einen Gaspfad vor. In diesem Gaspfad strömt im Betrieb der Turbomaschine ein Arbeitsgas. Ferner umfasst ein solcher Rotor typischerweise eine Rotorwelle, die für die jeweilige Laufschaufelreihe eine sich in Umfangsrichtung erstreckende Aufnahmenut aufweist, in welche die Laufschaufeln mit ihren Schaufelfüßen eingesetzt sind. Ferner können mehrere Zwischenstücke vorgesehen sein, die in der Aufnahmenut jeweils zwischen zwei benachbarten Laufschaufeln angeordnet sind.Typically, a rotor includes at least one blade row having a plurality of blades that are spaced from each other with respect to a rotational axis of the rotor in the circumferential direction. The rotor blades project from the rotor into a gas path. During operation of the turbomachine, a working gas flows in this gas path. Further, such a rotor typically includes a rotor shaft having a circumferentially extending receiving groove for the respective blade row into which the blades with their blade roots are inserted. Further, a plurality of intermediate pieces may be provided, which are arranged in the receiving groove in each case between two adjacent blades.

Die Laufschaufeln weisen außerdem jeweils ein Schaufelblatt auf, das vom zugehörigen Schaufelfuß, über den die jeweilige Laufschaufeln an der Rotorwelle befestigt ist, vom Rotor im Wesentlichen radial absteht und so in den Gaspfad hineinragt. Im Bereich eines dem Schaufelfuß zugeordneten inneren Endabschnitts kann insbesondere bei einem Verdichter eine Stabilisierung der Gasströmung im Betrieb der Turbomaschine durch eine spezielle Konturgebung an einer an das Schaufelblatt angrenzenden, dem Gaspfad ausgesetzten Außenseite des Rotors erzielt werden. Hierbei handelt es sich um eine den Gaspfad begrenzende Endwandkontur des Rotors, die insbesondere entlang des Gaspfads gewölbt sein kann. Dabei ist es grundsätzlich möglich, die Laufschaufeln an ihren Schaufelfüßen an einer dem Gaspfad zugewandten Außenseite in der Umfangsrichtung neben dem Schaufelblatt mit einer solchen gewölbten Endwandkontur auszustatten.In addition, the rotor blades each have an airfoil which protrudes substantially radially from the rotor blade, via which the respective rotor blades are fastened to the rotor shaft, and thus projects into the gas path. In the region of an inner end section assigned to the blade root, a stabilization of the gas flow during operation of the turbomachine can be achieved by a special contouring on an outer side of the rotor adjacent to the blade leaf, in particular for a compressor. This is an end wall contour of the rotor delimiting the gas path, which can be curved in particular along the gas path. It is basically possible to equip the blades at their blade roots on a side facing the gas path in the circumferential direction next to the blade with such a curved Endwandkontur.

Beispielsweise zeigen die Zeichnungen der US 5 232 348 A und der US 2 916 257 A gewölbte Endwandkonturen, wobei die gaspfadseitigen Endwände der Zwischenstücke bündig und stufenfrei in die Endwände der Schaufelfüße übergehen. Anstelle einer dem Gaspfad zugewandten konvexen Ausgestaltung der Wölbung kann auch eine geradlinige Ausgestaltung vorgesehen sein.For example, the drawings of the US 5 232 348 A and the US 2,916,257 A arched Endwandkonturen, wherein the gas path side end walls of the intermediate pieces flush and steplessly pass into the end walls of the blade roots. Instead of a gas path facing convex configuration of the curvature may also be provided a rectilinear configuration.

Darstellung der ErfindungPresentation of the invention

Hier setzt die vorliegende Erfindung an. Die Erfindung beschäftigt sich mit dem Problem, für einen Rotor der eingangs genannten Art eine verbesserte Ausführungsform anzugeben, die sich insbesondere dadurch auszeichnet, dass die Endwandkontur leichter herstellbar ist. Dabei soll auch eine vergleichsweise preiswerte Modernisierung bestehender Turbomaschinen ermöglicht werden.This is where the present invention begins. The invention is concerned with the problem of providing an improved embodiment for a rotor of the type mentioned, which is characterized in particular in that the end wall contour is easier to produce. At the same time, a comparatively inexpensive modernization of existing turbomachines is to be made possible.

Dieses Problem wird erfindungsgemäß durch den Gegenstand des unabhängigen Anspruchs gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.This problem is solved according to the invention by the subject matter of the independent claim. Advantageous embodiments are the subject of the dependent claims.

Die jeweilige Endwandkontur kann in einem Axialschnitt entsprechend einer vorteilhaften Ausführungsform genau zwei Wendepunkte aufweisen und insbesondere an ihren axialen Enden tangential in die Außenseite der Rotorwelle übergehen. Zusätzlich oder alternativ kann die jeweilige Endwandkontur konkav gewölbt sein. Zusätzlich oder alternativ ist es möglich, dass bei der jeweiligen Endwandkontur die Wölbung entlang des Gaspfads außermittig angeordnet ist, wobei sie insbesondere bei einem Verdichter zur Anströmseite hin verschoben sein kann.The respective end wall contour can have exactly two turning points in an axial section according to an advantageous embodiment and, in particular, transition tangentially into the outside of the rotor shaft at their axial ends. Additionally or alternatively, the respective end wall contour may be concavely curved. Additionally or alternatively, it is possible that in the respective end wall contour, the curvature along the gas path is arranged eccentrically, and it may be displaced in particular to a compressor to the upstream side.

Ein erfindungsgemäßer Verdichter bzw. eine erfindungsgemäße Turbine ist mit einem Rotor der vorbeschriebenen Art ausgestattet und kann in einer Turbomaschine zur Anwendung kommen, beispielsweise in einer stationären Turbomaschine einer Kraftwerksanlage.An inventive compressor or a turbine according to the invention is equipped with a rotor of the type described above and can be used in a turbomachine, for example in a stationary turbomachine of a power plant.

Bei der Erfindung ist insbesondere vorgesehen, nicht nur die dem Gaspfad zugewandten Außenseiten der Schaufelfüße, sondern auch die dem Gaspfad zugewandte Außenseite der Zwischenstücke mit einer derartigen Endwandkontur auszustatten. Hierdurch gestaltet sich der Übergang von der Endwandkontur der Außenseite des jeweiligen Schaufelfußes zur Endwandkontur der Außenseite des jeweils benachbarten Zwischenstücks einfacher. Es ist daher insbesondere keine komplexe dreidimensionale Formgebung für die Endwandkontur am Schaufelfuß mehr erforderlich. Somit kann der Aufwand zum Herstellen der Endwandkonturen reduziert werden. Da erfindungsgemäß nun auch die Zwischenstücke mit einer solchen Endwandkontur versehen sind, ist es z.B. im Rahmen einer Modernisierung möglich, die Laufschaufeln und die Zwischenstücke auszutauschen, um eine bestehende Turbomaschine nachträglich mit der gewölbten Endwandkontur auszustatten.In the case of the invention, provision is made in particular for equipping not only the outer sides of the blade roots facing the gas path, but also the outer side of the intermediate pieces facing the gas path with such an end wall contour. As a result, the transition from the end wall contour of the outer side of the respective blade root to the end wall contour of the outer side of the respectively adjacent intermediate piece is simpler. Therefore, in particular, no complex three-dimensional shaping is required for the end wall contour on the blade root. Thus, the cost of producing the Endwandkonturen can be reduced. Since according to the invention now also the intermediate pieces are provided with such a Endwandkontur, it is possible, for example in the context of modernization, replace the blades and the spacers to equip an existing turbomachine with the curved Endwandkontur subsequently.

Entsprechend einer vorteilhaften Ausführungsform können die Endwandkonturen an den Außenseiten der Schaufelfüße und der Zwischenstücke gleich sein. Die Herstellung gleicher Endwandkonturen sowohl an den Schaufelfüßen als auch an den Zwischenstücken vermeidet komplexe dreidimensionale Übergänge, was die Herstellung der Endwandkonturen vereinfacht.According to an advantageous embodiment, the end wall contours on the outsides of the blade roots and the intermediate pieces may be the same. The production of identical Endwandkonturen both on the blade roots and on the intermediate pieces avoids complex three-dimensional transitions, which simplifies the production of Endwandkonturen.

Entsprechend einer besonders vorteilhaften Ausführungsform können die Endwandkonturen axial-symmetrisch ausgestaltet sein. Das bedeutet, dass die Endwandkonturen bezüglich der Rotationsachse drehsymmetrisch ausgestaltet sind. Mit anderen Worten, die jeweilige Endwandkontur ist in einer Schnittebene, welche die Rotationsachse enthält, in der Umfangsrichtung gleichbleibend bzw. konstant profiliert. Hierdurch ist es besonders einfach, die Endwandkonturen an den Außenseiten der Schaufelfüße und an den Außenseiten der Zwischenstücke anzubringen.According to a particularly advantageous embodiment, the end wall contours can be designed axially symmetrical. This means that the end wall contours are rotationally symmetrical with respect to the axis of rotation. In other words, the respective Endwandkontur is profiled in a cutting plane containing the axis of rotation, in the circumferential direction constant or constant. This makes it particularly easy to attach the Endwandkonturen on the outer sides of the blade roots and on the outer sides of the spacers.

Gemäß einer anderen vorteilhaften Ausführungsform können die Zwischenstücke und die Schaufelfüße in der Axialrichtung asymmetrisch ausgestaltet sein, derart, dass die Zwischenstücke nur in einer einzigen Montageposition ordnungsgemäß montierbar sind. Für den Fall, dass die gewölbten Endwandkonturen in der Axialrichtung asymmetrisch konfiguriert sind, vermeidet die vorstehend vorgeschlagene Bauform eine fehlerhafte Montage der Zwischenstücke, die zu einer erheblichen Beeinträchtigung der Umströmung der jeweiligen Laufschaufeln im Bereich des Schaufelfußes führen würde.According to another advantageous embodiment, the intermediate pieces and the blade roots may be designed asymmetrically in the axial direction, such that the intermediate pieces can be mounted properly only in a single assembly position. In the event that the curved end wall contours are asymmetrically configured in the axial direction, the above proposed design avoids faulty mounting of the intermediate pieces, which would lead to a significant impairment of the flow around the respective blades in the region of the blade root.

Gemäß einer speziellen Ausführungsform kann die Aufnahmenut an sich axial gegenüberliegenden Nutwänden radial nach innen gerichtete Stützkonturen aufweisen, wobei die Zwischenstücke zu den Stützkonturen der Aufnahmenut komplementäre radial nach außen gerichtete Stützkonturen aufweisen, die sich im montierten Zustand radial an den Stützkonturen der Aufnahmenut abstützen. Hierdurch sind die Zwischenstücke in der Aufnahmenut radial nach außen durch intensiven Formschluss zwischen den aneinander anliegenden Stützkonturen fixiert. Um die Zwischenstücke in die jeweilige Aufnahmenut einführen zu können, kann die Rotorwelle in einer Axialebene geteilt sein.According to a special embodiment, the receiving groove may have axially inwardly directed groove walls radially inwardly directed support contours, wherein the intermediate pieces have complementary support contours to the support contours of the receiving groove, which in the mounted state are supported radially on the supporting contours of the receiving groove. As a result, the spacers in the receiving groove are radially outward through fixed intense positive engagement between the abutting support contours. In order to introduce the spacers into the respective receiving groove, the rotor shaft may be divided in an axial plane.

Entsprechend einer bevorzugten Weiterbildung können die Schaufelfüße an ihrer vom Gaspfad abgewandten bzw. von ihrer Außenseite abgewandten Innenseite in der Umfangsrichtung vorstehende Absätze aufweisen, die sich im montierten Zustand radial an einer von der jeweiligen Außenseite abgewandten Innenseite des jeweiligen benachbarten Zwischenstücks abstützen. Bei dieser Ausführungsform sind somit die Schaufelfüße mittelbar über die Zwischenstücke an der Rotorwelle radial festgelegt. Zusätzlich können die Schaufelfüße ebenso wie die Zwischenstücke Stützkonturen aufweisen, die mit den Stützkonturen der Aufnahmenut zusammenwirken.According to a preferred development, the blade roots may have, on their inner side facing away from the gas path or facing away from their outer side, protruding shoulders in the circumferential direction, which in the assembled state are supported radially on an inner side of the respective adjacent intermediate piece facing away from the respective outer side. In this embodiment, the blade roots are thus indirectly fixed radially via the intermediate pieces on the rotor shaft. In addition, the blade feet as well as the intermediate pieces may have supporting contours, which cooperate with the support contours of the receiving groove.

Bevorzugt ist jedoch eine Ausführungsform, bei der die Laufschaufeln ausschließlich mittelbar über die Zwischenstücke an der Rotorwelle radial befestigt sind. Hierdurch ist es besonders einfach möglich, für den Wartungsfall die Laufschaufeln radial aus der Aufnahmenut herauszuziehen, wenn hierzu wenigstens ein Zwischenstück aus der Aufnahmenut herausgenommen ist, so dass alle übrigen Zwischenstücke und Schaufelfüße innerhalb der Aufnahmenut in der Umfangsrichtung verschiebbar sind.However, an embodiment in which the blades are fastened radially only indirectly via the intermediate pieces on the rotor shaft is preferred. This makes it particularly easy to extract the blades radially from the receiving groove for the maintenance case, if for this purpose at least one intermediate piece is removed from the receiving groove, so that all remaining intermediate pieces and blade roots are displaceable within the receiving groove in the circumferential direction.

Weitere wichtige Merkmale und Vorteile der Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the invention will become apparent from the dependent claims, from the drawings and from the associated figure description with reference to the drawings.

Es versteht sich, dass die vorstehend genannten und die nachstehend noch zu erläuternden Merkmale nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen oder in Alleinstellung verwendbar sind, ohne den Rahmen der vorliegenden Erfindung zu verlassen.It is understood that the features mentioned above and those yet to be explained below can be used not only in the particular combination given, but also in other combinations or in isolation, without departing from the scope of the present invention.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Bauteile beziehen.Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components.

Es zeigen, jeweils schematisch,

Fig. 1
einen Längsschnitt durch eine Turbomaschine im Bereich eines Rotors,
Fig. 2
eine isometrische Ansicht auf einen Umfangsabschnitt einer Laufschaufelreihe des Rotors,
Fig. 3
eine radiale Draufsicht auf einen Umfangsabschnitt der Laufschaufelreihe,
Fig. 4
eine Draufsicht wie in Fig. 3, jedoch bei einer anderen Ausführungsform,
Fig. 5
eine Endwandkontur im Längsschnitt.
Show, in each case schematically,
Fig. 1
a longitudinal section through a turbomachine in the region of a rotor,
Fig. 2
an isometric view of a peripheral portion of a blade row of the rotor,
Fig. 3
a radial plan view of a peripheral portion of the blade row,
Fig. 4
a top view as in Fig. 3 but in another embodiment,
Fig. 5
an end wall contour in longitudinal section.

Wege zur Ausführung der ErfindungWays to carry out the invention

Entsprechend Figur 1 umfasst eine Turbomaschine 1, bei der es sich um eine Gasturbinenanlage oder um eine Dampfturbinenanlage eines Kraftwerks zur Stromgewinnung handeln kann, einen Verdichter 2 oder eine Turbine 3 mit einem Stator 4, in dem ein Rotor 5 um eine Rotationsachse 6 drehbar gelagert ist. Der Rotor 5 weist zumindest eine Laufschaufelreihe 7 auf, die mehrere Laufschaufeln 8 besitzt, die bezüglich der Rotationsachse 6 in der Umfangsrichtung zueinander benachbart angeordnet sind. Die in Figur 1 dargestellte, die Rotationsachse 6 repräsentierende strichpunktierte Linie ist nicht maßstäblich zu verstehen, sondern nur zur Andeutung der Orientierung der Rotationsachse 6.Corresponding FIG. 1 includes a turbomachine 1, which may be a gas turbine plant or a steam turbine plant of a power plant for power generation, a compressor 2 or a turbine 3 with a stator 4, in which a rotor 5 is rotatably mounted about a rotation axis 6. The rotor 5 has at least one blade row 7, the plurality of blades 8, which are arranged adjacent to each other with respect to the rotation axis 6 in the circumferential direction. In the FIG. 1 illustrated, the axis of rotation 6 representing dash-dotted line is not to scale, but only to suggest the orientation of the axis of rotation. 6

Der Rotor 5 weist ferner eine Rotorwelle 9 auf, in welche für die jeweilige Laufschaufelreihe 7 eine sich in der Umfangsrichtung ringförmig erstreckende Aufnahmenut 10 eingearbeitet ist. Die Laufschaufeln 8 besitzen jeweils ein Schaufelblatt 11, das im eingebauten Zustand in einen in Figur 1 durch eine strichpunktierte Linie angedeuteten Gaspfad 12 hineinragt, und einen Schaufelfuß 13, der in die Aufnahmenut 10 eingesetzt ist. Insoweit ist der Schaufelfuß 13 baulich in die Rotorwelle 9 integriert. Ferner umfasst der Rotor 5 gemäß Figur 2 mehrere Zwischenstücke 14, die ebenfalls in die Aufnahmenut 10 eingesetzt sind und dabei jeweils zwischen zwei benachbarten Laufschaufeln 8 bzw. zwischen zwei benachbarten Schaufelfüßen 13 angeordnet sind. Innerhalb der jeweiligen Laufschaufelreihe 7 bzw. innerhalb der zugehörigen Aufnahmenut 10 wechseln sich somit Zwischenstücke 14 und Laufschaufeln 8 bzw. Schaufelfüße 13 ab.The rotor 5 further has a rotor shaft 9, in which for the respective blade row 7 in the circumferential direction annularly extending receiving groove 10 is incorporated. The blades 8 each have an airfoil 11, which in the installed state in an in FIG. 1 projected by a dash-dotted line indicated gas path 12, and a blade root 13 which is inserted into the receiving groove 10. In that regard, the blade root 13 is structurally integrated into the rotor shaft 9. Furthermore, the rotor 5 according to FIG FIG. 2 a plurality of intermediate pieces 14, which are also inserted into the receiving groove 10 and in each case between two adjacent blades 8 and between two adjacent blade roots 13 are arranged. Within the respective blade row 7 or within the associated receiving groove 10 thus intermediate pieces 14 and blades 8 or blade feet 13 alternate.

Der jeweilige Schaufelfuß 13 weist an einer dem Gaspfad 12 zugewandten Außenseite 15, die sich in der Umfangsrichtung neben dem Schaufelblatt 8 befindet, eine gewölbte Endwandkontur 16 auf, die in Figur 1 angedeutet ist und in Figur 5 wiedergegeben ist. Die Zwischenstücke 14 besitzen ebenfalls eine dem Gaspfad 12 zugewandte Außenseite 17, an der die Zwischenstücke 14 ebenfalls jeweils eine derartige gewölbte Endwandkontur 16 aufweisen. Die Wölbung der Endwandkontur 16 erstreckt sich dabei entlang des Gaspfads 12, also im Wesentlichen entlang der Axialrichtung, die durch die Rotationsachse 6 definiert ist. Darüber hinaus können zumindest die Zwischenstücke 14 auch in der Umfangsrichtung gewölbt sein, nämlich entsprechend einem Radius 34 des Rotors 5.The respective blade root 13 has, on a side 15 facing the gas path 12, which is located in the circumferential direction next to the blade 8, a curved end wall contour 16, which in FIG FIG. 1 is indicated and in FIG. 5 is reproduced. The intermediate pieces 14 likewise have an outer side 17 facing the gas path 12, on which the intermediate pieces 14 likewise each have such a curved end wall contour 16. The curvature of the end wall contour 16 extends along the gas path 12, that is, substantially along the axial direction, which is defined by the rotation axis 6. In addition, at least the intermediate pieces 14 may also be curved in the circumferential direction, namely corresponding to a radius 34 of the rotor 5.

Besonders vorteilhaft ist es dabei, wenn die Endwandkonturen 16 der Außenseiten 15 der Schaufelfüße 13 einerseits und der Außenseiten 17 der Zwischenstücke 14 andererseits geometrisch gleich geformt sind. Insbesondere lassen sich dadurch bündige Übergänge an den aneinandergrenzenden Außenseiten 15, 17 der Schaufelfüße 13 und der Zwischenstücke 14 realisieren. Beispielsweise können die Außenseiten 15 der Schaufelfüße 13 und die Außenseiten 17 der Zwischenstücke 14 wie in Figur 2 erkennbar radial bündig in der Umfangsrichtung aneinandergrenzen.It is particularly advantageous if the end wall contours 16 of the outer sides 15 of the blade roots 13 on the one hand and the outer sides 17 of the intermediate pieces 14 on the other hand have the same geometric shape. In particular, flush transitions on the adjoining outer sides 15, 17 of the blade roots 13 and the intermediate pieces 14 can thereby be realized. For example, the outer sides 15 of the blade roots 13 and the outer sides 17 of the intermediate pieces 14 as in FIG. 2 recognizable radially adjacent to each other in the circumferential direction.

Von besonderem Interesse ist eine Ausführungsform, bei welcher die Endwandkonturen 16 der Außenseiten 15 der Schaufelfüße 13 und die Endwandkonturen 16 der Außenseiten 17 der Zwischenstücke 14 axial-symmetrisch ausgestaltet sind. Das bedeutet, dass die Endwandkonturen 16 in der Umfangsrichtung ein konstant bleibendes Profil aufweisen. Das jeweilige Profil ergibt sich dabei wie in den Figuren 1 und 5 durch einen Längsschnitt, der die Rotationsachse 6 enthält. Bezüglich dieser Rotationsachse 6 sind die Endwandkonturen 16 somit drehsymmetrisch ausgestaltet. Lediglich an der jeweiligen Laufschaufel 8 kann ein dreidimensionaler Übergang vom Schaufelfuß 13 zum Schaufelblatt 11 zweckmäßig sein.Of particular interest is an embodiment in which the end wall contours 16 of the outer sides 15 of the blade roots 13 and the end wall contours 16 of the outer sides 17 of the intermediate pieces 14 are configured axially symmetrical. This means that the end wall contours 16 have a constant profile in the circumferential direction. The respective profile results as in the FIGS. 1 and 5 by a longitudinal section containing the axis of rotation 6. With respect to this axis of rotation 6, the end wall contours 16 are thus designed rotationally symmetrical. Only at the respective blade 8, a three-dimensional transition from the blade root 13 to the blade 11 may be appropriate.

Bei der in Figur 3 gezeigten Ausführungsform sind die Schaufelfüße 13 und die Zwischenstücke 14 symmetrisch ausgestaltet, so dass es grundsätzlich möglich ist, die Schaufelfüße 13 und die Zwischenstücke 14 um 180° verdreht in der Aufnahmenut 10 anzuordnen. Die Verdrehung um 180° bezieht sich dabei auf eine Drehung um die Radialrichtung, die in den Figuren 3 und 4 senkrecht zur Zeichnungsebene steht.At the in FIG. 3 In the embodiment shown, the blade roots 13 and the intermediate pieces 14 are configured symmetrically, so that it is fundamentally possible to arrange the blade roots 13 and the intermediate pieces 14 rotated by 180 ° in the receiving groove 10. The rotation by 180 ° refers to a rotation about the radial direction in the FIGS. 3 and 4 is perpendicular to the plane of the drawing.

Sofern die Endwandkonturen 16 wie in den Figuren 1 und 5 angedeutet bezüglich der Axialrichtung asymmetrisch ausgestaltet sind, führt eine verkehrte Montage der Zwischenstücke 14 zu einer signifikanten Verschlechterung der Umströmung der Schaufelblätter 11 im Bereich der Schaufelfüße 13. Eine falsche Montage der Laufschaufeln 8 ist dabei nahezu ausgeschlossen, da dies aufgrund der Asymmetrie der Schaufelblätter 11 sofort offensichtlich ist. Zur Vermeidung einer Falschmontage der Zwischenstücke 14 kann gemäß Figur 4 vorgesehen sein, die Zwischenstücke 14 und die Schaufelfüße 13 asymmetrisch zu konfigurieren, derart, dass die Zwischenstücke 14 nur in einer einzigen, vorgegebenen Montageposition ordnungsgemäß montierbar sind. Erreicht wird dies im Beispiel der Figur 4 rein exemplarisch durch eine Keilform der Zwischenstücke 14 bezüglich ihrer axialen Erstreckung sowie durch eine dazu komplementäre Keilform der Schaufelfüße 13 ebenfalls hinsichtlich der axialen Erstreckung. Beispielsweise kann eine Breite 18 der Schaufelfüße 13, die in der in den Figuren 3 und 4 durch einen Doppelpfeil angedeuteten Umfangsrichtung 19 gemessen wird, in der in den Figuren 3 und 4 sowie in Figur 1 durch einen Doppelpfeil angedeuteten Axialrichtung 20 in der in den Figuren 3 und 4 durch einen Richtungspfeil angedeuteten Strömungsrichtung 21 des Arbeitsgases zunehmen, während eine in der Umfangsrichtung 19 gemessene Breite 22 der Zwischenstücke 14 in der Axialrichtung 20 in der Strömungsrichtung 21 entsprechend abnimmt. Im Unterschied dazu besitzen die Schaufelfüße 13 in Fig. 3 eine in der Strömungsrichtung 21 konstant bleibende Breite 18. Ebenso besitzen die Zwischenstücke 14 hier eine in der Strömungsrichtung 21 konstant bleibende Breite 22.If the Endwandkonturen 16 as in the FIGS. 1 and 5 are indicated asymmetrically with respect to the axial direction, a wrong assembly of the intermediate pieces 14 leads to a significant deterioration of the flow around the blades 11 in the area of the blade roots 13. An incorrect installation of Blades 8 is almost impossible, since this is immediately apparent due to the asymmetry of the blades 11. To avoid a wrong assembly of the intermediate pieces 14 can according to FIG. 4 be provided to configure the intermediate pieces 14 and the blade roots 13 asymmetric, such that the intermediate pieces 14 are properly mounted only in a single, predetermined mounting position. This is achieved in the example of FIG. 4 purely exemplarily by a wedge shape of the intermediate pieces 14 with respect to their axial extent and by a complementary wedge shape of the blade roots 13 also with respect to the axial extent. For example, a width 18 of the blade roots 13, which in the in the FIGS. 3 and 4 is indicated by a double arrow indicated circumferential direction 19, in the in the FIGS. 3 and 4 as in FIG. 1 indicated by a double arrow axial direction 20 in the in the FIGS. 3 and 4 indicated by a direction arrow flow direction 21 of the working gas, while a measured in the circumferential direction 19 width 22 of the intermediate pieces 14 in the axial direction 20 in the flow direction 21 decreases accordingly. In contrast, the blade roots have 13 in Fig. 3 a width 18 which remains constant in the flow direction 21. Likewise, the intermediate pieces 14 here have a width 22 which remains constant in the flow direction 21.

Durch die asymmetrische Formgebung der Zwischenstücke 14 und der Schaufelfüße 13 würde bei einer Fehlmontage zwangsläufig eine sichtbare Lücke zwischen Schaufelfuß 13 und Zwischenstück 14 verbleiben, so dass die Falschmontage sofort bemerkt werden kann.Due to the asymmetrical shaping of the intermediate pieces 14 and the blade roots 13, a visible gap between the blade root 13 and the intermediate piece 14 would inevitably remain in case of incorrect assembly, so that the incorrect assembly can be noticed immediately.

Gemäß Figur 1 weist die Aufnahmenut 10 an ihren aneinander axial gegenüberliegenden Nutwänden 23 radial nach innen gerichtete Stützkonturen 24 auf. Die Zwischenstücke 14 besitzen gemäß Figur 2 an in der Axialrichtung 20 voneinander abgewandten Enden 25 radial nach außen gerichtete Stützkonturen 26, die komplementär zu den Stützkonturen 24 der Aufnahmenut 10 geformt sind.According to FIG. 1 has the receiving groove 10 at its mutually axially opposite groove walls 23 radially inwardly directed support contours 24. The intermediate pieces 14 have according to FIG. 2 at in the axial direction 20 facing away from each other ends 25 radially outwardly directed support contours 26 which are complementary to the support contours 24 of the receiving groove 10 are formed.

Im montierten Zustand können sich die Stützkonturen 26 der Zwischenstücke 14 radial an den Stützkonturen 24 der Aufnahmenut 10 abstützen. Gemäß Figur 2 weisen die Schaufelfüße 13 an ihrer Innenseite 27, die vom Gaspfad 12 bzw. von der Außenseite 15 des Schaufelfußes 13 abgewandt ist, in der Umfangsrichtung 19 vorstehende Absätze 28 auf. Dabei sind je Schaufelfuß 13 zweckmäßig zwei derartige Absätze 28 vorgesehen, die an zwei voneinander abgewandten Stirnseiten in der Umfangsrichtung 19 von der jeweiligen Stirnseite vorstehen. Im montierten Zustand untergreifen diese Absätze 28 jeweils eine Innenseite 29 des benachbarten Zwischenstücks 14, die von der Außenseite 17 des Zwischenstücks 14 bzw. vom Gaspfad 12 abgewandt ist. Ferner stützen sich die genannten Absätze 28 im montierten Zustand radial an den Innenseiten 29 der benachbarten Zwischenstücke 14 ab. Besonders vorteilhaft ist dabei eine Ausführungsform, bei der die Laufschaufeln 8 ausschließlich mittelbar über die Zwischenstücke 14 an der Rotorwelle 9 radial verankert sind.In the assembled state, the support contours 26 of the intermediate pieces 14 can be supported radially on the support contours 24 of the receiving groove 10. According to FIG. 2 have the blade roots 13 on its inner side 27, which faces away from the gas path 12 and from the outer side 15 of the blade root 13, in the circumferential direction 19 projecting paragraphs 28 on. In this case, each blade root 13 expediently two such paragraphs 28 are provided, which protrude at two opposite end faces in the circumferential direction 19 of the respective end face. In the assembled state, these paragraphs 28 each engage under an inner side 29 of the adjacent intermediate piece 14, which faces away from the outer side 17 of the intermediate piece 14 or from the gas path 12. Furthermore, the paragraphs 28 are supported in the assembled state radially on the inner sides 29 of the adjacent intermediate pieces 14 from. Particularly advantageous is an embodiment in which the blades 8 are anchored exclusively indirectly via the intermediate pieces 14 on the rotor shaft 9 radially.

Gemäß Figur 5 kann die Endwandkontur 16 so konfiguriert sein, dass sie genau zwei Wendepunkte 30 aufweist, wodurch es möglich ist, eine zur Rotationsachse 6 hin orientierte konkave Wölbung 31 auszubilden sowie tangentiale Übergänge an den Endabschnitten 32 der Endwandkontur 16 zu realisieren. Die Wölbung 31 ist erkennbar bezüglich einer geometrischen Mitte 33 der Endwandkontur 16 bezüglich der Axialrichtung 20 versetzt angeordnet, also außermittig angeordnet. Insbesondere ist die Wölbung 31 dabei bezüglich der Mitte 33 zur Anströmseite hin verschoben positioniert.According to FIG. 5 For example, the end wall contour 16 may be configured to have exactly two inflection points 30, thereby making it possible to form a concave camber 31 oriented toward the rotation axis 6 and to realize tangential transitions at the end portions 32 of the end wall contour 16. The curvature 31 is recognizable offset with respect to a geometric center 33 of the end wall contour 16 with respect to the axial direction 20 arranged, that is arranged eccentrically. In particular, the curvature 31 is thereby positioned shifted with respect to the center 33 to the inflow side.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Turbomaschineturbomachinery
22
Verdichtercompressor
33
Turbineturbine
44
Statorstator
55
Rotorrotor
66
Rotationsachseaxis of rotation
77
LaufschaufelreiheBlade row
88th
Laufschaufelblade
99
Rotorwellerotor shaft
1010
Aufnahmenutreceiving groove
1111
Schaufelblattairfoil
1212
Gaspfadgas path
1313
Schaufelfußblade
1414
Zwischenstückconnecting piece
1515
Außenseite von 13Outside of 13
1616
EndwandkonturEndwandkontur
1717
Außenseite von 14Outside of 14
1818
Breite von 13Width of 13
1919
Umfangsrichtungcircumferentially
2020
Axialrichtungaxially
2121
Strömungsrichtungflow direction
2222
Breite von 14Width of 14
2323
Nutwandgroove wall
2424
Stützstruktur von 10Support structure of 10
2525
Ende von 14End of 14
2626
Stützstruktur von 14Support structure of 14
2727
Innenseite von 13Inside of 13
2828
Absatzparagraph
2929
Innenseite von 14Inside of 14
3030
Wendepunktturning point
3131
Wölbungbulge
3232
Endabschnittend
3333
Mittecenter

Claims (11)

Rotor für eine Turbomaschine (1), - mit wenigstens einer Laufschaufelreihe (7), die mehrere Laufschaufeln (8) aufweist, die bezüglich einer Rotationsachse (6) des Rotors (5) in der Umfangsrichtung (19) zueinander benachbart angeordnet sind, - mit wenigstens einer Rotorwelle (9), die für die jeweilige Laufschaufelreihe (7) eine sich in Umfangsrichtung (19) erstreckende Aufnahmenut (10) aufweist, in welche die Laufschaufeln (8) mit ihren Schaufelfüßen (13) eingesetzt sind, - mit mehreren Zwischenstücken (14), die in der Aufnahmenut (10) jeweils zwischen zwei benachbarten Laufschaufeln (8) angeordnet sind, - wobei die Laufschaufeln (8) an ihren Schaufelfüßen (13) an einer Außenseite (15) jeweils eine gewölbte Endwandkontur (16) in der Umfangsrichtung (19) neben einem Schaufelblatt (11) der jeweiligen Laufschaufel (8) aufweisen, - wobei die Zwischenstücke (14) an einer Außenseite (17) ebenfalls jeweils eine gewölbte Endwandkontur (17) aufweisen, - wobei die Außenseiten (15, 17) der Schaufelfüße (13) und der Zwischenstücke (14) radial bündig in der Umfangsrichtung (19) aneinandergrenzen, dadurch gekennzeichnet,
dass die Einwandkontur (16) in einer axialen Schnittebene des Rotors eine konkave Wölbung (31) aufweist.Rotor for a turbomachine (1), - having at least one blade row (7) having a plurality of blades (8) which are arranged adjacent to each other with respect to a rotation axis (6) of the rotor (5) in the circumferential direction (19), - With at least one rotor shaft (9), which for the respective blade row (7) in the circumferential direction (19) extending receiving groove (10) into which the blades (8) are inserted with their blade roots (13), - With a plurality of intermediate pieces (14) which are arranged in the receiving groove (10) between each two adjacent blades (8), - wherein the rotor blades (8) at their blade roots (13) on an outer side (15) each have a curved Endwandkontur (16) in the circumferential direction (19) adjacent to an airfoil (11) of the respective blade (8) - wherein the intermediate pieces (14) on an outer side (17) also each have a curved Endwandkontur (17), - Wherein the outer sides (15, 17) of the blade roots (13) and the intermediate pieces (14) radially flush adjacent in the circumferential direction (19), characterized,
objection that the contour (16) has a concave curvature (31) in an axial section plane of the rotor. Rotor nach Anspruch 1,
dadurch gekennzeichnet,
dass die Endwandkonturen (16) zwei Wendepunkte (30) aufweist.Rotor according to claim 1,
characterized,
that the Endwandkonturen (16) has two turning points (30). Rotor nach Anspruch 1 oder 2,
dadurch gekennzeichnet,
dass die Wölbung (31) zur Anströmseite oder zur Abströmseite verschoben angeordnet ist.Rotor according to claim 1 or 2,
characterized,
that the curvature (31) is arranged displaced to the inflow side or to the outflow side. Rotor nach Anspruch 1 oder 2,
dadurch gekennzeichnet,
dass die Endwandkonturen (16) axial-symmetrisch ausgestaltet sind.Rotor according to claim 1 or 2,
characterized,
that the end wall contours (16) are configured axially symmetrical. Rotor nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet,
dass die Endwandkonturen (16) an den Außenseiten (15, 17) der Schaufelfüße (13) und der Zwischenstücke (14) gleich sind.Rotor according to one of claims 1 to 4,
characterized,
that the Endwandkonturen (16) on the outer sides (15, 17) of the blade roots (13) and the intermediate pieces (14) are equal. Rotor nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet,
dass die Zwischenstücke (14) und die Schaufelfüße (13) asymmetrisch sind, so dass die Zwischenstücke (14) nur in einer Montageposition ordnungsgemäß montierbar sind.Rotor according to one of claims 1 to 5,
characterized,
in that the intermediate pieces (14) and the blade roots (13) are asymmetrical, so that the intermediate pieces (14) can be mounted correctly only in a mounting position. Rotor nach einem der Ansprüche 1 bis 6,
dadurch gekennzeichnet,
dass die Aufnahmenut (10) an ihren Nutwänden (23) radial nach innen gerichtete Stützkonturen (24) aufweist, wobei die Zwischenstücke (14) zu den Stützkonturen (24) der Aufnahmenut (10) komplementäre, radial nach außen gerichtete Stützkonturen (26) aufweisen, die sich im montierten Zustand radial an den Stützkonturen (24) der Aufnahmenut (10) abstützen.Rotor according to one of claims 1 to 6,
characterized,
in that the receiving groove (10) has radially inwardly directed support contours (24) on its groove walls (23), the intermediate pieces (14) having radially outwardly directed support contours (26) complementary to the support contours (24) of the receiving groove (10) , which are supported radially in the mounted state on the support contours (24) of the receiving groove (10). Rotor nach Anspruch 7,
dadurch gekennzeichnet,
dass die Schaufelfüße (13) an ihrer Innenseite (27) in der Umfangsrichtung (19) vorstehende Absätze (28) aufweisen, die sich im montierten Zustand radial an einer Innenseite (29) des jeweils benachbarten Zwischenstücks (14) abstützen.Rotor according to claim 7,
characterized,
in that the blade roots (13) have, on their inside (27) in the circumferential direction (19), projecting shoulders (28) which, in the mounted state, are supported radially on an inside (29) of the respectively adjacent intermediate piece (14). Rotor nach Anspruch 8,
dadurch gekennzeichnet,
dass die Laufschaufeln (8) ausschließlich mittelbar über die Zwischenstücke (14) an der Rotorwelle (9) radial befestigt sind.Rotor according to claim 8,
characterized,
that the rotor blades (8) are only indirectly attached radially above the intermediate pieces (14) on the rotor shaft (9). Verdichter oder Turbine für eine Turbomaschine (1) mit einem Rotor (5) nach einem der Ansprüche 1 bis 9.Compressor or turbine for a turbomachine (1) with a rotor (5) according to one of claims 1 to 9. Verfahren zum Modernisieren eines Rotors (5) einer Turbomaschine (1), insbesondere eines Verdichters (2) oder einer Turbine (3), wobei der Rotor (5) umfasst wenigstens eine Laufschaufelreihe (7), die mehrere Laufschaufeln (8) aufweist, die bezüglich einer Rotationsachse (6) des Rotors (5) in der Umfangsrichtung (19) zueinander benachbart angeordnet sind, wenigstens eine Rotorwelle (9), die für die jeweilige Laufschaufelreihe (7) eine sich in Umfangsrichtung (19) erstreckende Aufnahmenut (10) aufweist, in welche die Laufschaufeln (8) mit ihren Schaufelfüßen (13) eingesetzt sind, mit mehreren Zwischenstücken (14), die in der Aufnahmenut (10) jeweils zwischen zwei benachbarten Laufschaufeln (8) angeordnet sind, - bei dem die Laufschaufeln (8) gegen Laufschaufeln (8) ausgetauscht werden, die an ihren Schaufelfüßen (13) an einer Außenseite (15) jeweils eine gewölbte Endwandkontur (16) in der Umfangsrichtung (19) neben einem Schaufelblatt (11) der jeweiligen Laufschaufel (8) aufweisen, - bei dem die Zwischenstücke (14) gegen Zwischenstücke (14) ausgetauscht werden, die an ihrer Außenseite (17) ebenfalls jeweils eine gewölbte Endwandkontur (17) aufweisen. Method for modernizing a rotor (5) of a turbomachine (1), in particular a compressor (2) or a turbine (3), wherein the rotor (5) comprises at least one row of blades (7) having a plurality of moving blades (8) with respect to a rotation axis (6) of the rotor (5) in the circumferential direction (19) adjacent to each other, at least one rotor shaft (9) for the respective blade row (7) in the circumferential direction (19) extending receiving groove (10) in which the blades (8) are inserted with their blade roots (13), with a plurality of intermediate pieces (14) which are arranged in the receiving groove (10) in each case between two adjacent blades (8), - In which the blades (8) are replaced by blades (8) at their blade roots (13) on an outer side (15) each have a curved Endwandkontur (16) in the circumferential direction (19) adjacent to an airfoil (11) of the respective Have blade (8), - In which the intermediate pieces (14) are replaced by intermediate pieces (14), which also on their outer side (17) each have a curved Endwandkontur (17).
EP12162535.4A 2011-03-31 2012-03-30 Rotor for a turbomachine and corresponding upgrading method Active EP2505784B1 (en)

Priority Applications (1)

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Applications Claiming Priority (1)

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CH00583/11A CH704825A1 (en) 2011-03-31 2011-03-31 Turbomachinery rotor.

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EP (1) EP2505784B1 (en)
JP (1) JP5875439B2 (en)
CN (1) CN102733858B (en)
AU (1) AU2012201556B2 (en)
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HR (1) HRP20160587T1 (en)
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GB2488864B (en) * 2011-03-07 2016-05-04 Alstom Technology Ltd Rotor blade arrangement of a turbomachine

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RU2682217C1 (en) * 2018-03-30 2019-03-15 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Gas turbine engine working wheel of rotor
JP7162514B2 (en) * 2018-12-07 2022-10-28 三菱重工業株式会社 Axial turbomachinery and its blades

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US20120251325A1 (en) 2012-10-04
US8915716B2 (en) 2014-12-23
MY165413A (en) 2018-03-21
CN102733858A (en) 2012-10-17
HRP20160587T1 (en) 2016-07-01
AU2012201556A1 (en) 2012-10-18
CN102733858B (en) 2015-09-09
RU2544019C2 (en) 2015-03-10
JP5875439B2 (en) 2016-03-02
JP2012215175A (en) 2012-11-08
CH704825A1 (en) 2012-10-15
RU2012112418A (en) 2013-10-10
EP2505784B1 (en) 2016-03-02
AU2012201556B2 (en) 2015-07-23

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