EP2505784A1 - Rotor for a turbomachine and corresponding upgrading method - Google Patents
Rotor for a turbomachine and corresponding upgrading method Download PDFInfo
- 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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- Prior art keywords
- rotor
- intermediate pieces
- blades
- blade
- circumferential direction
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- 238000000034 method Methods 0.000 title claims abstract description 4
- 230000000295 complement effect Effects 0.000 claims description 4
- 230000007704 transition Effects 0.000 description 6
- 125000006850 spacer group Chemical group 0.000 description 4
- 230000001419 dependent effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- 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
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- 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
Description
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.
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
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.
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.
- 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.
Entsprechend
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
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
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
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
Bei der in
Sofern die Endwandkonturen 16 wie in den
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
Gemäß
Im montierten Zustand können sich die Stützkonturen 26 der Zwischenstücke 14 radial an den Stützkonturen 24 der Aufnahmenut 10 abstützen. Gemäß
Gemäß
- 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)
dass die Einwandkontur (16) in einer axialen Schnittebene des Rotors eine konkave Wölbung (31) aufweist.Rotor for a turbomachine (1),
objection that the contour (16) has a concave curvature (31) in an axial section plane of the rotor.
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).
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.
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.
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.
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.
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).
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).
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).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
HRP20160587TT HRP20160587T1 (en) | 2011-03-31 | 2016-05-31 | Rotor for a turbomachine and corresponding upgrading method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH00583/11A CH704825A1 (en) | 2011-03-31 | 2011-03-31 | Turbomachinery rotor. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2505784A1 true EP2505784A1 (en) | 2012-10-03 |
EP2505784B1 EP2505784B1 (en) | 2016-03-02 |
Family
ID=43857690
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12162535.4A Active EP2505784B1 (en) | 2011-03-31 | 2012-03-30 | Rotor for a turbomachine and corresponding upgrading method |
Country Status (9)
Country | Link |
---|---|
US (1) | US8915716B2 (en) |
EP (1) | EP2505784B1 (en) |
JP (1) | JP5875439B2 (en) |
CN (1) | CN102733858B (en) |
AU (1) | AU2012201556B2 (en) |
CH (1) | CH704825A1 (en) |
HR (1) | HRP20160587T1 (en) |
MY (1) | MY165413A (en) |
RU (1) | RU2544019C2 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3014942A1 (en) * | 2013-12-18 | 2015-06-19 | Snecma | DAWN, WHEEL IN AUBES AND TURBOMACHINE; PROCESS FOR MANUFACTURING DAWN |
GB2488864B (en) * | 2011-03-07 | 2016-05-04 | Alstom Technology Ltd | Rotor blade arrangement of a turbomachine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
WO2014028056A1 (en) | 2012-08-17 | 2014-02-20 | United Technologies Corporation | Contoured flowpath surface |
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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-
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- 2011-03-31 CH CH00583/11A patent/CH704825A1/en not_active Application Discontinuation
-
2012
- 2012-03-15 AU AU2012201556A patent/AU2012201556B2/en active Active
- 2012-03-26 MY MYPI2012700116A patent/MY165413A/en unknown
- 2012-03-29 US US13/433,314 patent/US8915716B2/en not_active Expired - Fee Related
- 2012-03-29 JP JP2012076732A patent/JP5875439B2/en not_active Expired - Fee Related
- 2012-03-30 EP EP12162535.4A patent/EP2505784B1/en active Active
- 2012-03-30 CN CN201210103914.1A patent/CN102733858B/en not_active Expired - Fee Related
- 2012-03-30 RU RU2012112418/06A patent/RU2544019C2/en active
-
2016
- 2016-05-31 HR HRP20160587TT patent/HRP20160587T1/en unknown
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Cited By (4)
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GB2488864B (en) * | 2011-03-07 | 2016-05-04 | Alstom Technology Ltd | Rotor blade arrangement of a turbomachine |
FR3014942A1 (en) * | 2013-12-18 | 2015-06-19 | Snecma | DAWN, WHEEL IN AUBES AND TURBOMACHINE; PROCESS FOR MANUFACTURING DAWN |
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Also Published As
Publication number | Publication date |
---|---|
US8915716B2 (en) | 2014-12-23 |
MY165413A (en) | 2018-03-21 |
AU2012201556A1 (en) | 2012-10-18 |
HRP20160587T1 (en) | 2016-07-01 |
CN102733858B (en) | 2015-09-09 |
RU2544019C2 (en) | 2015-03-10 |
AU2012201556B2 (en) | 2015-07-23 |
CN102733858A (en) | 2012-10-17 |
US20120251325A1 (en) | 2012-10-04 |
CH704825A1 (en) | 2012-10-15 |
JP2012215175A (en) | 2012-11-08 |
EP2505784B1 (en) | 2016-03-02 |
JP5875439B2 (en) | 2016-03-02 |
RU2012112418A (en) | 2013-10-10 |
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