EP2410131B1 - Rotor of a turbomachine - Google Patents

Rotor of a turbomachine Download PDF

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Publication number
EP2410131B1
EP2410131B1 EP11161987.0A EP11161987A EP2410131B1 EP 2410131 B1 EP2410131 B1 EP 2410131B1 EP 11161987 A EP11161987 A EP 11161987A EP 2410131 B1 EP2410131 B1 EP 2410131B1
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EP
European Patent Office
Prior art keywords
rotor
coupling element
blade
axial direction
radially
Prior art date
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Not-in-force
Application number
EP11161987.0A
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German (de)
French (fr)
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EP2410131A2 (en
EP2410131A3 (en
Inventor
Tilmann Dr. Raible
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MAN Energy Solutions SE
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MAN Diesel and Turbo SE
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Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2410131A2 publication Critical patent/EP2410131A2/en
Publication of EP2410131A3 publication Critical patent/EP2410131A3/en
Application granted granted Critical
Publication of EP2410131B1 publication Critical patent/EP2410131B1/en
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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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric

Definitions

  • the invention relates to a rotor of a turbomachine according to the preamble of claim 1.
  • a rotor of a turbomachine in particular a gas turbine or steam turbine, has a rotor base body and a plurality of rotor blades which are fastened to the rotor base body.
  • the blades of such a turbomachinery rotor have a blade root and an airfoil, each blade being secured via its blade root to the rotor body in a groove of the rotor body in a mounting direction defined by the blade roots, and each blade having at least one coupler segment in the region of its airfoil when it is positioned radially outward on the airfoil, is formed as an outer shroud segment.
  • the coupling element segments, in particular outer shroud segments, of all the moving blades of such a turbomachine rotor together form at least one coupling element closed in the circumferential direction, in particular an outer shroud, of the rotor.
  • a width of a coupling element segment, in particular an outer shroud segment, of each blade is defined by edges extending substantially in the axial direction.
  • a depth in the axial direction of the coupling element segment, in particular the outer shroud segment, of each blade is defined by substantially circumferentially extending edges.
  • a coupling element segment, in particular an outer shroud segment, each blade is also characterized by a thickness in the radial direction.
  • Turbomachine rotors whose rotor blades have such coupling element segments for forming at least one coupling element can be installed both in the region of a compressor and in the region of a turbine of the turbomachine.
  • Turbomachinery rotors on the rotor base body of which rotor blades are fastened, which have a coupling element segment formed radially on the outside of the airfoil as an outer cover band segment, are for example made DE 1 159 965 C , out DE 40 15 206 C1 as well as out US 4,400,915 A and from GB 2 072 760 A known. From the EP 1 134 359 A1 and the DE 1 122 551 C the attachment of the blades on the blade roots on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet is known. The blade feet may be fir-tree-like, hammerhead-like or otherwise contoured. For each blade root, a separate groove may be present on the rotor body. Furthermore, it is possible that all blade roots are mounted in a common groove and threaded into this common groove via a threading and thus mounted on the rotor body.
  • the coupling elements of such turbomachinery rotors designed as outer shrouds are exposed to high loads during operation, since they rotate with respect to a rotational axis of the turbomachine rotor to a maximum radius and are therefore exposed to high centrifugal forces.
  • corners or edges of the coupling element segments of the blades can bend outwards, which on the one hand in the coupling element voltage spikes are caused and on the other hand, a desired contact between adjacent coupling element segments adjacent blades is reduced to a punctiform contact or disappears completely.
  • a desired coupling between adjacent coupling element segments is reduced or eliminated, which ultimately worsens the vibration behavior of the turbomachine rotor.
  • the present invention is based on the problem to provide a rotor of a turbomachine, in which a good coupling of the coupling element segments of the blades is ensured with good mountability of the rotor during operation.
  • a rotor according to claim 1.
  • the or each coupling element segment of each blade on a first side, in the circumferential direction, a coupling element segment of a first immediately adjacent blade connects, and at one on one of the first side opposite the second side, seen in the circumferential direction, a coupling element segment a second immediately adjacent blade adjoins, contoured such that on the first side and on the second side of a substantially axially extending radially outer edge and a substantially axially extending radially inner edge of the respective coupling element segment each two separated by a dividing line Limiting surfaces, wherein at at least one circumferential position of the rotor between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent In some other circumferential position between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent blades to the mounting direction of the blades on the rotor blades at approximately approximately parallel or rectified to the plane defined
  • the contouring of the coupling element segments of the rotor blades ensures optimum support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor.
  • the present invention relates to a rotor of a turbomachine, in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine.
  • a rotor of a turbomachine in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine.
  • the invention is not limited to these applications, but the invention can be used in all turbomachinery rotors.
  • a rotor of a turbomachine basically has a rotor main body and a plurality of rotor blades, which are fastened to the rotor base body via blade feet.
  • the rotor body and the blade roots of blades are not shown in detail since these details are familiar to those skilled in the art.
  • each blade is fastened via its blade root on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet.
  • a separate groove on the rotor base body may be present for each blade or the blade root of each blade.
  • it is possible that all blades are fastened via their blade roots in a common groove and are threaded into this common groove via a threading opening and thus mounted on the rotor base body.
  • the mounting direction M of the blades on the rotor base body defined by the blade feet is shown schematically in dashed lines.
  • the mounting direction M rectilinear
  • the mounting direction M is curved.
  • the mounting direction M of the blades is inclined with respect to the axial direction A in a first orientation in the circumferential direction U, wherein the mounting direction M and the axial direction A include a so-called rhomboid angle, which in a curved mounting direction M in the axial direction A changed.
  • a radial direction R of the same is furthermore shown.
  • FIG. 1 to 4 show different detail views of a rotor according to the invention of a turbomachine according to a first embodiment of the invention, wherein in Fig. 1 3 shows a section of a coupling element designed as an outer cover strip, which is composed of coupling element segments 10, 10 ', 10 "of a plurality of moving blades formed as outer cover tape segments
  • the outer cover tape segments 10, 10', 10" are, as best 3 and 4 can be removed, is associated with a radially outer end of a blade 11 of the respective blade.
  • the airfoil 11 has a flow inlet edge 12, a flow outlet edge 13 and a suction side 14 and pressure side 15 extending between the flow inlet edge 12 and the flow outlet edge 13.
  • the outer shroud segment 10, 10 ', 10 "radially outwardly assigned to the blade 11 of each blade has a width in the circumferential direction U, which is defined by edges extending substantially in the axial direction A.
  • radially outer edge 18 and 19 on two opposite sides 16 and 17 of FIG Outer shroud segment 10, 10 ', 10 "in each case one extending substantially in the axial direction A, radially outer edge 18 and 19 and in each case also extending substantially in the axial direction A, radially inner edge 20 and 21.
  • the distance between this radially outer edge 18 and 19 and this radially inner edge 20 and 21 determined on the sides 16 and 17 in the radial direction R, the thickness of the outer shroud segment 10, 10 ', 10 ".
  • a depth in the axial direction A of the outer shroud segment 10, 10 ', 10 "of each blade is defined by edges extending substantially in the circumferential direction U, again by radially outer edges 22 and 23 and radially inner edges 24 and 25, respectively the edges at the edges 22 and 24 are flow-entry-side edges and edges at the edges 23 and 25.
  • the distance between these edges also determines the thickness of the outer shroud segment 10, 10 ', 10 "in the radial direction R, namely the flow inlet side and the flow outlet side.
  • the radially inner edge 20 of the outer shroud segment 10, 10 ', 10 "extending substantially in the axial direction A is opposite the radially outer edge 18, which also extends substantially in the axial direction A. Circumferential direction U before.
  • second side 17 of the outer shroud segment 10, 10 ', 10 " at which an immediately adjacent, second blade with its outer shroud segment, namely with a first side thereof, followed, the same is contoured such that the flow outlet side adjacent to the flow outlet edge 13 of the airfoil 11 which extends substantially in the axial direction A extending, radially outer edge 19 of the outer shroud segment 10, 10 ', 10 "relative to the also extending substantially in the axial direction A, radially inner edge 21 in the circumferential direction U protrudes.
  • the surface 28, which is concealed from the outside is positioned on the flow inlet side and the surface 30, which is visible from the radial outside, is positioned on the outlet side in the region of the opposite, second side 17 of the outer shroud segment 10, 10', 10 on the other hand, the surface 29, which is concealed radially from the outside, is positioned on the flow exit side and the surface 31, which is visible from the radial outside, is positioned on the flow inlet side.
  • the parting lines 26, 27 of these immediately adjacent moving blades are approximately parallel or rectified to the mounting direction M defined over the blade roots on immediately adjacent sides of the respective coupling element segments 10 'and 10 " of the rotor blades at the rotor base body, whereas at each other circumferential position between two directly adjacent rotor blades the separating lines 26, 27 of these immediately adjacent blades are inclined to the mounting direction M on immediately adjacent sides of the respective coupling element segments 10, 10 'and 10 ".
  • the mounting direction M of the rotor blades is inclined relative to the axial direction A in a first orientation in the circumferential direction U about the so-called rhomboid angle.
  • the parting lines 26, 27 are inclined in a direction opposite to the first orientation second orientation as the mounting direction M relative to the axial direction in the circumferential direction.
  • the above contouring of the coupling element segments 10, 10 'and 10 "of the rotor blades ensures optimal support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor Coupling element segments 10, 10 'and 10 "are inclined to the mounting direction M, an optimal support and thus coupling of the coupling element segments.
  • the radially outer edges 18, 19, which extend essentially in the axial direction A, and the radially inner edges 20, 21, which also extend essentially in the axial direction A, preferably run together with the dividing lines 26, 27, the surfaces 28, 29, 30 and 31 limit.
  • the dividing lines 26 and 27 which separate the surfaces 28 and 30 and the surfaces 29 and 31 from each other on the first side 16 and on the second side 17 are executed according to a preferred embodiment of the invention without turning points, wherein the same in the embodiment of Fig. 1 to 4 straight and in Fig. 5 curved. This allows a particularly simple production. Likewise, the substantially extending in the axial direction A edges 18, 19, 20 and 21 are executed without turning points.
  • dividing line 26 of the first side 16 is visible from radially outside, whereas the dividing line 27 of the second side 17 is hidden from the outside when viewed radially.
  • the dividing lines 26 and 27 of the two sides 16, 17, starting from the flow inlet-side edges to flow-outlet-side edges, run in each case from radially outside to radially inside.
  • first side 16 of the outer shroud segment 10 and the opposite, second side 17 of the outer shroud segment 10 are seen in the direction along the respective parting line 26 and 27 viewed from radially outside surfaces 28 and 29 and the visible from radially outside surfaces 30th or 31 each with respect to the radial direction R inclined at an angle.
  • the surfaces 28 and 29, which are concealed radially from the outside are inclined by a first angle relative to the radial direction R and the surfaces 30 and 31, which are visible from the radially outside, are inclined by a second angle relative to the radial direction R.
  • the first angle and the second angle are equal in magnitude, but have different signs. This is particularly advantageous in terms of manufacturing technology. In contrast to this, however, it is also possible for the first angle and the second angle to be different in magnitude on the first side 16 and on the second side 17, but in turn have different signs.
  • FIG. 1 How best Fig. 1 can be removed, as viewed from radially outside both on the first side 16 and on the second side 17 of the outer shroud segment 10 extending substantially in the axial direction A, radially outer edge 18 and 19 and which are substantially in the axial direction A extending, radially inner edge 20 and 21 congruent only at an axial position.
  • Fig. 1 to 4 are formed on the sides 16 and 17 of the outer shroud segment 10 surfaces 28 and 29 and the surfaces 30 and 31 respectively formed as a three-dimensional contoured, spatially radially curved. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24, and 25 are then curved.
  • these surfaces 28, 29, 30 and 31 are designed as two-dimensionally contoured, flat surfaces. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24 and 25 are then straight.
  • the embodiment differs from the Fig. 5 from the embodiment of Fig. 1 to 4 only in that the mounting direction M of the blades is not rectilinear but curved.
  • the embodiment of the Fig. 5 with the embodiment of Fig. 1 to 4 match, so that reference is made to the above statements.
  • a rotor according to the invention has no outer shroud segment but exclusively at least one coupling element segment embodied as an inner coupling element segment. Furthermore, it is possible for the parting line 26 of the first side 16 to be concealed from radially outside, whereas the parting line 27 of the second side 17 is visible from radially outside.

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

Description

Die Erfindung betrifft einen Rotor einer Turbomaschine nach dem Oberbegriff des Anspruchs 1.The invention relates to a rotor of a turbomachine according to the preamble of claim 1.

Ein Rotor einer Turbomaschine, insbesondere einer Gasturbine oder Dampfturbine, verfügt über einen Rotorgrundkörper sowie über mehrere Laufschaufeln, die am Rotorgrundkörper befestigt sind. Die Laufschaufeln eines solchen Turbomaschinenrotors verfügen über einen Schaufelfuß und ein Schaufelblatt, wobei jede Laufschaufel über ihren Schaufelfuß am Rotorgrundkörper in einer Nut des Rotorgrundkörpers in einer über die Schaufelfüße definierten Montagerichtung befestigt ist, und wobei jede Laufschaufel im Bereich ihres Schaufelblatts mindestens ein Koppelelementsegment aufweist, welches dann, wenn dasselbe radial außen am Schaufelblatt positioniert ist, als Außendeckbandsegment ausgebildet ist. Die Koppelelementsegmente, insbesondere Außendeckbandsegmente, aller Laufschaufeln eines solchen Turbomaschinenrotors bilden zusammen mindestens ein in Umfangsrichtung geschlossenes Koppelelement, insbesondere ein Außendeckband, des Rotors.A rotor of a turbomachine, in particular a gas turbine or steam turbine, has a rotor base body and a plurality of rotor blades which are fastened to the rotor base body. The blades of such a turbomachinery rotor have a blade root and an airfoil, each blade being secured via its blade root to the rotor body in a groove of the rotor body in a mounting direction defined by the blade roots, and each blade having at least one coupler segment in the region of its airfoil when it is positioned radially outward on the airfoil, is formed as an outer shroud segment. The coupling element segments, in particular outer shroud segments, of all the moving blades of such a turbomachine rotor together form at least one coupling element closed in the circumferential direction, in particular an outer shroud, of the rotor.

In Umfangsrichtung eines Turbomaschinenrotors gesehen ist eine Breite eines Koppelelementsegments, insbesondere eines Außendeckbandsegments, einer jeden Laufschaufel durch sich im Wesentlichen in Axialrichtung erstreckende Kanten definiert. Eine Tiefe in Axialrichtung des Koppelelementsegments, insbesondere des Außendeckbandsegments, einer jeden Laufschaufel ist durch sich im Wesentlichen in Umfangsrichtung erstreckende Kanten definiert. Neben der Breite in Umfangsrichtung sowie der Tiefe in Axialrichtung ist ein Koppelelementsegment, insbesondere ein Außendeckbandsegment, einer jeden Laufschaufel auch durch eine Dicke in Radialrichtung gekennzeichnet.As seen in the circumferential direction of a turbomachinery rotor, a width of a coupling element segment, in particular an outer shroud segment, of each blade is defined by edges extending substantially in the axial direction. A depth in the axial direction of the coupling element segment, in particular the outer shroud segment, of each blade is defined by substantially circumferentially extending edges. In addition to the width in the circumferential direction and the depth in the axial direction, a coupling element segment, in particular an outer shroud segment, each blade is also characterized by a thickness in the radial direction.

Turbomaschinenrotoren, deren Laufschaufeln derartige Koppelelementsegmente zur Bildung mindestens eines Koppelelements aufweisen, können sowohl im Bereich eines Verdichters als auch im Bereich einer Turbine der Turbomaschine verbaut sein.Turbomachine rotors whose rotor blades have such coupling element segments for forming at least one coupling element can be installed both in the region of a compressor and in the region of a turbine of the turbomachine.

Turbomaschinenrotoren, an deren Rotorgrundkörper Laufschaufeln befestigt sind, die radial außen am Schaufelblatt ein als Außendeckbandsegment ausgebildetes Koppelelementsegment aufweisen, sind zum Beispiel aus DE 1 159 965 C , aus DE 40 15 206 C1 sowie aus US 4,400,915 A und aus GB 2 072 760 A bekannt. Aus der EP 1 134 359 A1 und der DE 1 122 551 C ist die Befestigung der Laufschaufeln über die Schaufelfüße am Rotorgrundkörper in einer Nut des Rotorgrundkörpers in einer über die Schaufelfüße definierten Montagerichtung bekannt. Die Schaufelfüße können tannenbaumartig, hammerkopfartig oder auf sonstige Art und Weise konturiert sein. Für jeden Schaufelfuß kann eine separate Nut am Rotorgrundkörper vorhanden sein. Weiterhin ist es möglich, dass alle Schaufelfüße in einer gemeinsamen Nut befestigt sind und in diese gemeinsame Nut über eine Einfädelöffnung eingefädelt und damit am Rotorgrundkörper montiert werden.Turbomachinery rotors, on the rotor base body of which rotor blades are fastened, which have a coupling element segment formed radially on the outside of the airfoil as an outer cover band segment, are for example made DE 1 159 965 C , out DE 40 15 206 C1 as well as out US 4,400,915 A and from GB 2 072 760 A known. From the EP 1 134 359 A1 and the DE 1 122 551 C the attachment of the blades on the blade roots on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet is known. The blade feet may be fir-tree-like, hammerhead-like or otherwise contoured. For each blade root, a separate groove may be present on the rotor body. Furthermore, it is possible that all blade roots are mounted in a common groove and threaded into this common groove via a threading and thus mounted on the rotor body.

Insbesondere die als Außendeckbänder ausgebildeten Koppelelemente solcher Turbomaschinenrotoren sind im Betrieb hohen Belastungen ausgesetzt, da dieselben bezogen auf eine Drehachse des Turbomaschinenrotors auf maximalem Radius rotieren und daher hohen Fliehkräften ausgesetzt sind. In Folge der Fliehkraftbelastung können sich Ecken bzw. Kanten der Koppelelementsegmente der Laufschaufeln nach außen biegen, wodurch einerseits im Koppelelement Spannungsspitzen verursacht werden und andererseits ein gewünschter Kontakt zwischen benachbarten Koppelelementsegmenten benachbarter Laufschaufeln auf einen punktförmigen Kontakt reduziert wird bzw. ganz verschwindet. Dadurch wird eine gewünschte Kopplung zwischen benachbarten Koppelelementsegmenten reduziert bzw. aufgehoben, wodurch sich letztendlich das Schwingungsverhalten des Turbomaschinenrotors verschlechtert.In particular, the coupling elements of such turbomachinery rotors designed as outer shrouds are exposed to high loads during operation, since they rotate with respect to a rotational axis of the turbomachine rotor to a maximum radius and are therefore exposed to high centrifugal forces. As a result of the centrifugal force, corners or edges of the coupling element segments of the blades can bend outwards, which on the one hand in the coupling element voltage spikes are caused and on the other hand, a desired contact between adjacent coupling element segments adjacent blades is reduced to a punctiform contact or disappears completely. As a result, a desired coupling between adjacent coupling element segments is reduced or eliminated, which ultimately worsens the vibration behavior of the turbomachine rotor.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zugrunde, einen Rotor einer Turbomaschine zu schaffen, bei dem im Betrieb eine gute Kopplung der Koppelelementsegmente der Laufschaufeln bei guter Montierbarkeit des Rotors gewährleistet ist.On this basis, the present invention is based on the problem to provide a rotor of a turbomachine, in which a good coupling of the coupling element segments of the blades is ensured with good mountability of the rotor during operation.

Dieses Problem wird durch einen Rotor gemäß Anspruch 1 gelöst. Erfindungsgemäß ist das oder jedes Koppelelementsegment einer jeden Laufschaufel an einer ersten Seite, an der sich in Umfangsrichtung gesehen ein Koppelelementsegment einer ersten unmittelbar benachbarten Laufschaufel anschließt, und an einer an einer der ersten Seite gegenüberliegenden zweiten Seite, an der sich in Umfangsrichtung gesehen ein Koppelelementsegment einer zweiten unmittelbar benachbarten Laufschaufel anschließt, derart konturiert, dass an der ersten Seite und an der zweiten Seite eine sich im wesentlichen in Axialrichtung erstreckende radial äußere Kante und eine sich im wesentlichen in Axialrichtung erstreckende radial innere Kante des jeweiligen Koppelelementsegments jeweils zwei durch eine Trennlinie voneinander getrennte Flächen begrenzen, wobei an mindestens einer Umfangsposition des Rotors zwischen zwei unmittelbar benachbarten Laufschaufeln die an unmittelbar benachbarten Seiten der Koppelelementsegmente ausgebildeten Trennlinien dieser unmittelbar benachbarten Laufschaufeln in etwa annähernd parallel bzw. gleichgerichtet zur der über die Schaufelfüße definierten Montagerichtung der Laufschaufeln am Rotorgrundkörper verlaufen, wohingegen an jeder anderen Umfangsposition zwischen zwei unmittelbar benachbarten Laufschaufeln die an unmittelbar benachbarten Seiten der Koppelelementsegmente ausgebildeten Trennlinien dieser unmittelbar benachbarten Laufschaufeln zur Montagerichtung der Laufschaufeln am Rotorgrundkörper schräggestellt sind.This problem is solved by a rotor according to claim 1. According to the invention, the or each coupling element segment of each blade on a first side, in the circumferential direction, a coupling element segment of a first immediately adjacent blade connects, and at one on one of the first side opposite the second side, seen in the circumferential direction, a coupling element segment a second immediately adjacent blade adjoins, contoured such that on the first side and on the second side of a substantially axially extending radially outer edge and a substantially axially extending radially inner edge of the respective coupling element segment each two separated by a dividing line Limiting surfaces, wherein at at least one circumferential position of the rotor between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent In some other circumferential position between two directly adjacent blades formed on immediately adjacent sides of the coupling element segments dividing lines of these immediately adjacent blades to the mounting direction of the blades on the rotor blades at approximately approximately parallel or rectified to the plane defined by the blade feet assembly direction of the rotor blades Rotor body are tilted.

Beim erfindungsgemäßen Rotor einer Turbomaschine wird durch die Konturierung der Koppelelementsegmente der Laufschaufeln eine optimale Abstützung und damit Kopplung der das oder jedes Koppelelement bildenden Koppelelementsegmente bei guter Montierbarkeit des Rotors gewährleistet.In the case of the rotor of a turbomachine according to the invention, the contouring of the coupling element segments of the rotor blades ensures optimum support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor.

Hierdurch können bei guter Montierbarkeit des Rotors im Betrieb Spannungsspitzen in dem oder jedem Koppelelement des Rotors deutlich reduziert werden. Ferner kann hierdurch das Eigenfrequenzverhalten und damit Schwingungsverhalten des erfindungsgemäßen Rotors bei guter Montierbarkeit desselben verbessert werden.As a result, voltage spikes in the or each coupling element of the rotor can be significantly reduced with good mountability of the rotor during operation. Furthermore, this can improve the natural frequency behavior and therefore the vibration behavior of the rotor according to the invention with good mountability thereof.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

  • Fig. 1: eine schematisierte, ausschnittsweise Draufsicht auf ein als Außendeckband ausgebildetes Koppelelement eines erfindungsgemäßen Rotors einer Turbomaschine in Blickrichtung von radial außen nach einem ersten Ausführungsbeispiel der Erfindung;
  • Fig. 2: eine schematisierte Draufsicht auf eine Laufschaufel des Rotors der Fig. 1, nämlich auf ein als Außendeckbandsegment ausgebildetes Koppelelementsegment der Laufschaufel des Rotors der Fig. 1, in Blickrichtung von radial außen;
  • Fig. 3: einen perspektivischen Ausschnitt aus der Laufschaufel der Fig. 2 in Umfangsblickrichtung I der Fig. 2 gesehen;
  • Fig. 4: einen weiteren perspektivischen Ausschnitt aus der Laufschaufel der Fig. 2 in Umfangsblickrichtung II der Fig. 2 gesehen; und
  • Fig. 5: eine schematisierte, ausschnittsweise Draufsicht auf ein als Außendeckband ausgebildetes Koppelelement eines erfindungsgemäßen Rotors einer Turbomaschine in Blickrichtung von radial außen nach einem zweiten Ausführungsbeispiel der Erfindung.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
  • Fig. 1 FIG. 2: a schematic, fragmentary plan view of a coupling element of an inventive rotor of a turbomachine designed as an outer cover tape in the direction of view from radially outside according to a first exemplary embodiment of the invention; FIG.
  • Fig. 2 : A schematic plan view of a rotor blade of the rotor Fig. 1 , Namely on a coupling element segment formed as an outer cover band segment of the rotor blade of the rotor Fig. 1 , in view from radially outside;
  • Fig. 3 : a perspective section of the blade of the Fig. 2 in the circumferential direction of the I Fig. 2 seen;
  • Fig. 4 : Another perspective section of the blade of the Fig. 2 in the circumferential direction II of Fig. 2 seen; and
  • Fig. 5 : A schematic, fragmentary plan view of a formed as an outer shroud coupling element of a rotor according to the invention of a turbomachine in the direction from the outside radially according to a second embodiment of the invention.

Die hier vorliegende Erfindung betrifft einen Rotor einer Turbomaschine, insbesondere einen Rotor eines Verdichters oder einer Turbine einer als Gasturbine oder Dampfturbine ausgebildeten Turbomaschine. Die Erfindung ist jedoch nicht auf diese Anwendungsfälle beschränkt, vielmehr kann die Erfindung bei allen Turbomaschinenrotoren zum Einsatz kommen.The present invention relates to a rotor of a turbomachine, in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine. However, the invention is not limited to these applications, but the invention can be used in all turbomachinery rotors.

Ein Rotor einer Turbomaschine verfügt grundsätzlich über einen Rotorgrundkörper und mehrere Laufschaufeln, die über Schaufelfüße am Rotorgrundkörper befestigt sind. In Fig. 1 bis 5 sind der Rotorgrundkörper sowie die Schaufelfüße von Laufschaufeln nicht im Detail gezeigt, da diese Details dem hier angesprochenen Fachmann geläufig sind. Es sei jedoch an dieser Stelle darauf hingewiesen, dass jede Laufschaufel über ihren Schaufelfuß am Rotorgrundkörper in einer Nut des Rotorgrundkörpers in einer über die Schaufelfüße definierten Montagerichtung befestigt ist. Dabei kann für jede Laufschaufel bzw. den Schaufelfuß jeder Laufschaufel eine separate Nut am Rotorgrundkörper vorhanden sein. Weiterhin ist es möglich, dass alle Laufschaufeln über ihre Schaufelfüße in einer gemeinsamen Nut befestigt sind und in diese gemeinsame Nut über eine Einfädelöffnung eingefädelt und damit am Rotorgrundkörper montiert werden.A rotor of a turbomachine basically has a rotor main body and a plurality of rotor blades, which are fastened to the rotor base body via blade feet. In Fig. 1 to 5 the rotor body and the blade roots of blades are not shown in detail since these details are familiar to those skilled in the art. However, it should be noted at this point that each blade is fastened via its blade root on the rotor base body in a groove of the rotor base body in a mounting direction defined by the blade feet. In this case, a separate groove on the rotor base body may be present for each blade or the blade root of each blade. Furthermore, it is possible that all blades are fastened via their blade roots in a common groove and are threaded into this common groove via a threading opening and thus mounted on the rotor base body.

In Fig. 1 und 5 ist die über die Schaufelfüße definierte Montagerichtung M der Laufschaufeln am Rotorgrundkörper in gestrichelter Linienführung schematisiert gezeigt. In Fig. 1 und 5 ist für den Schaufelfuß jeder Laufschaufel eine separate Nut am Rotorgrundkörper vorhanden, wobei in Fig. 1 die Montagerichtung M geradlinig und in Fig. 5 die Montagerichtung M gekrümmt verläuft. In beiden Fällen ist die Montagerichtung M der Laufschaufeln in Axialrichtung A des Rotors gesehen gegenüber der Axialrichtung A in einer ersten Orientierung in Umfangrichtung U geneigt, wobei die Montagerichtung M und die Axialrichtung A einen sogenannten Rhomboidwinkel einschließen, der sich bei einer gekrümmten Montagerichtung M in Axialrichtung A verändert. Neben der Axialrichtung A und Umfangrichtung U des Rotors ist weiterhin eine Radialrichtung R desselben gezeigt.In Fig. 1 and 5 the mounting direction M of the blades on the rotor base body defined by the blade feet is shown schematically in dashed lines. In Fig. 1 and 5 For the blade root of each blade a separate groove on the rotor body is present, in Fig. 1 the mounting direction M rectilinear and in Fig. 5 the mounting direction M is curved. In both cases, as seen in the axial direction A of the rotor, the mounting direction M of the blades is inclined with respect to the axial direction A in a first orientation in the circumferential direction U, wherein the mounting direction M and the axial direction A include a so-called rhomboid angle, which in a curved mounting direction M in the axial direction A changed. In addition to the axial direction A and the circumferential direction U of the rotor, a radial direction R of the same is furthermore shown.

Fig. 1 bis 4 zeigen unterschiedliche Detailansichten eines erfindungsgemäßen Rotors einer Turbomaschine nach einem ersten Ausführungsbeispiel der Erfindung, wobei in Fig. 1 einen Ausschnitt aus einem als Außendeckband ausgebildeten Koppelelement zeigt, welches aus als Außendeckbandsegmenten ausgebildeten Koppelelementsegmenten 10, 10', 10" mehrerer Laufschaufeln zusammengesetzt ist. Die Außendeckbandsegmente 10, 10', 10" sind, wie am besten Fig. 3 und 4 entnommen werden kann, einem radial äußeren Ende eines Schaufelblatts 11 der jeweiligen Laufschaufel zugeordnet ist. Das Schaufelblatt 11 verfügt über eine Strömungseintrittskante 12, eine Strömungsaustrittskante 13 sowie über eine zwischen der Strömungseintrittskante 12 und der Strömungsaustrittskante 13 verlaufende Saugseite 14 und Druckseite 15. Fig. 1 to 4 show different detail views of a rotor according to the invention of a turbomachine according to a first embodiment of the invention, wherein in Fig. 1 3 shows a section of a coupling element designed as an outer cover strip, which is composed of coupling element segments 10, 10 ', 10 "of a plurality of moving blades formed as outer cover tape segments The outer cover tape segments 10, 10', 10" are, as best 3 and 4 can be removed, is associated with a radially outer end of a blade 11 of the respective blade. The airfoil 11 has a flow inlet edge 12, a flow outlet edge 13 and a suction side 14 and pressure side 15 extending between the flow inlet edge 12 and the flow outlet edge 13.

Das dem Schaufelblatt 11 einer jeden Laufschaufel radial außen zugeordnete Außendeckbandsegment 10, 10', 10" verfügt in Umfangsrichtung U über eine Breite, die durch sich im Wesentlichen in Axialrichtung A erstreckende Kanten definiert ist. So verlaufen an zwei sich gegenüberliegenden Seiten 16 und 17 des Außendeckbandsegments 10, 10', 10" jeweils eine sich im Wesentlichen in Axialrichtung A erstreckende, radial äußere Kante 18 bzw. 19 sowie jeweils eine sich ebenfalls im Wesentlichen in Axialrichtung A erstreckende, radial innere Kante 20 bzw. 21. Der Abstand zwischen dieser radial äußeren Kante 18 bzw. 19 und dieser radial inneren Kante 20 bzw. 21 bestimmt an den Seiten 16 und 17 in Radialrichtung R die Dicke des Außendeckbandsegments 10, 10', 10".The outer shroud segment 10, 10 ', 10 "radially outwardly assigned to the blade 11 of each blade has a width in the circumferential direction U, which is defined by edges extending substantially in the axial direction A. Thus, on two opposite sides 16 and 17 of FIG Outer shroud segment 10, 10 ', 10 "in each case one extending substantially in the axial direction A, radially outer edge 18 and 19 and in each case also extending substantially in the axial direction A, radially inner edge 20 and 21. The distance between this radially outer edge 18 and 19 and this radially inner edge 20 and 21 determined on the sides 16 and 17 in the radial direction R, the thickness of the outer shroud segment 10, 10 ', 10 ".

Eine Tiefe in Axialrichtung A des Außendeckbandsegments 10, 10', 10" einer jeden Laufschaufel wird durch sich im Wesentlichen in Umfangsrichtung U erstreckende Kanten definiert, nämlich wiederum durch radial äußere Kanten 22 bzw. 23 und radial innere Kanten 24 bzw. 25, wobei es sich bei den Kanten 22 und 24 um strömungseintrittsseitige Kanten und bei den Kanten 23 und 25 strömungsaustrittsseitige Kanten handelt. Auch der Abstand zwischen diesen Kanten bestimmt in Radialrichtung R die Dicke des Außendeckbandsegments 10, 10', 10", nämlich strömungseintrittsseitig und strömungsaustrittsseitig.A depth in the axial direction A of the outer shroud segment 10, 10 ', 10 "of each blade is defined by edges extending substantially in the circumferential direction U, again by radially outer edges 22 and 23 and radially inner edges 24 and 25, respectively the edges at the edges 22 and 24 are flow-entry-side edges and edges at the edges 23 and 25. The distance between these edges also determines the thickness of the outer shroud segment 10, 10 ', 10 "in the radial direction R, namely the flow inlet side and the flow outlet side.

In Blickrichtung von radial außen gesehen ist das Außendeckbandsegment 10, 10', 10" einer jeden Laufschaufel im Bereich einer ersten Seite 16, an der sich in Umfangsrichtung U ein Außendeckbandsegment einer ersten unmittelbar benachbarten Laufschaufel mit einer zweiten Seite derselben anschließt, derart konturiert, dass strömungseintrittsseitig benachbart zu der Strömungseintrittskante 12 des Schaufelblatts 11 der jeweiligen Laufschaufel die sich im Wesentlichen in Axialrichtung A erstreckende, radial äußere Kante 18 des Außendeckbandsegments 10, 10', 10" gegenüber der sich im Wesentlichen in Axialrichtung A erstreckenden, radial inneren Kante 20 des Außendeckbandsegments 10, 10', 10" in Umfangsrichtung U vorsteht.As seen from radially outside, the outer shroud segment 10, 10 ', 10 "of each blade in the region of a first side 16, in which adjoins an outer shroud segment of a first immediately adjacent blade with a second side thereof in the circumferential direction U, contoured such that the radially inward edge 18 of the outer shroud segment 10, 10 ', 10 "extending substantially in the axial direction A, relative to the radially inner edge 20 of the outer shroud segment extending substantially in the axial direction A, the flow inlet side adjacent to the flow inlet edge 12 of the blade 11 of the respective blade 10, 10 ', 10 "protrudes in the circumferential direction U.

An dieser ersten Seite 16 strömungsaustrittsseitig gewandt von der Strömungsaustrittskante 13 steht die sich im Wesentlichen in Axialrichtung A erstreckende, radial innere Kante 20 des Außendeckbandsegments 10, 10', 10" gegenüber der sich ebenfalls im Wesentlichen in Axialrichtung A erstreckenden, radial äußeren Kante 18 in Umfangsrichtung U vor.On this first side 16 facing the flow outlet on the flow outlet edge 13, the radially inner edge 20 of the outer shroud segment 10, 10 ', 10 "extending substantially in the axial direction A is opposite the radially outer edge 18, which also extends substantially in the axial direction A. Circumferential direction U before.

An der gegenüberliegenden, zweiten Seite 17 des Außendeckbandsegments 10, 10', 10", an der sich eine unmittelbar benachbarte, zweite Laufschaufel mit ihrem Außendeckbandsegment, nämlich mit einer ersten Seite desselben, anschließt, ist dasselbe derart konturiert, dass strömungsaustrittsseitig benachbart zu der Strömungsaustrittskante 13 des Schaufelblatts 11 die sich im Wesentlichen in Axialrichtung A erstreckende, radial äußere Kante 19 des Außendeckbandsegments 10, 10', 10" gegenüber der sich ebenfalls im Wesentlichen in Axialrichtung A erstreckenden, radial inneren Kante 21 in Umfangsrichtung U vorsteht.At the opposite, second side 17 of the outer shroud segment 10, 10 ', 10 ", at which an immediately adjacent, second blade with its outer shroud segment, namely with a first side thereof, followed, the same is contoured such that the flow outlet side adjacent to the flow outlet edge 13 of the airfoil 11 which extends substantially in the axial direction A extending, radially outer edge 19 of the outer shroud segment 10, 10 ', 10 "relative to the also extending substantially in the axial direction A, radially inner edge 21 in the circumferential direction U protrudes.

An dieser zweiten Seite 17 strömungseintrittsseitig abgewandt von der Strömungseintrittskante 12 steht die sich im Wesentlichen in Axialrichtung A erstreckende, radial innere Kante 21 des Außendeckbandsegments 10, 10', 10" gegenüber der sich ebenfalls im Wesentlichen in Axialrichtung A erstreckenden, radial äußeren Kante 19 in Umfangsrichtung U vor.Facing away from the flow inlet edge 12 on this second side 17, the radially inner edge 21 of the outer shroud segment 10, 10 ', 10 "extends essentially in the axial direction A, relative to the radially outer edge 19 which also extends essentially in the axial direction A. Circumferential direction U before.

An der ersten Seite 16 des Außendeckbandsegments 10, 10', 10", die der Strömungseintrittskante 12 des Schaufelblatts 11 zugewandt und von der Strömungsaustrittskante 13 desselben abgewandt ist, sowie an der zweite Seite 17 des Außendeckbandsegments 10, 10', 10", die der Strömungseintrittskante 13 des Schaufelblatts 11 zugewandt und von der Strömungseintrittskante 12 abgewandt ist, begrenzen die sich im Wesentlichen in Axialrichtung A erstreckenden, radial äußeren Kanten 18 bzw. 19 zusammen mit den jeweiligen sich ebenfalls im Wesentlichen in Axialrichtung A erstreckenden, radial inneren Kanten 20 bzw. 21 jeweils zwei durch eine Trennlinie 26 bzw. 27 voneinander getrennte Flächen, nämlich jeweils eine in Blickrichtung von radial außen verdeckte Fläche 28 bzw. 29 sowie jeweils eine in Blickrichtung von radial außen gesehen sichtbare Fläche 30 bzw. 31.On the first side 16 of the outer shroud segment 10, 10 ', 10 ", which faces the flow inlet edge 12 of the blade 11 and facing away from the flow outlet edge 13 thereof, as well as on the second side 17 of the outer shroud segment 10, 10', 10", the The flow inlet edge 13 of the blade 11 facing and facing away from the flow inlet edge 12, limit the extending substantially in the axial direction A, radially outer edges 18 and 19 together with the respective also extending substantially in the axial direction A, radially inner edges 20 and 21 in each case two surfaces separated from one another by a dividing line 26 or 27, namely in each case one surface 28 or 29 concealed in the viewing direction from radially outside and one surface 30 or 31 visible in the viewing direction from radially outside.

An der ersten Seite 16 des Außendeckbandsegments 10, 10', 10" ist die von radial außen verdeckte Fläche 28 strömungseintrittsseitig und die von radial außen sichtbare Fläche 30 strömungsaustrittsseitig positioniert. Im Bereich der gegenüberliegenden, zweiten Seite 17 des Außendeckbandsegments 10, 10', 10" hingegen ist die von radial außen verdeckte Fläche 29 strömungsaustrittsseitig und die von radial außen sichtbare Fläche 31 strömungseintrittsseitig positioniert.On the first side 16 of the outer shroud segment 10, 10 ', 10 ", the surface 28, which is concealed from the outside, is positioned on the flow inlet side and the surface 30, which is visible from the radial outside, is positioned on the outlet side in the region of the opposite, second side 17 of the outer shroud segment 10, 10', 10 on the other hand, the surface 29, which is concealed radially from the outside, is positioned on the flow exit side and the surface 31, which is visible from the radial outside, is positioned on the flow inlet side.

Erfindungsgemäß verlaufen an mindestens einer Umfangsposition des Rotors zwischen zwei unmittelbar benachbarten Laufschaufeln die an unmittelbar benachbarten Seiten der jeweiligen Koppelelementsegmente 10' und 10" ausgebildeten Trennlinien 26, 27 dieser unmittelbar benachbarten Laufschaufeln in etwa annähernd parallel bzw. gleichgerichtet zu der über die Schaufelfüße definierten Montagerichtung M der Laufschaufeln am Rotorgrundkörper, wohingegen an jeder anderen Umfangsposition zwischen zwei unmittelbar benachbarten Laufschaufeln die an unmittelbar benachbarten Seiten der jeweiligen Koppelelementsegmente 10, 10' und 10" ausgebildeten Trennlinien 26, 27 dieser unmittelbar benachbarten Laufschaufeln zur Montagerichtung M schräggestellt sind.According to the invention, at at least one circumferential position of the rotor between two directly adjacent moving blades, the parting lines 26, 27 of these immediately adjacent moving blades are approximately parallel or rectified to the mounting direction M defined over the blade roots on immediately adjacent sides of the respective coupling element segments 10 'and 10 " of the rotor blades at the rotor base body, whereas at each other circumferential position between two directly adjacent rotor blades the separating lines 26, 27 of these immediately adjacent blades are inclined to the mounting direction M on immediately adjacent sides of the respective coupling element segments 10, 10 'and 10 ".

Wie bereits ausgeführt ist die Montagerichtung M der Laufschaufeln am Rotorgrundkörper in Axialrichtung A des Rotors gesehen gegenüber der Axialrichtung A in einer ersten Orientierung in Umfangrichtung U um den sogenannten Rhomboidwinkel geneigt. An der oder jeder Umfangsposition des Rotors, an welcher die an den unmittelbar benachbarten Laufschaufeln ausgebildeten Trennlinien 26, 27 in etwa annähernd parallel bzw. gleichgerichtet zu der über die Schaufelfüße definierten Montagerichtung M der Laufschaufeln am Rotorgrundkörper verlaufen, sind die Trennlinien 26, 27 in der gleichen ersten Orientierung wie die Montagerichtung gegenüber der Axialrichtung A in Umfangrichtung U geneigt. Hingegen sind an der oder jeder anderen Umfangsposition des Rotors zwischen zwei unmittelbar benachbarten Laufschaufeln die Trennlinien 26, 27 in einer zur ersten Orientierung entgegen gesetzten zweiten Orientierung wie die Montagerichtung M gegenüber der Axialrichtung in Umfangrichtung geneigt.As already stated, as seen in the axial direction A of the rotor, the mounting direction M of the rotor blades is inclined relative to the axial direction A in a first orientation in the circumferential direction U about the so-called rhomboid angle. At the or each circumferential position of the rotor at which the dividing lines 26, 27 formed on the immediately adjacent blades extend approximately parallel or rectified to the mounting direction M of the blades on the rotor base defined by the blade feet, the parting lines 26, 27 in FIG same first orientation as the mounting direction relative to the axial direction A in the circumferential direction U inclined. On the other hand, at the or any other circumferential position of the rotor between two directly adjacent blades, the parting lines 26, 27 are inclined in a direction opposite to the first orientation second orientation as the mounting direction M relative to the axial direction in the circumferential direction.

Durch die obige Konturierung der Koppelelementsegmente 10, 10' und 10" der Laufschaufeln wird eine optimale Abstützung und damit Kopplung der das oder jedes Koppelelement bildenden Koppelelementsegmente bei guter Montierbarkeit des Rotors gewährleistet. So gewährleisten die Trennlinien 26 und 27, die an unmittelbar benachbarten Seiten der Koppelelementsegmente 10, 10' und 10" zur Montagerichtung M schräggestellt sind, eine optimale Abstützung und damit Kopplung der Koppelelementsegmente. Die Trennlinien 26 und 27, die an unmittelbar benachbarten Seiten der Koppelelementsegmente 10' und 10" in etwa annähernd parallel bzw. gleichgerichtet zur Montagerichtung M verlaufen, ermöglichen eine gute Montierbarkeit insbesondere der zuletzt am Rotorgrundkörper zu montierenden Laufschaufel. Es ist ausreichend, wenn an einer einzigen Umfangsposition des Rotors zwischen zwei unmittelbar benachbarten Laufschaufeln die an unmittelbar benachbarten Seiten der jeweiligen Koppelelementsegmente 10' und 10" ausgebildeten Trennlinien 26, 27 in etwa annähernd parallel bzw. gleichgerichtet zur Montagerichtung M der Laufschaufeln am Rotorgrundkörper verlaufen. Dies kann zur Verbesserung des Schwingungsverhaltens aber auch an mehreren Umfangspositionen des Rotors der Fall sein.The above contouring of the coupling element segments 10, 10 'and 10 "of the rotor blades ensures optimal support and thus coupling of the coupling element segments forming the or each coupling element with good mountability of the rotor Coupling element segments 10, 10 'and 10 "are inclined to the mounting direction M, an optimal support and thus coupling of the coupling element segments. The dividing lines 26 and 27, which extend approximately directly parallel to or parallel to the mounting direction M on immediately adjacent sides of the coupling element segments 10 'and 10 ", allow a good mountability, in particular of the last rotor blade to be mounted on the rotor blade single circumferential position of the rotor between two immediately adjacent blades on approximately immediately adjacent sides of the respective coupling element segments 10 'and 10 "formed dividing lines 26, 27 in approximately approximately parallel or rectified to the mounting direction M of the blades run on the rotor body. This can be the case for improving the vibration behavior but also at a plurality of circumferential positions of the rotor.

Durch die obige Konturierung der Koppelelementsegmente 10, 10' und 10" der Laufschaufeln können bei guter Montierbarkeit des Rotors im Betrieb Spannungsspitzen in dem oder jedem Koppelelement des Rotors deutlich reduziert werden. Ferner kann das Eigenfrequenzverhalten und damit Schwingungsverhalten des erfindungsgemäßen Rotors bei guter Montierbarkeit desselben verbessert werden.By virtue of the above contouring of the coupling element segments 10, 10 'and 10 "of the rotor blades, in the case of good mountability of the rotor during operation, voltage peaks in the or each coupling element of the rotor can be markedly reduced.Furthermore, the natural frequency behavior and thus oscillation behavior of the rotor according to the invention can be improved with good mountability become.

An der oder jeder Umfangsposition des Rotors, an welcher die an den Koppelelementsegmenten 10, 10' und 10" unmittelbar benachbarten Laufschaufeln ausgebildeten Trennlinien 26, 27 in etwa annähernd parallel zu der über die Schaufelfüße definierten Montagerichtung M der Laufschaufeln am Rotorgrundkörper verlaufen, schließen die Trennlinien 26, 27 mit der Montagerichtung M einen Winkel von maximal 10°, vorzugsweise von maximal 5°, ein.At the or each circumferential position of the rotor, on which the dividing lines 26, 27 formed on the coupling element segments 10, 10 'and 10 "directly approximately parallel to the mounting direction M of the blades defined on the blade feet on the rotor main body, close the parting lines 26, 27 with the mounting direction M an angle of not more than 10 °, preferably of at most 5 °, a.

In der gleichen Orientierung wie die Trennlinien 26, 27 verlaufen vorzugsweise auch die sich im Wesentlichen in Axialrichtung A erstreckenden, radial äußeren Kanten 18 bzw. 19 sowie die sich ebenfalls im Wesentlichen in Axialrichtung A erstreckenden, radial inneren Kanten 20 bzw. 21, die zusammen mit den Trennlinien 26, 27 die Flächen 28, 29, 30 bzw. 31 begrenzen.In the same orientation as the parting lines 26, 27, the radially outer edges 18, 19, which extend essentially in the axial direction A, and the radially inner edges 20, 21, which also extend essentially in the axial direction A, preferably run together with the dividing lines 26, 27, the surfaces 28, 29, 30 and 31 limit.

Dann, wenn eine Trennlinie 26 bzw. 27 in etwa annähernd parallel bzw. gleichgerichtet zu der Montagerichtung M der Laufschaufeln verläuft, verlaufen auch die jeweiligen Kanten 18, 20 bzw. 19, 21 in etwa annähernd parallel bzw. gleichgerichtet zu der Montagerichtung M.Then, when a parting line 26 and 27 is approximately approximately parallel or rectified to the mounting direction M of the blades, the respective edges 18, 20 and 19, 21 extend approximately parallel or rectified to the mounting direction M.

Dann, wenn eine Trennlinie 26 bzw. 27 gegenüber Montagerichtung M der Laufschaufeln schräggestellt ist, sind auch die jeweiligen Kanten 18, 20 bzw. 19, 21 zu der Montagerichtung M schräggestellt, und zwar in der gleichen Orientierung wie die jeweilige Trennlinie 26 bzw. 27.Then, when a parting line 26 and 27 are inclined with respect to the mounting direction M of the blades, the respective edges 18, 20 and 19, 21 are inclined to the mounting direction M, in the same orientation as the respective parting line 26 and 27th ,

Die Trennlinien 26 und 27, die an der ersten Seite 16 sowie an der zweiten Seite 17 die Flächen 28 und 30 bzw. die Flächen 29 und 31 voneinander trennen, sind nach einer bevorzugten Weiterbildung der Erfindung wendepunktfrei ausgeführt, wobei dieselben im Ausführungsbeispiel der Fig. 1 bis 4 geradlinig und in Fig. 5 gekrümmt verlaufen. Dies erlaubt eine besonders einfache Fertigung. Ebenso sind die sich im Wesentlichen in Axialrichtung A erstreckenden Kanten 18, 19, 20 und 21 wendepunktfrei ausgeführt.The dividing lines 26 and 27 which separate the surfaces 28 and 30 and the surfaces 29 and 31 from each other on the first side 16 and on the second side 17 are executed according to a preferred embodiment of the invention without turning points, wherein the same in the embodiment of Fig. 1 to 4 straight and in Fig. 5 curved. This allows a particularly simple production. Likewise, the substantially extending in the axial direction A edges 18, 19, 20 and 21 are executed without turning points.

Im Ausführungsbeispiel der Fig. 1 bis 4 ist die Trennlinie 26 der ersten Seite 16 von radial außen gesehen sichtbar, wohingegen die Trennlinie 27 der zweiten Seite 17 von radial außen gesehen verdeckt ist. Gemäß Fig. 3 und 4 verlaufen die Trennlinien 26 und 27 der beiden Seiten 16, 17 ausgehend von strömungseintrittsseitigen Kanten zu strömungsaustrittsseitigen Kanten jeweils von radial außen nach radial innen.In the embodiment of Fig. 1 to 4 the dividing line 26 of the first side 16 is visible from radially outside, whereas the dividing line 27 of the second side 17 is hidden from the outside when viewed radially. According to 3 and 4 The dividing lines 26 and 27 of the two sides 16, 17, starting from the flow inlet-side edges to flow-outlet-side edges, run in each case from radially outside to radially inside.

Im Bereich der ersten Seite 16 des Außendeckbandsegments 10 sowie der gegenüberliegenden, zweiten Seite 17 des Außendeckbandsegments 10 sind in Blickrichtung entlang der jeweiligen Trennlinie 26 bzw. 27 gesehen die von radial außen verdeckten Flächen 28 bzw. 29 sowie die von radial außen gesehen sichtbaren Flächen 30 bzw. 31 gegenüber der Radialrichtung R jeweils um einen Winkel geneigt. Dabei sind die von radial außen verdeckten Flächen 28 bzw. 29 gegenüber der Radialrichtung R um einen ersten Winkel und die von radial außen sichtbaren Flächen 30 bzw. 31 gegenüber der Radialrichtung R um einen zweiten Winkel geneigt. An der ersten Seite 16 und an der zweiten Seite 17 sind vorzugsweise der erste Winkel und der zweite Winkel betragsmäßig gleich groß, jedoch mit unterschiedlichen Vorzeichen behaftet. Dies ist fertigungstechnisch besonders vorteilhaft. Im Unterschied hierzu ist es jedoch auch möglich, dass an der ersten Seite 16 und an der zweiten Seite 17 der erste Winkel und der zweite Winkel betragsmäßig unterschiedlich groß sind, jedoch wiederum unterschiedliche Vorzeichen aufweisen.In the region of the first side 16 of the outer shroud segment 10 and the opposite, second side 17 of the outer shroud segment 10 are seen in the direction along the respective parting line 26 and 27 viewed from radially outside surfaces 28 and 29 and the visible from radially outside surfaces 30th or 31 each with respect to the radial direction R inclined at an angle. In this case, the surfaces 28 and 29, which are concealed radially from the outside, are inclined by a first angle relative to the radial direction R and the surfaces 30 and 31, which are visible from the radially outside, are inclined by a second angle relative to the radial direction R. On the first side 16 and on the second side 17, preferably the first angle and the second angle are equal in magnitude, but have different signs. This is particularly advantageous in terms of manufacturing technology. In contrast to this, however, it is also possible for the first angle and the second angle to be different in magnitude on the first side 16 and on the second side 17, but in turn have different signs.

Nach einer Weiterbildung der Erfindung weisen sowohl an der ersten Seite 16 des Außendeckbandsegments 10 als auch an der zweiten Seite 17 des Außendeckbandsegments 10 die von radial außen verdeckte Fläche 28 bzw. 29 und die von radial außen sichtbare Fläche 30 bzw. 31 ein Flächenverhältnis von 1:1 auf, was bedeutet, dass an beiden Seiten 16 und 17 die von radial außen verdeckte Fläche 28 bzw. 29 und die von radial außen sichtbare Fläche 30 bzw. 31 gleich groß sind. Es sei darauf hingewiesen, dass an der ersten Seite 16 und an der zweiten Seite 17 diese Flächen auch unterschiedlich groß sein können. So ist es möglich, dass an der ersten Seite 16 und/oder an der zweiten Seite 17 die von radial außen verdeckte Fläche 28 bzw. 29 und die von radial außen sichtbare Fläche 30 bzw. 31 ein Flächenverhältnis von bis zu 1:5 oder von bis zu 5:1, insbesondere ein Flächenverhältnis von bis zu 1:3 oder von bis zu 3:1, aufweisen. Mit dem gezielten Vergrößern oder Verkleinern des Flächenverhältnisses zwischen der von radial außen verdeckten Fläche 28 bzw. 29 und der von radial außen sichtbaren Fläche 30 bzw. 31 an den Seiten 16 und 17 ist es möglich, die gewünschte Kopplung zwischen Außendeckbandsegmenten 10 benachbarter Laufschaufeln optimal anzupassen. Dies kann auch über die bereits oben erwähnten Winkel, welche diese Flächen mit der jeweiligen Trennlinie 26 bzw. 27 einschließen, erfolgen.According to a development of the invention, both on the first side 16 of the outer shroud segment 10 and on the second side 17 of the outer shroud segment 10, the radially outwardly hidden surface 28 and 29 and the radially outwardly visible surface 30 and 31, respectively, an area ratio of 1 1, which means that on both sides 16 and 17, the radially outwardly hidden surface 28 and 29 and the radially outwardly visible surface 30 and 31 are the same size. It should be noted that on the first side 16 and on the second side 17, these surfaces can also be different in size. Thus, it is possible that on the first side 16 and / or on the second side 17 of the radially outer concealed surface 28 and 29 and the radially outwardly visible surface 30 and 31, an area ratio of up to 1: 5 or up to 5: 1, in particular an area ratio of up to 1: 3 or of up to 3: 1. With the targeted enlargement or reduction of the area ratio between the radially outwardly hidden surface 28 and 29 and the radially outwardly visible surface 30 and 31 on the sides 16 and 17, it is possible to optimally adapt the desired coupling between outer shroud segments 10 adjacent blades , This can also be done via the already mentioned above angles, which include these surfaces with the respective dividing line 26 and 27, respectively.

Wie am besten Fig. 1 entnommen werden kann, sind in Blickrichtung von radial außen gesehen sowohl an der ersten Seite 16 als auch an der zweiten Seite 17 des Außendeckbandsegments 10 die sich im Wesentlichen in Axialrichtung A erstreckende, radial äußere Kante 18 bzw. 19 und die sich im Wesentlichen in Axialrichtung A erstreckende, radial innere Kante 20 bzw. 21 ausschließlich an einer Axialposition deckungsgleich.How best Fig. 1 can be removed, as viewed from radially outside both on the first side 16 and on the second side 17 of the outer shroud segment 10 extending substantially in the axial direction A, radially outer edge 18 and 19 and which are substantially in the axial direction A extending, radially inner edge 20 and 21 congruent only at an axial position.

Gemäß Fig. 1 bis 4 sind die an den Seiten 16 und 17 des Außendeckbandsegments 10 ausgebildeten Flächen 28 bzw. 29 und die Flächen 30 bzw. 31 jeweils als dreidimensional konturierte, räumlich radial gekrümmte ausgebildet. Sich im Wesentlichen in Radialrichtung erstreckende Kanten 32, die das Außendeckbandsegment 10 zusammen mit den Kanten 18, 19, 20, 21, 22, 23, 24 und 25 begrenzen, sind dann gekrümmt.According to Fig. 1 to 4 are formed on the sides 16 and 17 of the outer shroud segment 10 surfaces 28 and 29 and the surfaces 30 and 31 respectively formed as a three-dimensional contoured, spatially radially curved. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24, and 25 are then curved.

Im Unterschied hierzu ist es auch möglich, dass diese Flächen 28, 29, 30 und 31 als zweidimensional konturierte, ebene Flächen ausgeführt sind. Sich im Wesentlichen in Radialrichtung erstreckende Kanten 32, die das Außendeckbandsegment 10 zusammen mit den Kanten 18, 19, 20, 21, 22, 23, 24 und 25 begrenzen, sind verlaufen dann geradlinig.In contrast, it is also possible that these surfaces 28, 29, 30 and 31 are designed as two-dimensionally contoured, flat surfaces. Essentially radially extending edges 32 bounding the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24 and 25 are then straight.

Wie bereits ausgeführt, unterscheidet sich das Ausführungsbeispiel der Fig. 5 vom Ausführungsbeispiel der Fig. 1 bis 4 lediglich dadurch, dass die Montagerichtung M der Laufschaufeln nicht geradlinig sondern gekrümmt verläuft. Hinsichtlich der übrigen Details stimmt das Ausführungsbeispiel der Fig. 5 mit dem Ausführungsbeispiel der Fig. 1 bis 4 überein, sodass auf die obigen Ausführungen verwiesen wird.As already stated, the embodiment differs from the Fig. 5 from the embodiment of Fig. 1 to 4 only in that the mounting direction M of the blades is not rectilinear but curved. With regard to the remaining details, the embodiment of the Fig. 5 with the embodiment of Fig. 1 to 4 match, so that reference is made to the above statements.

Es sind weitere Abwandlungen der Erfindung möglich. So ist es möglich, dass zusätzlich die radial äußeren Kanten 18 und 19 sowie die radial inneren Kanten 20 und 21, die sich im wesentlichen in Axialrichtung A erstrecken und die Breite des Außendeckbandsegments 10 in Umfangsrichtung U definieren, an beiden sich gegenüberliegenden Seiten 16 und 17 ebenso wie die Trennlinien 26, 27 jeweils eine gekrümmte Kontur bzw. einen gekrümmten, jedoch wendepunktfreien Verlauf aufweisen. Weiterhin ist es möglich, dass ein erfindungsgemäßer Rotor nicht nur ein als Außendeckband 10 ausgebildetes Koppelelement sondern zusätzlich auch ein als Innenkoppelelement ausgebildetes Koppelelement aufweist. Dabei sind dann die Außendeckbandsegmente und Innenkoppelelementsegmente wie oben beschrieben ausgebildet. Ferner ist es möglich, dass ein erfindungsgemäßer Rotors kein Außendeckbandsegment sondern ausschließlich mindestens ein als Innenkoppelelementsegment ausgebildetes Koppelelementsegment aufweist. Ferner ist möglich, dass die Trennlinie 26 der ersten Seite 16 von radial außen gesehen verdeckt, wohingegen die Trennlinie 27 der zweiten Seite 17 von radial außen gesehen sichtbar ist. Bezugszeichenliste 10, 10', 10" Koppelelementsegment/Außendeckbandsegment 11 Schaufelblatt 12 Strömungseinrittskante 13 Strömungsausrittskante 14 Saugseite 15 Druckseite 16 erste Seite 17 zweite Seite 18 radial äußere Kante 19 radial äußere Kante 20 radial innere Kante 21 radial innere Kante 22 strömungseintrittsseitig radial äußere Kante 23 strömungsaustrittsseitig radial äußere Kante 24 strömungseintrittsseitig radial innere Kante 25 strömungsaustrittsseitig radial innere Kante 26 Tennlinie 27 Tennlinie 28 von radial außen verdeckte Fläche 29 von radial außen verdeckte Fläche 30 von radial außen sichtbare Fläche 31 von radial außen sichtbare Fläche 32 Kante There are further modifications of the invention possible. Thus, it is possible that in addition the radially outer edges 18 and 19 and the radially inner edges 20 and 21 which extend substantially in the axial direction A and define the width of the outer shroud segment 10 in the circumferential direction U, on both opposite sides 16 and 17th as well as the dividing lines 26, 27 each have a curved contour or a curved, but without turning point course. Furthermore, it is possible that a rotor according to the invention not only has a coupling element designed as outer cover tape 10 but additionally also has a coupling element designed as an inner coupling element. In this case, then the outer shroud segments and inner coupling element segments are formed as described above. Furthermore, it is possible that a rotor according to the invention has no outer shroud segment but exclusively at least one coupling element segment embodied as an inner coupling element segment. Furthermore, it is possible for the parting line 26 of the first side 16 to be concealed from radially outside, whereas the parting line 27 of the second side 17 is visible from radially outside. LIST OF REFERENCE NUMBERS 10, 10 ', 10 " Coupling element segment / outer shroud segment 11 airfoil 12 Strömungseinrittskante 13 Flow edge ride 14 suction 15 pressure side 16 first page 17 second page 18 radially outer edge 19 radially outer edge 20 radially inner edge 21 radially inner edge 22 flow inlet side radially outer edge 23 flow outlet side radially outer edge 24 flow inlet side radially inner edge 25 flow outlet side radially inner edge 26 Building a proper division 27 Building a proper division 28 of radially outwardly hidden surface 29 of radially outwardly hidden surface 30 surface visible radially outwards 31 surface visible radially outwards 32 edge

Claims (15)

  1. A rotor of a turbomachine, with a rotor basic body and with multiple moving blades, wherein each moving blade comprises a blade root and a blade leaf, wherein each moving blade is fastened via its blade root to the rotor basic body in a groove of the rotor basic body in an assembly direction defined via the blade roots, wherein each moving blade in the region of its blade leaf comprises at least one coupling element segment (10, 10', 10"), and wherein in the circumferential direction a width of the or each coupling element segment (10, 10', 10") of each moving blade is defined by edges extending substantially in the axial direction, characterized in that the or each coupling element segment (10, 10', 10") of each moving blade is contoured on a first side (16), which, seen in the circumferential direction, is followed by a coupling element segment of a first directly adjacent moving blade, and on a second side (17) located opposite the first side (16), which, seen in the circumferential direction, is followed by a coupling element of a second directly adjacent moving blade in such a manner that on the first side (16) and on the second side (17) the radially outer edge (18, 19) extending substantially in the axial direction and the radially inner edge (20, 21) extending substantially in the axial direction of the respective coupling element segment each delimit two faces that are separated from one another by a separating line (26, 27), wherein in at least one circumferential position of the rotor between two directly adjacent moving blades the separating lines (26, 27) of these directly adjacent moving blades formed on directly adjacent sides (16, 17) of the coupling element segments (10', 10") run approximately parallel or equi-directionally to the assembly direction of the moving blades on the rotor basic body defined via the blade roots, whereas in every other circumferential position between two directly adjacent moving blades, the separating lines (26, 27) of these directly adjacent moving blades formed on directly adjacent sides of the coupling element segments (10, 10', 10") are set obliquely to the assembly direction.
  2. The rotor according to Claim 1, characterized in that in the or any circumferential position of the rotor, in which on the separating lines (26, 27) run approximately parallel or equi-directionally to the assembly direction of the moving blades on the rotor basic body defined via the roots, the separating lines (26, 27) include an angle of maximally 10° with the assembly direction.
  3. The rotor according to Claim 2, characterized in that in the or any circumferential direction of the rotor, in which the separating lines (26, 27), formed on the directly adjacent moving blades, run approximately parallel or equi-directionally to the assembly direction of the moving blades on the rotor basic body defined via the blade roots, the separating lines (26, 27) include an angle of maximally 5° with the assembly direction.
  4. The rotor according to any one of the Claims 1 to 3, characterized in that the assembly direction of the moving blades on the rotor basic body seen in the axial direction is inclined in a first orientation in the circumferential direction relative to the axial direction, wherein in the or any circumferential position of the rotor, on which the separating lines (26, 27) formed on the directly adjacent moving blades run approximately parallel or equi-directionally to the assembly direction of the moving blades on the rotor basic body defined via the blade roots, the separating lines (26, 27) are inclined in the circumferential direction in the same orientation as the assembly direction relative to the axial direction, whereas in the or any other circumferential position of the rotor between two directly adjacent moving blades, the separating lines (26, 27) are inclined in the circumferential direction in a second orientation that is opposite to the first orientation regarding the assembly direction relative to the axial direction.
  5. The rotor according to any one of the Claims 1 to 4, characterized in that in the viewing direction from radially outside the or each coupling element segment (10, 10', 10") of each moving blade is contoured on the first side (16) in such a manner that on the flow inlet side adjacent to a flow inlet edge (12) of the respective moving blade the radially outer edge (18) extending substantially in the axial direction protrudes in the circumferential direction relative to the radially inner edge (20) extending substantially in the axial direction, whereas on this first side (16) on the flow outlet side facing away from a flow outlet edge (13) of the respective moving blade the radially inner edge (20) extending substantially in the axial direction protrudes in the circumferential direction relative to the radially outer edge (18) extending substantially in the axial direction, and in that the or each coupling element segment (10, 10', 10') of each moving blade on the second side (17) is contoured in such a manner that on the flow outlet side adjacent to the flow outlet edge (13) of the respective moving blade the radially outer edge (19) extending substantially in the axial direction protrudes in the circumferential direction relative to the radially inner edge (21) extending substantially in the axial direction, whereas on this second side (17) on the flow inlet side facing away from the flow inlet edge (12) of the respective moving blade, the radially inner edge (21) extending substantially in the axial direction protrudes in the circumferential direction relative to the radially outer edge (19) substantially extending in the axial direction.
  6. The rotor according to any one of the Claims 1 to 5, characterized in that on the first side (16) and on the second side (17) in each case a face (28, 29) that is concealed in viewing direction from radially outside and in each case a face (30, 31) that is visible in viewing direction from radially outside is formed, wherein on the first side (16) the face (28) that is concealed from radially outside is positioned on the flow inlet side and the face (30) that is visible from radially outside is positioned on the flow outlet side, and wherein on the second side (17) the face (29) that is concealed from radially outside is positioned on the flow outlet side and the face (31) that is visible from radially outside is positioned on the flow inlet side.
  7. The rotor according to any one of the Claims 1 to 6, characterized in that on the first side (16) and on the second side (17) of the respective coupling element segment the separating lines (26, 27), which on the first side (16) and on the second side (17) separate the face (28, 29) that is concealed from radially outside and the face (30, 31) that is visible from radially outside from one another, are formed without inflection point.
  8. The rotor according to any one of the Claims 1 to 7, characterized in that on the first side (16) and on the second side (17) of the respective coupling element segment seen in viewing direction along the separating lines (26, 27) the face (28, 29) that is concealed from radially outside is inclined relative to the radial direction by a first angle and the face (30, 31) that is visible from radially outside is inclined relative to the radial direction by a second angle.
  9. The rotor according to Claim 8, characterized in that on the first side (16) and on the second side (17) of the respective coupling element segment the first angle and the second angle are identical in size in the amount and have different signs or the first angle and the second angle are different in size in the amount and have different signs.
  10. The rotor according to any one of the Claims 1 to 9, characterized in that on the first side (16) and on the second side (17) of the respective coupling element segment the face (28, 29) that is concealed from radially outside and the face (30, 31) that is visible from radially outside are identical in size and accordingly have a face ratio of 1:1.
  11. The rotor according to any one of the Claims 1 to 9, characterized in that on the first side (16) and on the second side (17) of the respective coupling element segment the face (28, 29) that is concealed from radially outside and the face (30, 31) that is visible from radially outside are different in size and preferentially have an area ratio of up to 1:5 or of up to 5:1, in particular an area ratio of up to 1:3 or of up to 3:1.
  12. The rotor according to any one of the Claims 1 to 11, characterized in that on the first side (16) and on the second size (17) of the respective coupling element segment the face (28, 29) that is concealed from radially outside and the face (30, 31) that is visible from radially outside are each two-dimensionally contoured flat faces or three-dimensionally contoured spatially curved faces.
  13. The rotor according to any one of the Claims 1 to 12, characterized in that on the first side (16) and/or on the second side (17) of the respective coupling element segment in viewing direction from radially outside, the radially outer edge (18, 19) substantially extending in the axial direction and the radially inner edge (20, 21) extending substantially in the axial direction are congruent in exclusively one axial position.
  14. The rotor according to any one of the Claims 1 to 13, characterized in that each moving blade in the region of its blade leaf comprises radially outside a coupling element segment formed as outer shroud segment.
  15. The rotor according to any one of the Claims 1 to 14, characterized in that each moving blade in the region of its blade leaf comprises at least one coupling element segment formed as inner coupling element segment.
EP11161987.0A 2010-07-12 2011-04-12 Rotor of a turbomachine Not-in-force EP2410131B1 (en)

Applications Claiming Priority (1)

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DE102010031213A DE102010031213A1 (en) 2010-07-12 2010-07-12 Rotor of a turbomachine

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EP2410131A2 EP2410131A2 (en) 2012-01-25
EP2410131A3 EP2410131A3 (en) 2017-08-02
EP2410131B1 true EP2410131B1 (en) 2018-08-15

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US (1) US8974186B2 (en)
EP (1) EP2410131B1 (en)
JP (1) JP5274625B2 (en)
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CN114382555A (en) * 2020-10-16 2022-04-22 中国航发商用航空发动机有限责任公司 Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate

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JP5274625B2 (en) 2013-08-28
EP2410131A2 (en) 2012-01-25
DE102010031213A1 (en) 2012-01-12
US20120009067A1 (en) 2012-01-12
US8974186B2 (en) 2015-03-10
JP2012021529A (en) 2012-02-02
CN102330572B (en) 2014-07-09
EP2410131A3 (en) 2017-08-02
CN102330572A (en) 2012-01-25

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