EP2414641B1 - Axial turbo engine rotor with sealing disc - Google Patents

Axial turbo engine rotor with sealing disc Download PDF

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Publication number
EP2414641B1
EP2414641B1 EP10715749.7A EP10715749A EP2414641B1 EP 2414641 B1 EP2414641 B1 EP 2414641B1 EP 10715749 A EP10715749 A EP 10715749A EP 2414641 B1 EP2414641 B1 EP 2414641B1
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EP
European Patent Office
Prior art keywords
sealing ring
rotor
sealing
axial
radially
Prior art date
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EP10715749.7A
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German (de)
French (fr)
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EP2414641A1 (en
Inventor
Sascha Dungs
Peter Schröder
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Siemens AG
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Siemens AG
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Priority to EP10715749.7A priority Critical patent/EP2414641B1/en
Priority to PL10715749T priority patent/PL2414641T3/en
Publication of EP2414641A1 publication Critical patent/EP2414641A1/en
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Publication of EP2414641B1 publication Critical patent/EP2414641B1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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

Definitions

  • the invention relates to a Axialturbomaschinenrotor with a sealing washer.
  • An axial turbomachine for example a gas turbine, has a turbine in which hot gas is expanded.
  • the temperature of the hot gas at the inlet to the turbine is to be selected as high as possible.
  • the maximum feasible temperature level of the hot gas is limited by turbine strength requirements defined by design and material selection of turbine components.
  • the temperature load and the mechanical stress of the components dictates their service life, which has to be above certain limits for reasons of safety and economy.
  • a conventional turbine rotor has a shaft and discs mounted thereon in rotationally symmetrical manner, on the outer edge of which a plurality of rotor blades are fastened next to each other over the circumference.
  • the blades and discs are sometimes the most stressed components in the turbine, which primarily defines servicing cycles of the gas turbine for these components.
  • the blades are made of a filigree structure that is traversed by cooling channels through which the cooling air flows to cool the blades.
  • the cooling channels open into the blade root, where the cooling channels are fed with the cooling air.
  • the object of the invention is to provide a Axialturbomaschinenrotor, which has a long service life.
  • the axial turbomachinery rotor according to the invention has a rotor body rotationally symmetrical about the rotor axis, a rotor blade having a plurality of blades, which are each fixed with their blade root on the rotor body, and a rotationally symmetrical about the rotor axis formed sealing disc, the radially adjacent with its outer edge inside is arranged on an axially extending projection of the blade root, so that between the blade root and the sealing disc, a cavity is formed, wherein on the outer edge of a radially outwardly opening groove is provided, in which a sealing ring is mounted, which during operation of the rotor under the action of Centrifugal force is slidable radially outward in the groove until the sealing ring bears radially on the inside of the projection and thereby seals the cavity on the blade root.
  • the sealing ring Due to the fact that, during operation of the axial turbomachinery rotor, the sealing ring is pressed against the projection by the centrifugal force, the sealing ring is biased against the projection over the entire circumference. Thus, the contact between the sealing ring and the projection is well sealed, whereby the sealing effect between the projection and the sealing disc is high.
  • the cavity is, for example, a channel for supplying cooling air to the blade root, as may for example be provided in a turbine of a gas turbine, leakage of cooling air at the sealing ring is small. This is the cooling of the blades with the cooling air effectively, whereby the life of the axial turbomachinery rotor is high.
  • the gasket includes a plurality of gasket segments, which allows the assembly of blades and gasket after manufacture of a rotor - welded or stacked from rotor disks - allows a stationary gas turbine.
  • the sealing disk segments are preferably coupled to each other in the circumferential direction with a stepped rebate.
  • the assembly of the sealing disc to the rotor body is simple, wherein with the help of the stepped rebate with an offset in the circumferential direction of the individual sealing disc segments to each other a gaping apart of the sealing disc segments is prevented.
  • the sealing ring is formed by a plurality of circumferentially successively arranged sealing ring segments, which are each inserted in the at the outer edge of their associated sealing disc segment.
  • the sealing ring segments preferably have two longitudinal ends facing away from each other, each of which is formed by an envelope, which is in engagement with a recess provided on the groove, so that the sealing ring segments are fixed in the circumferential direction in a form-fitting manner on the outer edge.
  • the envelopes are preferably designed as legs formed in the axial direction in an L-shaped manner.
  • each of the legs preferably has a radius of curvature which is at least greater than half the longitudinal extension of the affected leg. It is thereby achieved that at the longitudinal ends of the sealing ring segment rests gas-tight on the sealing disc segment.
  • the projection has a radially inwardly opening groove into which the outer edge engages radially movable and at the bottom of the sealing ring can be applied.
  • the outer edge of the sealing disc is advantageously accommodated in the groove of the projection, whereby harmful influences, in particular a mechanical and / or thermal stress, are reduced to the sealing ring.
  • a pressure difference is reduced transversely to the sealing ring, so that the sealing effect of the sealing ring is high.
  • the sealing ring segments are formed as a band having an elongated cross section, the longitudinal sides extend in the radial direction and the outer short side can be applied to the blade root. Characterized in that the longitudinal sides of the sealing ring segments extend in the radial direction, the sealing ring segments are guided in their radial movement in the groove of the sealing ring segments. Thus, a twisting and tilting of the sealing ring segments is prevented in the grooves of the sealing disc segments.
  • the axial turbomachine rotor is preferably an axial turbine rotor, and the rotor blades preferably have air ducts which open into the cavity at the blade root, wherein the cavity is provided for supplying cooling air and / or cooling air for the cooling air ducts.
  • an axial turbine rotor 1 has a plurality of rotor blades 2, which are lined up over the circumference of the axial turbine rotor 1 and thereby form a blade grid.
  • the axial turbine rotor 1 further comprises a disc 3, on which the rotor blades 2 are mounted.
  • Each blade 2 has an airfoil 4 with which the blade 2 is aerodynamically effective.
  • this has a blade root 5, which is held in a form-fitting manner in the disc 3, so that the blade 2 is fixed in the radial direction of the blade root 5.
  • a base plate 7 of the blade 2 is provided which extends in the axial direction and in the circumferential direction and is aerodynamically effective on its radially outer side.
  • the disc 2 is frontally limited with a plane perpendicular to the axis of the axial turbine rotor surface. Axially spaced from this surface, a sealing disc 7 is arranged, whereby between the sealing disc 7 and the disc 3, a cavity is formed. As a result, the cavity of the hot gas side 8 of the axial turbine rotor is limited by the sealing disk 7.
  • the cavity is adeluftzu 1500kanal 9, which is provided for the cooling air supply of cooling air to the blade root 5.
  • An inner edge 22, which is thickened with respect to the average wall thickness of the sealing disk 7, of the sealing disk 7 is radially hooked to the disk 3, as a result of which, in operation, the Seal 7 is held radially from the disc 3 directly.
  • the outer edge 10 of the sealing disc 7 is arranged radially adjacent to the radially inner side of the base plate 6, wherein the outer edge 10 of the sealing disc 7 engages in a provided in the radially inner side of the base plate 6, circumferential groove 11.
  • a circumferential groove 12 is provided, which opens radially outward into the groove 11 of the base plate 6.
  • the outer edge 10 of the sealing disc 7 is arranged radially at a distance from the bottom of the groove 11 of the base plate 6, so that a radial play 13 is provided.
  • a sealing ring 14 is inserted, which has a cross-section which is elongated or rectangular in the radial direction.
  • the groove 12 in the sealing disc 7 is provided in the sealing disc 7 so deep that the sealing ring 14 in the groove 12 is flush with the outer edge 10 of the sealing disc 7.
  • a centrifugal force which leads to a radial movement 15 of the sealing ring.
  • the radial movement 15 is completed by the sealing ring 14 until the sealing ring 14 rests against the bottom of the groove 11 in the base plate 6.
  • the radial play 13 is adjusted to the radial extent of the sealing ring 14 such that when concerns of the sealing ring 14 at the bottom of the groove 11 of the base plate 6 of the sealing ring 14 is still engaged with the groove 12 in the outer edge 10 of the sealing washer 7.
  • the sealing disc 7 is formed by a plurality of sealing disc segments 16, which are lined up next to each other over the circumference. At their edges at which the sealing disk segments 16 are arranged adjacent to each other, a stepped fold 17 is formed in each case by a stop 18 of a sealing disk segment 16 and with a the stop 18 corresponding step 19 of the other, adjacent sealing disc segment is formed.
  • each sealing ring segment 20 spans the outer edge 10 of its associated sealing disk segment 14 in the circumferential direction.
  • Each sealing ring segment 20 has two opposite sealing ring segment longitudinal ends 21.
  • Each sealing ring segment longitudinal end 21 is folded in the axial direction, whereby at each sealing ring segment longitudinal end 21, a leg 22 is formed, with which the sealing ring segment longitudinal end 21 is formed L-shaped.
  • a curvature is provided with a radius of curvature 23, wherein at the outer edge 10 of the sealing disk segment 16, a correspondingly shaped recess 24 is made.
  • the legs 22 and the recesses 24 are arranged on the outer edge 10 of the sealing disc segments 16 so that the legs 22 in the axial direction away from the stop 18 and the stage 19 show.
  • the strength of the sealing disc segments 16 in the region of the stepped rebate 17 is not unduly impaired by the provision of the recess 24.

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

Description

Die Erfindung betrifft einen Axialturbomaschinenrotor mit einer Dichtscheibe.The invention relates to a Axialturbomaschinenrotor with a sealing washer.

Eine Axialturbomaschine, beispielsweise eine Gasturbine, weist eine Turbine auf, in der Heißgas entspannt wird. Zum Erzielen eines hohen thermischen Wirkungsgrads der Gasturbine ist die Temperatur des Heißgases am Eintritt in die Turbine als möglichst hoch zu wählen. Das maximal machbare Temperaturniveau des Heißgases ist durch Festigkeitsanforderungen an die Turbine begrenzt, die durch Konstruktion und Werkstoffwahl der Bauteile der Turbine definiert sind. Die Temperaturbelastung und die mechanische Beanspruchung der Bauteile gibt deren Lebensdauer vor, die aus Gründen der Sicherheit und Wirtschaftlichkeit oberhalb bestimmter Grenzen zu liegen hat.An axial turbomachine, for example a gas turbine, has a turbine in which hot gas is expanded. To achieve a high thermal efficiency of the gas turbine, the temperature of the hot gas at the inlet to the turbine is to be selected as high as possible. The maximum feasible temperature level of the hot gas is limited by turbine strength requirements defined by design and material selection of turbine components. The temperature load and the mechanical stress of the components dictates their service life, which has to be above certain limits for reasons of safety and economy.

Ein herkömmlicher Turbinenrotor weist eine Welle und daran rotationssymmetrisch angebrachte Scheiben auf, an deren Außenrand über dem Umfang nebeneinanderliegend eine Mehrzahl an Laufschaufeln befestigt ist. Die Laufschaufeln und die Scheiben sind mitunter die am stärksten beanspruchten Bauteile in der Turbine, wodurch in erster Linie von diesen Bauteilen Wartungszyklen der Gasturbine definiert sind. Zum Verlängern der Laufzeiten der Laufschaufeln und der Scheiben ist es bekannt, die Laufschaufeln und die Scheiben mit Kühlluft zu kühlen, die herkömmlich aus einem Verdichter der Gasturbine abgezapft wird. Insbesondere sind die Laufschaufeln aus einer filigranen Struktur hergestellt, die mit Kühlkanälen durchzogen ist, durch die die Kühlluft zum Kühlen der Laufschaufeln strömt. Die Kühlkanäle münden in den Laufschaufelfuß, an dem die Kühlkanäle mit der Kühlluft gespeist werden.A conventional turbine rotor has a shaft and discs mounted thereon in rotationally symmetrical manner, on the outer edge of which a plurality of rotor blades are fastened next to each other over the circumference. The blades and discs are sometimes the most stressed components in the turbine, which primarily defines servicing cycles of the gas turbine for these components. To extend the running times of the blades and disks, it is known to cool the blades and disks with cooling air conventionally tapped from a compressor of the gas turbine. In particular, the blades are made of a filigree structure that is traversed by cooling channels through which the cooling air flows to cool the blades. The cooling channels open into the blade root, where the cooling channels are fed with the cooling air.

Herkömmlich, wie beispielsweise bei der Ausgestaltung nach der US 2005/0265849 A1 , ist an der Scheibe im Bereich des Schaufelfußes ein Kühlluftzuströmkanal vorgesehen, der zwischen der Scheibe und einer dazu benachbarten ringförmigen Dichtscheibe gebildet ist, die radial am Schaufelfuß unmittelbar benachbart angeordnet ist. An die einstückige plattenförmigen Dichtscheibe sind Designanforderungen dahingehend gestellt, eine Leckage der Kühlluft möglichst gering zu halten und einen Eintritt von Heißgas in die Kühlkanäle zu unterbinden. Deswegen ist die Dichtscheibe an ihrem radial außenliegenden Rand mit einem Dichtring versehen, welcher unter Fliehkraft an den Unterseiten der Plattformen der Schaufeln zu anliegen gelangt.Conventionally, such as in the embodiment of the US 2005/0265849 A1 , is at the disc in the area of Blade foot provided a Kühlluftzuströmkanal formed between the disc and an adjacent thereto annular sealing disc, which is arranged radially adjacent to the blade root immediately adjacent. On the integral plate-shaped sealing disc design requirements are made to keep a leakage of the cooling air as low as possible and to prevent entry of hot gas into the cooling channels. Therefore, the sealing disc is provided at its radially outer edge with a sealing ring which comes to rest under centrifugal force on the undersides of the platforms of the blades.

Anstelle eines Dichtrings kann auch eine Dichtspitze vorgesehen sein. Jedoch stellt sich aufgrund von unterschiedlichen thermischen Ausdehnungen der Bauteile sowie der sich daraus ergebenden relativen Lage der Dichtscheibe und des Schaufelfußes zueinander beim Betrieb des Axialturbomaschinenrotors ein Verschleiß der Dichtspitzen ein. Dadurch ist die Dichtwirkung der Dichtspitzen verschlechtert, so dass an der Dichtscheibe Kühlluft in den Heißgasbereich der Turbine strömen kann. Außerdem besteht die Gefahr, dass an den Dichtspitzen vorbei Heißgas in die Kühlkanäle eindringen kann und dadurch die thermische Belastung der Laufschaufeln ansteigt, wodurch das Risiko eines vorzeitigen Versagens der Laufschaufeln erhöht ist.Instead of a sealing ring and a sealing tip can be provided. However, due to different thermal expansions of the components and the resulting relative position of the sealing disk and the blade root to each other during operation of the axial turbomachinery rotor wear of the sealing tips. As a result, the sealing effect of the sealing tips is deteriorated, so that cooling air can flow into the hot gas area of the turbine at the sealing disk. In addition, there is a risk that hot gas may enter the cooling channels past the sealing tips, thereby increasing the thermal load on the blades, thereby increasing the risk of premature failure of the blades.

Daneben ist aus der WO 2007/028703 A1 eine stirnseitige Abdichtung des Kühlluftzuströmkanals bekannt, bei der Anstelle einer einstückigen, ringförmigen Dichtscheibe eine Mehrzahl von Dichtscheibensegmenten vorgesehen sind, die gemeinschaftlich den Dichtring bilden. Unter Fliehkraft liegen diese an den Unterseiten der Plattformen der Laufschaufeln an. Eine separate Abdichtung mit Hilfe eines Dichtrings ist daher nicht erforderlich.Besides that is from the WO 2007/028703 A1 a front-side sealing of the Kühlluftzuströmkanals known in which instead of a one-piece, annular sealing disc a plurality of sealing disc segments are provided, which together form the sealing ring. Under centrifugal force they are applied to the undersides of the platforms of the blades. A separate seal using a sealing ring is therefore not required.

Aufgabe der Erfindung ist es, einen Axialturbomaschinenrotor zu schaffen, der eine hohe Lebensdauer hat.The object of the invention is to provide a Axialturbomaschinenrotor, which has a long service life.

Der erfindungsgemäße Axialturbomaschinenrotor weist einen um die Rotorachse rotationssymmetrisch ausgebildeten Rotorkörper, einen Laufschaufelkranz, der eine Mehrzahl an Laufschaufeln aufweist, die jeweils mit ihrem Schaufelfuß an dem Rotorkörper festgelegt sind, und eine um die Rotorachse rotationssymmetrisch ausgebildete Dichtscheibe auf, die mit ihrem Außenrand radial innerhalb benachbart an einem axial sich erstreckenden Vorsprung des Schaufelfußes angeordnet ist, sodass zwischen dem Schaufelfuß und der Dichtscheibe ein Hohlraum ausgebildet ist, wobei am Außenrand eine radial nach außen mündende Nut vorgesehen ist, in der ein Dichtring gelagert ist, der beim Betrieb des Rotors unter Einwirkung der Zentrifugalkraft radial nach außen in der Nut gleitbar ist, bis der Dichtring radial an der Innenseite des Vorsprungs anliegt und dadurch den Hohlraum am Schaufelfuß abdichtet.The axial turbomachinery rotor according to the invention has a rotor body rotationally symmetrical about the rotor axis, a rotor blade having a plurality of blades, which are each fixed with their blade root on the rotor body, and a rotationally symmetrical about the rotor axis formed sealing disc, the radially adjacent with its outer edge inside is arranged on an axially extending projection of the blade root, so that between the blade root and the sealing disc, a cavity is formed, wherein on the outer edge of a radially outwardly opening groove is provided, in which a sealing ring is mounted, which during operation of the rotor under the action of Centrifugal force is slidable radially outward in the groove until the sealing ring bears radially on the inside of the projection and thereby seals the cavity on the blade root.

Beim Betrieb des Axialturbomaschinenrotors stellt sich eine radiale Relativbewegung zwischen dem Vorsprung und dem Dichtring ein. Dadurch kann an dem Dichtring ein Verschleiß auftreten, der die Dichtwirkung des Dichtrings beeinträchtigen kann. Ist der Dichtring derart stark verschlissen, dass eine ausreichende Dichtwirkung nicht mehr gegeben ist, so kann der Dichtring, beispielsweise bei einem Wartungszyklus des Axialturbomaschinenrotors, an der Dichtscheibe ausgewechselt werden. Dadurch braucht vorteilhaft nicht die gesamte Dichtscheibe mit ausgetauscht zu werden, wodurch eine einfache und effektive Wartung des Axialturbomaschinenrotors erzielt ist. Dadurch, dass beim Betrieb des Axialturbomaschinenrotors der Dichtring durch die Zentrifugalkraft an den Vorsprung gedrückt wird, liegt der Dichtring über den gesamten Umfang vorgespannt an dem Vorsprung an. Somit ist der Kontakt zwischen dem Dichtring und dem Vorsprung gut abgedichtet, wodurch die Dichtwirkung zwischen dem Vorsprung und der Dichtscheibe hoch ist. Ist der Hohlraum beispielsweise ein Kanal zum Zuführen von Kühlluft zu dem Schaufelfuß, wie es beispielsweise in einer Turbine einer Gasturbine vorgesehen sein kann, so ist eine Leckage von Kühlluft an dem Dichtring gering. Dadurch ist die Kühlung der Laufschaufeln mit der Kühlluft effektiv, wodurch die Lebensdauer des Axialturbomaschinenrotors hoch ist.During operation of the axial turbomachinery rotor, a relative radial movement between the projection and the sealing ring occurs. This can cause wear on the sealing ring, which can impair the sealing effect of the sealing ring. If the sealing ring is so severely worn that a sufficient sealing effect is no longer present, then the sealing ring can be exchanged on the sealing disk, for example during a maintenance cycle of the axial-turbomachinery rotor. This advantageously does not need to be replaced with the entire sealing disc, whereby a simple and effective maintenance of the Axialturbomaschinenrotors is achieved. Due to the fact that, during operation of the axial turbomachinery rotor, the sealing ring is pressed against the projection by the centrifugal force, the sealing ring is biased against the projection over the entire circumference. Thus, the contact between the sealing ring and the projection is well sealed, whereby the sealing effect between the projection and the sealing disc is high. If the cavity is, for example, a channel for supplying cooling air to the blade root, as may for example be provided in a turbine of a gas turbine, leakage of cooling air at the sealing ring is small. This is the cooling of the blades with the cooling air effectively, whereby the life of the axial turbomachinery rotor is high.

Die Dichtscheibe umfasst eine Mehrzahl an Dichtscheibensegmenten, was die Montage von Laufschaufeln und Dichtscheibe nach dem Herstellen eines Rotors - geschweißt oder aus Rotorscheiben gestapelt - einer stationären Gasturbine erlaubt. Bevorzugt sind die Dichtscheibensegmente jeweils in Umfangsrichtung mit einem Stufenfalz miteinander gekoppelt. Dadurch ist die Montage der Dichtscheibe an den Rotorkörper einfach, wobei mit Hilfe des Stufenfalzes bei einem Versatz in Umfangsrichtung der einzelnen Dichtscheibensegmente zueinander ein Auseinanderklaffen der Dichtscheibensegmente unterbunden ist. Ferner ist der Dichtring von einer Mehrzahl an in Umfangsrichtung hintereinander angeordneten Dichtringsegmenten gebildet, die jeweils in die am Außenrand des ihnen zugeordneten Dichtscheibensegments eingelegt sind. Folglich stützen sich lediglich der Dichtring bzw. dessen Segmente an den Plattformen und Laufschaufeln ab, was die Dichtwirkung verbessert. Gleichzeitig stützen sich die Dichtscheibensegmente radial nunmehr an der Rotorscheibe unmittelbar ab. Dadurch kann die Fliehkraftbelastung jeder einzelnen Laufschaufelbefestigung reduziert werden, was die Lebensdauer der Rotorscheibe und der Laufschaufel erhöht.The gasket includes a plurality of gasket segments, which allows the assembly of blades and gasket after manufacture of a rotor - welded or stacked from rotor disks - allows a stationary gas turbine. The sealing disk segments are preferably coupled to each other in the circumferential direction with a stepped rebate. As a result, the assembly of the sealing disc to the rotor body is simple, wherein with the help of the stepped rebate with an offset in the circumferential direction of the individual sealing disc segments to each other a gaping apart of the sealing disc segments is prevented. Furthermore, the sealing ring is formed by a plurality of circumferentially successively arranged sealing ring segments, which are each inserted in the at the outer edge of their associated sealing disc segment. Consequently, only the sealing ring or its segments are supported on the platforms and blades, which improves the sealing effect. At the same time, the sealing disk segments are now supported radially on the rotor disk directly. Thereby, the centrifugal load of each blade attachment can be reduced, which increases the life of the rotor disc and the blade.

Die Dichtringsegmente weisen bevorzugt zwei einander abgewandte Längsenden auf, die jeweils von einem Umschlag gebildet sind, der mit einer an der Nut vorgesehenen Aussparung in Eingriff steht, so dass die Dichtringsegmente in Umfangsrichtung formschlüssig am Außenrand festgelegt sind. Dadurch ist vorteilhaft ein Verschieben des Dichtringsegments in Umfangsrichtung unterbunden. Die Umschläge sind bevorzugt als in Axialrichtung L-förmig umgeformte Schenkel ausgebildet. Dabei weist jeder der Schenkel bevorzugt einen Krümmungsradius auf, der mindestens größer als die Hälfte der Längserstreckung des betroffenen Schenkels ist. Dadurch ist erreicht, dass an den Längsenden das Dichtringsegment an dem Dichtscheibensegment gasdicht anliegt. Ferner ist es bevorzugt, dass die Schenkel in entgegengesetzte Richtungen zeigen, so dass das Dichtringsegment Z-förmig ausgebildet ist.The sealing ring segments preferably have two longitudinal ends facing away from each other, each of which is formed by an envelope, which is in engagement with a recess provided on the groove, so that the sealing ring segments are fixed in the circumferential direction in a form-fitting manner on the outer edge. This advantageously prevents displacement of the sealing ring segment in the circumferential direction. The envelopes are preferably designed as legs formed in the axial direction in an L-shaped manner. In this case, each of the legs preferably has a radius of curvature which is at least greater than half the longitudinal extension of the affected leg. It is thereby achieved that at the longitudinal ends of the sealing ring segment rests gas-tight on the sealing disc segment. Furthermore, it is preferred that the legs pointing in opposite directions, so that the sealing ring segment is Z-shaped.

Bevorzugtermaßen weist der Vorsprung eine radial nach innen mündende Nut auf, in die der Außenrand radial beweglich eingreift und an deren Grund der Dichtring anlegbar ist. Dadurch ist vorteilhaft der Außenrand der Dichtscheibe in der Nut des Vorsprungs untergebracht, wodurch schädliche Einflüsse, insbesondere eine mechanische und/oder thermische Belastung, auf den Dichtring reduziert sind. Außerdem ist ein Druckunterschied quer zum Dichtring herabgesetzt, sodass die Abdichtwirkung des Dichtrings hoch ist.Preferably, the projection has a radially inwardly opening groove into which the outer edge engages radially movable and at the bottom of the sealing ring can be applied. As a result, the outer edge of the sealing disc is advantageously accommodated in the groove of the projection, whereby harmful influences, in particular a mechanical and / or thermal stress, are reduced to the sealing ring. In addition, a pressure difference is reduced transversely to the sealing ring, so that the sealing effect of the sealing ring is high.

Bevorzugtermaßen sind die Dichtringsegmente als ein Band mit einem länglichen Querschnitt ausgebildet, dessen Längsseiten in Radialrichtung sich erstrecken und dessen außenliegende Kurzseite an dem Schaufelfuß anlegbar ist. Dadurch, dass die Längsseiten der Dichtringsegmente in Radialrichtung sich erstrecken, sind die Dichtringsegmente bei ihrer Radialbewegung in der Nut der Dichtringsegmente geführt. Somit ist ein Verdrehen und ein Verkippen der Dichtringsegmente in den Nuten der Dichtscheibensegmente unterbunden. Der Axialturbomaschinenrotor ist bevorzugt ein Axialturbinenrotor und die Laufschaufeln weisen bevorzugt Luftkanäle auf, die am Schaufelfuß in den Hohlraum münden, wobei der Hohlraum zur Kühlluftzufuhr und/oder Kühlluftabfuhr für die Kühlluftkanäle vorgesehen ist.Preferred dimensions of the sealing ring segments are formed as a band having an elongated cross section, the longitudinal sides extend in the radial direction and the outer short side can be applied to the blade root. Characterized in that the longitudinal sides of the sealing ring segments extend in the radial direction, the sealing ring segments are guided in their radial movement in the groove of the sealing ring segments. Thus, a twisting and tilting of the sealing ring segments is prevented in the grooves of the sealing disc segments. The axial turbomachine rotor is preferably an axial turbine rotor, and the rotor blades preferably have air ducts which open into the cavity at the blade root, wherein the cavity is provided for supplying cooling air and / or cooling air for the cooling air ducts.

Im Folgenden wird eine bevorzugte Ausführungsform des erfindungsgemäßen Axialturbinenrotors anhand der beigefügten schematischen Zeichnungen erläutert. Es zeigen:

FIG 1
einen Ausschnitt eines Längsschnitts der erfindungsgemäßen Ausführungsform des Axialturbinenrotors,
FIG 2
Detail A aus FIG 1,
FIG 3
Detail B aus FIG 1,
FIG 4
eine perspektivische Darstellung eines Dichtscheibensegments,
FIG 5
Detail D aus FIG 4 und
FIG 6
Detail C aus FIG 4.
In the following, a preferred embodiment of the axial turbine rotor according to the invention is explained with reference to the accompanying schematic drawings. Show it:
FIG. 1
a detail of a longitudinal section of the embodiment according to the invention of the axial turbine rotor,
FIG. 2
Detail A off FIG. 1 .
FIG. 3
Detail B off FIG. 1 .
FIG. 4
a perspective view of a sealing disk segment,
FIG. 5
Detail D off FIG. 4 and
FIG. 6
Detail C off FIG. 4 ,

Wie es aus FIG 1 bis 6 ersichtlich ist, weist ein Axialturbinenrotor 1 eine Mehrzahl an Laufschaufeln 2 auf, die über den Umfang des Axialturbinenrotors 1 aufgereiht sind und dadurch ein Laufschaufelgitter bilden. Der Axialturbinenrotor 1 weist ferner eine Scheibe 3 auf, auf der die Laufschaufeln 2 befestigt sind. Jede Laufschaufel 2 weist ein Schaufelblatt 4 auf, mit dem die Laufschaufel 2 aerodynamisch wirksam ist. Zum Befestigen der Laufschaufel 2 weist diese einen Schaufelfuß 5 auf, der formschlüssig in der Scheibe 3 gehalten ist, so dass von dem Schaufelfuß 5 die Laufschaufel 2 in Radialrichtung festgelegt ist. Zwischen dem Schaufelblatt 4 und dem Schaufelfuß 5 ist eine Fußplatte 7 der Laufschaufel 2 vorgesehen, die in Axialrichtung und in Umfangsrichtung sich erstreckt sowie an ihrer radial außenliegenden Seite aerodynamisch wirksam ist.Like it out 1 to 6 As can be seen, an axial turbine rotor 1 has a plurality of rotor blades 2, which are lined up over the circumference of the axial turbine rotor 1 and thereby form a blade grid. The axial turbine rotor 1 further comprises a disc 3, on which the rotor blades 2 are mounted. Each blade 2 has an airfoil 4 with which the blade 2 is aerodynamically effective. To attach the blade 2, this has a blade root 5, which is held in a form-fitting manner in the disc 3, so that the blade 2 is fixed in the radial direction of the blade root 5. Between the blade 4 and the blade root 5, a base plate 7 of the blade 2 is provided which extends in the axial direction and in the circumferential direction and is aerodynamically effective on its radially outer side.

Die Scheibe 2 ist stirnseitig mit einer senkrecht zur Achse des Axialturbinenrotors verlaufenden Fläche begrenzt. Axial im Abstand zu dieser Fläche ist eine Dichtscheibe 7 angeordnet, wodurch zwischen der Dichtscheibe 7 und der Scheibe 3 ein Hohlraum ausgebildet ist. Dadurch ist von der Dichtscheibe 7 der Hohlraum von der Heißgasseite 8 des Axialturbinenrotors begrenzt. Der Hohlraum ist ein Kühlluftzuführkanal 9, der zur Kühlluftzufuhr von Kühlluft zu dem Schaufelfuß 5 vorgesehen ist. Ein in Bezug auf die mittlere Wandstärke der Dichtscheibe 7 aufgedickter Innenrand 22 der Dichtscheibe 7 ist mit der Scheibe 3 radial verhakt, wodurch im Betrieb die Dichtscheibe 7 unmittelbar von der Scheibe 3 radial gehalten wird.The disc 2 is frontally limited with a plane perpendicular to the axis of the axial turbine rotor surface. Axially spaced from this surface, a sealing disc 7 is arranged, whereby between the sealing disc 7 and the disc 3, a cavity is formed. As a result, the cavity of the hot gas side 8 of the axial turbine rotor is limited by the sealing disk 7. The cavity is a Kühlluftzuführkanal 9, which is provided for the cooling air supply of cooling air to the blade root 5. An inner edge 22, which is thickened with respect to the average wall thickness of the sealing disk 7, of the sealing disk 7 is radially hooked to the disk 3, as a result of which, in operation, the Seal 7 is held radially from the disc 3 directly.

Der Außenrand 10 der Dichtscheibe 7 ist radial benachbart zur radial innenliegenden Seite der Fußplatte 6 angeordnet, wobei der Außenrand 10 der Dichtscheibe 7 in eine in der radial innenliegenden Seite der Fußplatte 6 vorgesehenen, umlaufenden Nut 11 eingreift. Im Außenrand 10 der Dichtscheibe 7 ist eine umlaufende Nut 12 vorgesehen, die radial nach außen in die Nut 11 der Fußplatte 6 mündet. Der Außenrand 10 der Dichtscheibe 7 ist radial im Abstand vom Grund der Nut 11 der Fußplatte 6 angeordnet, so dass ein Radialspiel 13 vorgesehen ist.The outer edge 10 of the sealing disc 7 is arranged radially adjacent to the radially inner side of the base plate 6, wherein the outer edge 10 of the sealing disc 7 engages in a provided in the radially inner side of the base plate 6, circumferential groove 11. In the outer edge 10 of the sealing disc 7, a circumferential groove 12 is provided, which opens radially outward into the groove 11 of the base plate 6. The outer edge 10 of the sealing disc 7 is arranged radially at a distance from the bottom of the groove 11 of the base plate 6, so that a radial play 13 is provided.

In der Nut 12 der Dichtscheibe 7 ist ein Dichtring 14 eingelegt, der einen Querschnitt hat, der in Radialrichtung länglich bzw. rechteckig ausgebildet ist. Die Nut 12 in der Dichtscheibe 7 ist in der Dichtscheibe 7 derart tief vorgesehen, dass der Dichtring 14 in der Nut 12 bündig mit dem Außenrand 10 der Dichtscheibe 7 versenkbar ist.In the groove 12 of the sealing washer 7, a sealing ring 14 is inserted, which has a cross-section which is elongated or rectangular in the radial direction. The groove 12 in the sealing disc 7 is provided in the sealing disc 7 so deep that the sealing ring 14 in the groove 12 is flush with the outer edge 10 of the sealing disc 7.

Beim Betrieb des Axialturbinenrotors 1 wirkt auf den Dichtring 14 eine Zentrifugalkraft, die zu einer Radialbewegung 15 des Dichtrings führt. Die Radialbewegung 15 wird von dem Dichtring 14 vollzogen, bis der Dichtring 14 an dem Grund der Nut 11 in der Fußplatte 6 anliegt. Das Radialspiel 13 ist auf die Radialerstreckung des Dichtrings 14 derart eingestellt, dass beim Anliegen des Dichtrings 14 am Grund der Nut 11 der Fußplatte 6 der Dichtring 14 dennoch mit der Nut 12 im Außenrand 10 der Dichtscheibe 7 in Eingriff steht.During operation of the axial turbine rotor 1 acts on the sealing ring 14, a centrifugal force, which leads to a radial movement 15 of the sealing ring. The radial movement 15 is completed by the sealing ring 14 until the sealing ring 14 rests against the bottom of the groove 11 in the base plate 6. The radial play 13 is adjusted to the radial extent of the sealing ring 14 such that when concerns of the sealing ring 14 at the bottom of the groove 11 of the base plate 6 of the sealing ring 14 is still engaged with the groove 12 in the outer edge 10 of the sealing washer 7.

Die Dichtscheibe 7 ist von einer Mehrzahl an Dichtscheibensegmenten 16 gebildet, die über dem Umfang nebeneinanderliegend aufgereiht sind. An ihren Rändern, an denen die Dichtscheibensegmente 16 miteinander benachbart angeordnet sind, ist jeweils ein Stufenfalz 17 ausgebildet, der von einem Anschlag 18 des einen Dichtscheibensegments 16 und einer mit dem Anschlag 18 korrespondierenden Stufe 19 des anderen, benachbarten Dichtscheibensegments gebildet ist.The sealing disc 7 is formed by a plurality of sealing disc segments 16, which are lined up next to each other over the circumference. At their edges at which the sealing disk segments 16 are arranged adjacent to each other, a stepped fold 17 is formed in each case by a stop 18 of a sealing disk segment 16 and with a the stop 18 corresponding step 19 of the other, adjacent sealing disc segment is formed.

Analog zur Aufteilung der Dichtscheibe 7 in die Dichtscheibensegmente 16 ist der Dichtring 14 in Dichtringsegmente 20 unterteilt, wobei jedes Dichtringsegment 20 den Außenrand 10 des ihm zugeordneten Dichtscheibensegments 14 in Umfangsrichtung überspannt. Jedes Dichtringsegment 20 weist zwei einander abgewandte Dichtringsegmentlängsenden 21 auf. Jedes Dichtringsegmentlängsende 21 ist in Axialrichtung umgelegt, wodurch an jedem Dichtringsegmentlängsende 21 ein Schenkel 22 geformt ist, mit dem das Dichtringsegmentlängsende 21 L-förmig ausgebildet ist. An jedem Schenkel 22 ist eine Krümmung mit einem Krümmungsradius 23 vorgesehen, wobei am Außenrand 10 des Dichtscheibensegments 16 eine entsprechend geformte Aussparung 24 gefertigt ist. Die Schenkel 22 und die Aussparungen 24 sind an dem Außenrand 10 der Dichtscheibensegmente 16 so angeordnet, dass die Schenkel 22 in Axialrichtung weg von dem Anschlag 18 bzw. der Stufe 19 zeigen. Somit ist die Festigkeit der Dichtscheibensegmente 16 im Bereich des Stufenfalzes 17 durch das Vorsehen der Aussparung 24 nicht übermäßig beeinträchtigt.Analogous to the division of the sealing disk 7 in the sealing disk segments 16 of the sealing ring 14 is divided into sealing ring segments 20, wherein each sealing ring segment 20 spans the outer edge 10 of its associated sealing disk segment 14 in the circumferential direction. Each sealing ring segment 20 has two opposite sealing ring segment longitudinal ends 21. Each sealing ring segment longitudinal end 21 is folded in the axial direction, whereby at each sealing ring segment longitudinal end 21, a leg 22 is formed, with which the sealing ring segment longitudinal end 21 is formed L-shaped. On each leg 22, a curvature is provided with a radius of curvature 23, wherein at the outer edge 10 of the sealing disk segment 16, a correspondingly shaped recess 24 is made. The legs 22 and the recesses 24 are arranged on the outer edge 10 of the sealing disc segments 16 so that the legs 22 in the axial direction away from the stop 18 and the stage 19 show. Thus, the strength of the sealing disc segments 16 in the region of the stepped rebate 17 is not unduly impaired by the provision of the recess 24.

Claims (9)

  1. Axial turbomachine rotor having a rotor body (3), which is rotationally symmetrically formed around the rotor axis,
    a rotor blade ring, which has a multiplicity of rotor blades (2) which are fastened in each case by their blade root (5) on the rotor body (3),
    and a sealing plate (7), which is rotationally symmetrically formed around the rotor axis and which by its outer edge (10) is arranged radially inside and adjacently on an axially extending projection (6) of the blade root (5) so that between the blade root (5) and the sealing plate (7) a cavity (9) is formed,
    wherein provision is made on the outer edge (10) for a radially outwardly opening groove (12) in which is supported a sealing ring (14) which during operation of the rotor (1) can slide radially outwards in the groove (12) by action of centrifugal force (15) until the sealing ring (14) bears radially against the inner side of the projection (6) and as a result seals the cavity (9) at the blade root (5), characterized in that
    the sealing plate (7) is formed from a multiplicity of sealing plate segments (16) and the sealing ring (14) is formed from a multiplicity of sealing ring segments (20) which are arranged in series in the circumferential direction and are radially supported in each case directly on the rotor body (3),
    wherein the respective sealing ring segments (20) are inserted into those on the outer edge (10) of the sealing plate segment (16) which is associated with them.
  2. Axial turbomachine rotor according to Claim 1,
    wherein the sealing ring segments (20) have two long ends (21), facing away from each other, which are formed in each case by a bend (22) which engages with a cutout (24) provided in the groove (12) so that the sealing ring segments (20) are fastened in a form-fitting manner on the outer edge (10) in the circumferential direction.
  3. Axial turbomachine rotor according to Claim 1 or 2,
    wherein the projection has a radially inwards opening groove (11) in which the outer edge (10) engages in a radially movable manner and against the base of which the sealing ring (14) can bear.
  4. Axial turbomachine rotor according to Claim 1, 2 or 3,
    wherein the sealing plate segments (16) are interconnected in the circumferential direction in each case by a recessed edge (17).
  5. Axial turbomachine rotor according to one of Claims 1 to 4,
    wherein the bends are designed as legs (22) which are of an L-shaped form in the axial direction.
  6. Axial turbomachine rotor according to Claim 5,
    wherein each of the legs (22) has a curvature radius (23) which is at least greater than half the longitudinal extent of the leg (22) in question.
  7. Axial turbomachine rotor according to Claim 5 or 6,
    wherein the legs point (22) in opposite directions so that the sealing ring segment (20) is of a Z-shaped form.
  8. Axial turbomachine rotor according to one of Claims 1 to 7,
    wherein the sealing ring segments (20) are designed as a band with an oblong, preferably rectangular, cross section, the long sides of which extend in the radial direction and the outer short side of which can bear against the blade root (5).
  9. Axial turbomachine rotor according to one of Claims 1 to 8,
    wherein the axial turbomachine rotor is an axial turbine (1) rotor and the rotor blades (2) have cooling air passages which open into the cavity (9) at the blade root (5), wherein the cavity (9) is provided for cooling air feed and/or cooling air discharge for the cooling air passages.
EP10715749.7A 2009-03-31 2010-03-26 Axial turbo engine rotor with sealing disc Not-in-force EP2414641B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10715749.7A EP2414641B1 (en) 2009-03-31 2010-03-26 Axial turbo engine rotor with sealing disc
PL10715749T PL2414641T3 (en) 2009-03-31 2010-03-26 Axial turbo engine rotor with sealing disc

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09004781A EP2239419A1 (en) 2009-03-31 2009-03-31 Axial turbo engine rotor with sealing disc
EP10715749.7A EP2414641B1 (en) 2009-03-31 2010-03-26 Axial turbo engine rotor with sealing disc
PCT/EP2010/054001 WO2010112422A1 (en) 2009-03-31 2010-03-26 Axial turbomachine rotor having sealing disc

Publications (2)

Publication Number Publication Date
EP2414641A1 EP2414641A1 (en) 2012-02-08
EP2414641B1 true EP2414641B1 (en) 2013-07-03

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EP09004781A Withdrawn EP2239419A1 (en) 2009-03-31 2009-03-31 Axial turbo engine rotor with sealing disc
EP10715749.7A Not-in-force EP2414641B1 (en) 2009-03-31 2010-03-26 Axial turbo engine rotor with sealing disc

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Application Number Title Priority Date Filing Date
EP09004781A Withdrawn EP2239419A1 (en) 2009-03-31 2009-03-31 Axial turbo engine rotor with sealing disc

Country Status (7)

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US (1) US8920121B2 (en)
EP (2) EP2239419A1 (en)
JP (1) JP5324700B2 (en)
CN (1) CN102378850B (en)
ES (1) ES2426156T3 (en)
PL (1) PL2414641T3 (en)
WO (1) WO2010112422A1 (en)

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EP2957725A1 (en) 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor with sealing sheets
CN105658912A (en) * 2013-09-25 2016-06-08 斯奈克玛 Rotary assembly for a turbomachine
EP3564489A1 (en) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor with for centrifugal forces optimized contact surfaces

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CN105658912A (en) * 2013-09-25 2016-06-08 斯奈克玛 Rotary assembly for a turbomachine
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WO2015193033A1 (en) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor having sealing plates
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US11319824B2 (en) 2018-05-03 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with centrifugally optimized contact faces

Also Published As

Publication number Publication date
PL2414641T3 (en) 2013-12-31
WO2010112422A1 (en) 2010-10-07
US8920121B2 (en) 2014-12-30
EP2239419A1 (en) 2010-10-13
ES2426156T3 (en) 2013-10-21
JP2012522169A (en) 2012-09-20
JP5324700B2 (en) 2013-10-23
CN102378850A (en) 2012-03-14
EP2414641A1 (en) 2012-02-08
US20120034087A1 (en) 2012-02-09
CN102378850B (en) 2014-07-16

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