EP2394028B1 - Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine and the use thereof - Google Patents

Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine and the use thereof Download PDF

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Publication number
EP2394028B1
EP2394028B1 EP10710168.5A EP10710168A EP2394028B1 EP 2394028 B1 EP2394028 B1 EP 2394028B1 EP 10710168 A EP10710168 A EP 10710168A EP 2394028 B1 EP2394028 B1 EP 2394028B1
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EP
European Patent Office
Prior art keywords
blade
sealing apparatus
rotor
bulkheads
sealing
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EP10710168.5A
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German (de)
French (fr)
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EP2394028A1 (en
Inventor
Manfred Feldmann
Markus Uecker
Benedikt Heidenreich
Dieter Freno
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP2394028A1 publication Critical patent/EP2394028A1/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
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to a sealing device according to the preamble of claim 1, as in the document DE 37 43 253 A1 described.
  • a turbine stage in which the blade roots of the individual blades are equipped with a double-walled bulkhead. Furthermore, the individual blades are held in the axial direction by further sealing plates, which simultaneously seal the Schaufelfzißabites, wherein the further Abdichtplatten are used both at a designated edge of the inner rotor and at one edge of the blade root. Since the sealing plates are also provided as attachment of the blades, they experience high mechanical stresses in both the axial and in the radial direction, which can lead to failure of the sealing properties between the plates as the life progresses.
  • the GB 1 295 003 discloses a rotor for a turbomachine having a plurality of blades with blade roots which are positioned at a regular distance by engagement of lateral bimetallic plates on the periphery of a rotor.
  • the rotor and the blades to be mounted on a U-shaped edge, in which the bimetallic plates are latched.
  • a turbine blade inner end fastener which is attached to the inner rotor.
  • the blade inner ends have parts with a hook-like configuration in the region of the blade root, which are received in grooves formed by flanges and arranged at an axial distance along the inner rotor.
  • the chopping parts are secured by a locking device by precisely fitting engagement with the grooves, so that radial and axial movements are prevented relative to the rotor housing.
  • the blades are arranged one after the other on the rotor, so that open slots can be provided between the individual blades and their attachments.
  • extremely small tolerances must be maintained both for the assembly and because of the consideration of the thermal expansion of the components. Pressure losses are therefore not completely ruled out and, moreover, high mechanical stresses on the fastening devices occur, which result in a reduced service life and in a loss of the sealing properties as the service life progresses.
  • a seal assembly for the rotor of a turbomachine for sealing between a blade root and a laterally disposed heat shield is known.
  • T-shaped sealing elements in designated slots of the blade root and the heat shield added.
  • the seal assembly uses sealing elements, which do not serve as fasteners in contrast to the aforementioned prior art.
  • the mechanical loads on the sealing elements are reduced, and the sealing properties are no longer so drastically dependent on the service life of the components.
  • this method is very time consuming and expensive both in component manufacture and connected during assembly of the blades on the inner rotor. Furthermore, massive and thus heavy components are necessary because of the slots.
  • the invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for sealing the flow cross-section of a rotor. Furthermore, a solution is to be provided which allows a simple and cost-effective production of the sealing devices for sealing the flow cross section of a rotor, whereby the assembly time of the individual blades is reduced on the rotor and the performance of the turbomachine is increased. At the same time, the mechanical stresses to which the ends of the bulkhead walls are exposed at the blade root should also be reduced and a secure, permanent sealing of the flow cross-section and of a rotor of a turbomachine should be made possible.
  • the sealing device according to the invention for sealing the rotor of a turbomachine is located on the blade shank of the rotor blades of a Rotor stage of an axial flow machine, wherein a plurality of blades are arranged in the circumferential direction side by side on the rotor.
  • the sealing device has on the blade shank in the axial direction to the front and rear protruding bottom plates and in the radial direction along the blade shank extending bulkheads, which form a double-walled seal in the axial direction.
  • the transition cross section from the bottom plates to the bulkheads is preferably rounded, or parabolic.
  • at least one of the two bulkhead walls is offset inwardly with respect to the blade root edge at the level of an identical radial distance from the rotor axis in the direction of the radial longitudinal axis of the blade shaft.
  • the sealing device also consists of a single solid component.
  • two bulkhead walls which are formed in the radial direction and extend from the protruding bottom plates in the direction of the rotor axis, have a total parabolic shape.
  • the separately produced components can be connected to one another by welding, for example, and the sealing device can be coated with a friction-reducing coating.
  • a sealing device which consists of two interconnected T-pieces and is connected to a blade shank of a blade, a force acts on the outwardly facing plates in a mechanical stress peak in the region of the two T-joints at the base of the blade out.
  • the forces that are exerted, inter alia, on the axially protruding bottom plates of the blades result by their overall shape and by the position of the sealing device in a homogeneous distribution of mechanical stresses in the region of the blade airfoil.
  • the wall thickness of the bottom plates is greater than the wall thickness of the radial bulkhead walls.
  • At least one of the axially protruding bottom plates and the blade foot disc has different inclinations.
  • the sealing device according to the invention is thus applicable in a variety of different types of engines. Different inclinations are further provided as adjustment parameters for predetermined expansion slots.
  • the paddle table opens in at least one of the protruding bottom plates L-shaped. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the blade shaft and the axially protruding bottom plates are different.
  • the paddle table opens into the two protruding bottom plates U-shaped. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the two axially protruding bottom plates is symmetrical.
  • the Schaufelfußtisch is formed straight, inclined or curved.
  • a straight configuration of the blade root table is particularly advantageous if the bottom plates protruding in the axial direction are likewise formed straight and in the same plane, and in particular if the turbomachine has a constant flow cross section.
  • An inclined configuration of the blade root table is particularly advantageous if the bottom plates projecting in the axial direction have different inclinations and / or if the flow cross section of the Turbomachine changes.
  • a domed configuration of the blade root table is particularly advantageous for optimally reinforcing the joints in particular configurations of the floor panels and / or the bulkhead walls.
  • the blade and the sealing device are integrally formed. This has the advantage that no mounting slots, neither on the blade shank nor on the rotor stage with extremely small tolerances, for the engagement of lateral sealing plates, which would also have to be produced with extremely low tolerances, are necessary. Another advantage is that only a single component at the rotor stage must be arranged during assembly in order to provide a double-walled seal in the circumferential direction.
  • the blade and the sealing device form two separate components, which are arranged against one another.
  • the separately produced components can be connected to one another by welding, for example, and the sealing device can be coated with a friction-reducing coating.
  • the device according to the invention for sealing the flow cross-section of a rotor is used both in turbines and in compressors of gas turbine plants and generally in turbomachines.
  • Fig. 1 shows a part of a rotor, on which a blade is arranged, which contains a preferred embodiment of the invention
  • the laterally indicated adjacent to the rotor shaft components 11 have rounded corners and define respective expansion slots 3 for receiving the axially protruding bottom plate 6 of the sealing element 1.
  • Each sealing element has a Schaufelfußtisch 8 with two axially projecting bottom plates 6 and two to the center directed to the rotor 5 and connected to the axially projecting bottom plate 6 connected parabolic partition wall 7, 7 '.
  • the sealing elements 1 can be regarded as segments of a ring in which the blade root tables 8 are arranged radially, and in which the bulkheads 7,7 'define a double-walled sealing ring disc.
  • the sealing ring disc segments are strongly compressed so that no leakage flow can form between the adjacent ends of the individual segments. At the same time, enough space for the expansion caused by the operating temperature in the circumferential direction of the sealing members 1 is left.
  • each axially projecting bottom plate 6 is housed in a radially and extending in the circumferential direction of expansion slot 3, which is formed by arranged on the rotor shaft 5 laterally arranged components 11. This already reduces the leakage flow due to the reduced open area.
  • the device has a sealing device 2, which contains two parabolic trained bulkheads 7, 7 ', which are offset with respect to the blade root edge 14, 14' in the axial direction to each other.
  • a sealing device 2 which contains two parabolic trained bulkheads 7, 7 ', which are offset with respect to the blade root edge 14, 14' in the axial direction to each other.
  • Fig. 2 shows a longitudinal section through the sealing device 2, according to a first preferred embodiment of the invention.
  • the axially protruding bottom plates 6 and the Schaufelfußtisch 8 have the same inclination and are in the same plane.
  • the bulkheads 7, 7 ' extending downwardly and radially form with the protruding bottom plates 6 and with the blade root table 8 rounded connections and run in the direction of the rotor axis.
  • the wall thickness of the blade root table 8, the bottom plates 6 and the bulkheads 7, 7 ' is the same.
  • the sealing device 2 has two differently configured bulkheads 7, 7 '.
  • the right in the plane of the bulkhead wall 7 ' is L-shaped and runs parallel to the longitudinal axis 13 of the blade shank 4, while the left in the drawing plane bulkhead 7 in the direction of the longitudinal axis 13 of the blade shank 4 straight and offset with respect to the Schaufelfußrandes 14 inside is.
  • the offset 12 of the left in the plane of the bulkhead wall 7 with respect to the Schaufelfußrandes 14 in the direction of the radial longitudinal axis 13 of the blade shank 4 are significantly reduced.
  • Fig. 3 shows a longitudinal section through the sealing device 2, according to a second preferred embodiment of the invention.
  • the bottom plates 6 protruding in the axial direction and the blade foot table 8 have different Inclinations and lie on different levels.
  • the parabolic bulkheads 7, 7 'extending after the rotor center and in the radial direction form parabolic connections with the protruding bottom plates 6 and with the blade root table 8 and extend parabolically in the direction of the rotor axis and subsequently parallel to one another.
  • the Schaufelfußtisch 8 also opens here L-shaped in the drawing plane right projecting bottom plate 6.
  • the wall thickness of the blade root table 8 and the bottom plates 6 is also greater than the wall thickness of the bulkheads 7, 7 '.
  • the right in the plane of the bulkhead wall 7 ' is also in the direction of the longitudinal axis 13 of the blade shank 4 first parabolic and then straight and offset with respect to the Schaufelfußrandes 14' to the inside. Due to the offset 12 of the right in the plane of the bulkhead wall 7 'with respect to the Schaufelfußrandes 14' in the direction of the radial longitudinal axis 13 of the blade shank 4, the voltage peaks at the ends of the bulkheads 7, 7 'on the blade shank 4 are significantly reduced, as a result, the power flow of the introduced Forces is optimized.
  • Fig. 4 shows a longitudinal section through the sealing device 2, according to a third preferred embodiment of the invention.
  • the bottom plates 6 projecting in the axial direction and the blade foot table 8 have the same inclination, they are located at different levels.
  • the bulkheads 7, 7 ' which extend after the rotor center and in the radial direction and parabolically taper, form rounded connections with the protruding bottom plates 6 and with the blade root table 8 and run parabolically in the direction of the rotor axis.
  • the wall thickness of the bulkheads 7, 7 ' greater than the wall thickness of the blade root table 8 and the bottom plates 6.
  • the right in the drawing plane bulkhead 7' is also in the direction of the longitudinal axis 13 of the blade shaft 4, ie in the radial direction with respect on the axial flow machine, first parabolic and then rectilinear. In this case, approximately the last third is formed as a straight line in the present embodiment, while the first two thirds of the blade shank 4 form approximately a parabola. With respect to the Schaufelfußrandes 14 'is in the plane of the drawing right bulkhead 7 'offset inside.

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

Description

Die vorliegende Erfindung betrifft eine Abdichtvorrichtung nach dem Oberbegriff des Anspruchs 1, wie in der Druckschrift DE 37 43 253 A1 beschrieben.The present invention relates to a sealing device according to the preamble of claim 1, as in the document DE 37 43 253 A1 described.

Derartige Abdichtvorrichtungen sind aus dem Stand der Technik bekannt.Such sealing devices are known from the prior art.

In der WO 097 016 95 ist beispielsweise eine Turbinenstufe offenbart, an der die Schaufelfüße der einzelnen Schaufeln mit einer doppelwandigen Schottwand ausgerüstet sind. Ferner werden die einzelnen Schaufeln in axialer Richtung durch weiteren Abdichtplatten gehalten, welche gleichzeitlich den Schaufelfzißabschnitt abdichten, wobei die weitere Abdichtplatten sowohl an einer dafür vorgesehenen Kante des inneren Rotors als auch an einer Kante des Schaufelfußes eingesetzt werden. Da die Abdichtplatten ebenfalls als Befestigung der Schaufeln vorgesehen sind, erfahren sie sowohl in axialer als auch in radialer Richtung hohe mechanische Beanspruchungen, die mit fortschreitender Lebensdauer zum Versagen der Abdichteigenschaften zwischen den Platten führen kann. Ferner entstehen an den Enden der Schottwände am Schaufelfuß hohe Spannungsspitzen durch die Torsion der Schaufel, Fliehkräfte und weitere Torsionsspannungen, die durch Gaskräfte verursacht werden. Diese Spannungsspitzen können die Ursache für Materialermüdung oder gar Bauteilversagen sein, weswegen die Schottwände an dieser Stelle besonders stabil und der Schaufelfuß in axialer Richtung besonders lang ausgebildet sein müssen.In the WO 097 016 95 For example, a turbine stage is disclosed in which the blade roots of the individual blades are equipped with a double-walled bulkhead. Furthermore, the individual blades are held in the axial direction by further sealing plates, which simultaneously seal the Schaufelfzißabschnitt, wherein the further Abdichtplatten are used both at a designated edge of the inner rotor and at one edge of the blade root. Since the sealing plates are also provided as attachment of the blades, they experience high mechanical stresses in both the axial and in the radial direction, which can lead to failure of the sealing properties between the plates as the life progresses. Furthermore, at the ends of the bulkhead walls on the blade root, high voltage peaks occur due to the torsion of the blade, centrifugal forces and other torsional stresses caused by gas forces. These voltage peaks can be the cause of material fatigue or even component failure, which is why the bulkheads at this point must be particularly stable and the blade root in the axial direction must be made particularly long.

Die GB 1 295 003 offenbart einen Rotor für eine Strömungsmaschine, welcher eine Vielzahl von Schaufeln mit Schaufelfüßen aufweist, die in einem regelmäßigen Abstand durch Einklinken von seitlichen bimetallischen Platten an der Peripherie eines Rotors positioniert werden. Dabei weisen der Rotor sowie die zu montierenden Schaufeln eine U-förmige Kante auf, in der die bimetallischen Platten eingeklinkt werden. Durch diese Konstruktion wird einerseits sichergestellt, dass die an der Peripherie des Rotors montierten Schaufeln in ihrer Position sicher gehalten werden und anderseits dass die Druckverluste im Strömungsquerschnitt reduziert werden. Da jedoch für eine Rotorstufe mehrere Platten notwendig sind, sind Druckverluste nicht vollständig auszuschließen und die Montage der einzelnen Bauteile ist außerdem zeitaufwändig. Außerdem müssen äußerst geringe Toleranzen der Bauteile eingehalten werden und die durch die Betriebstemperatur verursachte Expansion der Bauteile dabei berücksichtigt werden. Aufgrund des Einflusses hoher Temperaturen und Zentrifugalkräften beim Betrieb kann sich ferner die relative Position der Schlitze ändern, was zur Plattenscherung oder sogar Plattenbruch führen kann. Weiterhin kann dadurch ein Verlust der Dichteigenschaften resultieren.The GB 1 295 003 discloses a rotor for a turbomachine having a plurality of blades with blade roots which are positioned at a regular distance by engagement of lateral bimetallic plates on the periphery of a rotor. In this case, the rotor and the blades to be mounted on a U-shaped edge, in which the bimetallic plates are latched. By this construction, on the one hand, it ensures that the at the periphery of the rotor mounted blades are held securely in position and on the other hand that the pressure losses are reduced in the flow cross-section. However, since several plates are necessary for a rotor stage, pressure losses can not be completely ruled out and the assembly of the individual components is also time-consuming. In addition, extremely low tolerances of the components must be complied with and the expansion of the components caused by the operating temperature must be taken into account. Further, due to the influence of high temperatures and centrifugal forces during operation, the relative position of the slots may change, which may result in plate shearing or even plate breakage. Furthermore, this can result in a loss of sealing properties.

Aus der DE 4 110 214 A1 ist eine Befestigungsvorrichtung für Innenenden von Turbinenlaufschaufeln bekannt, welche am inneren Rotor befestigt werden. Die Schaufelinnenenden weisen Teile mit einer hakenartigen Konfiguration im Bereich des Schaufelfußes auf, welche in durch Flansche gebildete und in axialem Abstand längs des inneren Rotors angeordneten Nuten aufgenommen werden. Dabei werden die hackenartigen Teile durch eine Verriegelungsvorrichtung durch passgenauen Eingriff mit den Nuten abgesichert, so dass radiale und axiale Bewegungen relativ zum Rotorgehäuse verhindert werden. Auch hier sind die Schaufeln am Rotor nacheinander angeordnet, so dass zwischen den einzelnen Schaufeln und deren Befestigungen offene Schlitze entsehen können. Insbesondere müssen sowohl für die Montage als auch wegen der Berücksichtigung der thermischen Expansion der Bauteile auch hier äußerst geringe Toleranzen eingehalten werden. Druckverluste sind daher nicht vollständig auszuschließen und außerdem treten hohe mechanischen Beanspruchungen an den Befestigungsvorrichtungen auf, welche in einer reduzierten Lebensdauer und in einem Verlust der Abdichteigenschaften mit fortschreitender Benutzungsdauer resultieren.From the DE 4 110 214 A1 For example, there is known a turbine blade inner end fastener which is attached to the inner rotor. The blade inner ends have parts with a hook-like configuration in the region of the blade root, which are received in grooves formed by flanges and arranged at an axial distance along the inner rotor. In this case, the chopping parts are secured by a locking device by precisely fitting engagement with the grooves, so that radial and axial movements are prevented relative to the rotor housing. Again, the blades are arranged one after the other on the rotor, so that open slots can be provided between the individual blades and their attachments. In particular, extremely small tolerances must be maintained both for the assembly and because of the consideration of the thermal expansion of the components. Pressure losses are therefore not completely ruled out and, moreover, high mechanical stresses on the fastening devices occur, which result in a reduced service life and in a loss of the sealing properties as the service life progresses.

Aus der WO 031 046 17 ist eine Dichtungsanordnung für den Rotor einer Turbomaschine zum Abdichten zwischen einem Schaufelfuß und einer seitlich angeordneten Wärmeabschirmung bekannt. Dabei werden T-förmige Abdichtelemente in dafür vorgesehene Schlitze des Schaufelfußes und der Wärmeabschirmung aufgenommen. Die Dichtungsanordnung verwendet dabei Abdichtelemente, die im Gegensatz zum vorher genannten Stand der Technik nicht gleichzeitig als Befestigungselemente dienen. Dadurch sind die mechanischen Belastungen an den Abdichtelementen reduziert, und die Abdichteigenschaften nicht mehr so drastisch von der Nutzungsdauer der Bauteile abhängig. Durch die Verwendung von einzelnen Abdichtelementen, die separat hergestellt werden müssen, als auch durch die Notwendigkeit Schlitze sowohl am Schaufelfuß jeder einzelnen Schaufel als auch an der Wärmabschirmung bereit zu stellen, ist diese Methode jedoch sehr zeitaufwändig und mit hohen Kosten sowohl bei der Bauteilherstellung als auch bei der Montage der Schaufeln am inneren Rotor verbunden. Ferner sind wegen der Schlitze massive und damit schwere Bauteile notwendig.From the WO 031 046 17 For example, a seal assembly for the rotor of a turbomachine for sealing between a blade root and a laterally disposed heat shield is known. In this case, T-shaped sealing elements in designated slots of the blade root and the heat shield added. The seal assembly uses sealing elements, which do not serve as fasteners in contrast to the aforementioned prior art. As a result, the mechanical loads on the sealing elements are reduced, and the sealing properties are no longer so drastically dependent on the service life of the components. However, by using individual sealing elements which need to be manufactured separately, as well as by the need to provide slots on both the blade root of each individual blade and the heat shield, this method is very time consuming and expensive both in component manufacture and connected during assembly of the blades on the inner rotor. Furthermore, massive and thus heavy components are necessary because of the slots.

Der Erfindung liegt daher die Aufgabe zugrunde, die Nachteile der bekannten Lösungen des Standes der Technik zu vermeiden und eine verbesserte Lösung zum Abdichten des Strömungsquerschnitts eines Rotors zur Verfügung zu stellen. Ferner soll eine Lösung bereitgestellt werden, welche eine einfache und kostengünstige Herstellung der Abdichtvorrichtungen zum Abdichten des Strömungsquerschnitts eines Rotors ermöglicht, wodurch auch die Montagezeit der einzelnen Schaufeln am Rotor reduziert wird und die Leistung der Strömungsmaschine gesteigert wird. Gleichzeitig sollen die mechanischen Beanspruchungen, welchen die Enden der Schottwände am Schaufelfuß ausgesetzt sind, ebenfalls reduziert werden und eine sichere, dauerhafte Abdichtung des Strömungsquerschnitts sowie eines Rotors einer Strömungsmaschine ermöglicht werden.The invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for sealing the flow cross-section of a rotor. Furthermore, a solution is to be provided which allows a simple and cost-effective production of the sealing devices for sealing the flow cross section of a rotor, whereby the assembly time of the individual blades is reduced on the rotor and the performance of the turbomachine is increased. At the same time, the mechanical stresses to which the ends of the bulkhead walls are exposed at the blade root should also be reduced and a secure, permanent sealing of the flow cross-section and of a rotor of a turbomachine should be made possible.

Diese Aufgabe wird erfindungsgemäß durch eine Vorrichtung zum Abdichten des Strömungsquerschnitts eines Rotors einer Strömungsmaschine gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausführungen der Erfindung sind in den Unteransprüchen beschrieben.This object is achieved by a device for sealing the flow cross-section of a rotor of a turbomachine according to the features of claim 1. Advantageous embodiments of the invention are described in the subclaims.

Die erfindungsgemäße Abdichtvorrichtung zum Abdichten des Rotors einer Strömungsmaschine befindet sich an dem Schaufelschaft der Laufschaufeln einer Rotorstufe einer axialen Strömungsmaschine, wobei mehrere Schaufeln in Umfangsrichtung nebeneinander auf dem Rotor angeordnet sind. Die Abdichtvorrichtung weist am Schaufelschaft in axialer Richtung nach vorne und hinten hervorstehende Bodenplatten und in radialer Richtung sich entlang des Schaufelschafts erstreckenden Schottwände auf, die dabei eine doppelwandige Dichtung in axialer Richtung ausbilden. Der Übergangsquerschnitt von den Bodenplatten zu den Schottwänden ist dabei vorzugsweise abgerundet, bzw. parabolisch ausgebildet. Ferner ist zumindest eine der beiden Schottwände bezüglich des Schaufelfußrandes auf Höhe eines identischen radialen Abstands zur Rotorachse in Richtung der radialen Längsachse des Schaufelschafts nach Innen versetzt.The sealing device according to the invention for sealing the rotor of a turbomachine is located on the blade shank of the rotor blades of a Rotor stage of an axial flow machine, wherein a plurality of blades are arranged in the circumferential direction side by side on the rotor. The sealing device has on the blade shank in the axial direction to the front and rear protruding bottom plates and in the radial direction along the blade shank extending bulkheads, which form a double-walled seal in the axial direction. The transition cross section from the bottom plates to the bulkheads is preferably rounded, or parabolic. Furthermore, at least one of the two bulkhead walls is offset inwardly with respect to the blade root edge at the level of an identical radial distance from the rotor axis in the direction of the radial longitudinal axis of the blade shaft.

Dadurch wird erreicht, dass die Spannungsspitzen, welche durch die Torsion der Schaufel ausgehend vom äußeren Deckband, oder durch Fliehkräfte eingeleitete Spannungen am inneren Deckband oder weitere durch Gaskräfte verursachten Torsionsspannungen, an den Enden der Schottwände am Schaufelfuß reduziert werden. Durch den Versatz von zumindest einer der Schottwände bezüglich des Schaufelfußrandes in Richtung der radialen Längsachse des Schaufelschafts wird außerdem erreicht, dass die Schaufelfußlänge in axialer Richtung verringert wird. Diese Verringerung der Schaufelfußlänge ermöglicht wiederum eine kostengünstigere Herstellung der Bauteile, da weniger Material für das Bauteil notwendig ist, sowie eine gesteigerte Leistung der Strömungsmaschine, da das gesamte Gewicht der Maschine dadurch verringert wird. Ferner wird ein vermindertes Bruch-Risiko im Fall einer vorhandenen Plattenscherung aufgrund des Einflusses hoher Temperaturen und Zentrifugalkräften beim Betrieb der Strömungsmaschine erzielt. Die homogene Verteilung der mechanischen Spannungen am Ansatz der Schaufel bewirkt außerdem eine geringere punktuell konzentrierte Materialbeanspruchung des Bauteils, welche schonend für die Bauteile ist und in einer verlängerten Lebensdauer resultiert. Durch diese Konstruktion besteht die Abdichtvorrichtung außerdem aus einem einzigen massiven Bauteil. Mit der Spannungsreduzierung und der Homogenisierung der mechanischen Spannungen am Schaufelschaftansatz wird es außerdem möglich, die Dicke der Schottwände zu reduzieren, was zu einer weiteren Gewichtsreduzierung und dementsprechend zu einer weiteren Leistungssteigerung der Strömungsmaschine führt. Ferner kann die Höhe des Schaufelschafts ebenfalls reduziert werden.This ensures that the voltage peaks, which are caused by the torsion of the blade, starting from the outer shroud, or by centrifugal forces induced stresses on the inner shroud or other caused by gas forces torsional stresses at the ends of the bulkhead walls on the blade root. By the offset of at least one of the bulkhead walls with respect to the blade root edge in the direction of the radial longitudinal axis of the blade shaft is also achieved that the Schaufelfußlänge is reduced in the axial direction. This reduction in blade root length, in turn, allows for less costly component fabrication because less material is required for the component, as well as increased turbomachine performance, as it reduces the overall weight of the machine. Furthermore, a reduced risk of breakage is achieved in the case of existing plate shear due to the influence of high temperatures and centrifugal forces in the operation of the turbomachine. The homogeneous distribution of the mechanical stresses at the base of the blade also causes a lower concentrated concentrated material stress of the component, which is gentle on the components and results in a prolonged life. By this construction, the sealing device also consists of a single solid component. With the reduction in stress and the homogenization of the mechanical stresses on the blade shank approach, it is also possible to reduce the thickness of the bulkheads, leading to further weight reduction and accordingly leads to a further increase in performance of the turbomachine. Furthermore, the height of the blade shank can also be reduced.

Erfindungsgemäß sind zwei in radialer Richtung ausgebildete Schottwände, die sich von den hervorstehenden Bodenplatten in Richtung der Rotorachse erstrecken, insgesamt parabelförmig ausgebildet.According to the invention, two bulkhead walls, which are formed in the radial direction and extend from the protruding bottom plates in the direction of the rotor axis, have a total parabolic shape.

Durch die Wahl der parabolischen Form des Übergangsquerschnitts an der Verbindung zwischen der Bodenplatte und der radialen Schottwand als auch durch die Wahl der von den hervorstehenden Bodenplatten in Richtung der Rotorachse sich parabolisch erstreckende Schottwand, wird eine optimierte Dichtung geschaffen, welche die mechanischen Spannungen am Ansatz des Schaufelblatts weiter reduziert als auch die homogene Spannungsverteilung der Spannungen am Ansatz unterstützt.By choosing the parabolic shape of the transitional cross section at the connection between the bottom plate and the radial bulkhead, as well as by the choice of the partition wall extending parabolically from the protruding bottom plates in the direction of the rotor axis, an optimized seal is provided, which the mechanical stresses at the neck of Blade further reduced as well as the homogeneous stress distribution of the stresses supported at the neck.

Die getrennt hergestellten Bauteile können beispielsweise durch Schweißen miteinander verbunden werden und die Abdichtvorrichtung mit einer reibungsmindernden Beschichtung beschichtet sein.The separately produced components can be connected to one another by welding, for example, and the sealing device can be coated with a friction-reducing coating.

Stellt man sich eine Abdichtvorrichtung vor, welche aus zwei miteinander verbundenen T-Stücken besteht und an einem Schaufelschaft einer Schaufel verbunden ist, wirkt sich eine Kraft auf den nach außen gerichteten Platten in einer mechanischen Spannungsspitze im Bereich der zwei T-Verbindungen am Ansatz des Schaufelblattes aus. Die Kräfte, welche unter anderem auf die in axialer Richtung hervorstehenden Bodenplatten der Laufschaufeln ausgeübt werden, resultieren dagegen durch ihre gesamte Form und durch die Lage der Abdichtvorrichtung in einer homogenen Verteilung der mechanischen Spannungen im Bereich des Schaufelblattansatzes. In einem weiteren Ausführungsbeispiel der Erfindung ist die Wandstärke der Bodenplatten größer als die Wandstärke der radialen Schottwände. Dadurch wird beispielsweise eine Verstärkung des abgerundeten oder parabolischen Übergangsquerschnittes der Verbindungsstelle mit dem Schaufelfußtisch und mit den radialen Schottwände erreicht und gleichzeitig die Möglichkeit der Anpassung an vorgegebene breitere Ausdehnungsschlitze geschaffen.If one imagines a sealing device which consists of two interconnected T-pieces and is connected to a blade shank of a blade, a force acts on the outwardly facing plates in a mechanical stress peak in the region of the two T-joints at the base of the blade out. The forces that are exerted, inter alia, on the axially protruding bottom plates of the blades, on the other hand result by their overall shape and by the position of the sealing device in a homogeneous distribution of mechanical stresses in the region of the blade airfoil. In a further embodiment of the invention, the wall thickness of the bottom plates is greater than the wall thickness of the radial bulkhead walls. As a result, for example, an amplification of the rounded or parabolic cross-section of the junction with the blade root table and with the achieved radial bulkheads and at the same time created the possibility of adaptation to predetermined wider expansion slots.

In einem weiteren Ausführungsbeispiel der Erfindung besitzt zumindest eine der axial hervorstehenden Bodenplatten und der Schaufelfußtiscb, unterschiedliche Neigungen. Die erfindungsgemäße Abdichtvorrichtung ist somit in einer Vielzahl von verschiedenen Triebwerksarten anwendbar. Unterschiedliche Neigungen sind ferner als Anpassungsparameter für vorgegebene Ausdehnungsschlitze vorgesehen.In another embodiment of the invention, at least one of the axially protruding bottom plates and the blade foot disc has different inclinations. The sealing device according to the invention is thus applicable in a variety of different types of engines. Different inclinations are further provided as adjustment parameters for predetermined expansion slots.

In einem weiteren Ausführungsbeispiel der Erfindung mündet der Schaufeltisch in zumindest einer der hervorstehenden Bodenplatten L-förmig ein. Dadurch wird eine besonders effiziente Verteilung der an den axial hervorstehenden Bodenplatten ausgeübten Kräfte und eine weitere Homogenisierung der mechanischen Spannungen im Bereich des Schaufelblattansatzes erzielt, insbesondere wenn die Neigung des Schaufelschafts und der axial hervorstehenden Bodenplatten unterschiedlich sind.In a further embodiment of the invention, the paddle table opens in at least one of the protruding bottom plates L-shaped. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the blade shaft and the axially protruding bottom plates are different.

In einem weiteren Ausführungsbeispiel der Erfindung mündet der Schaufeltisch in die zwei hervorstehenden Bodenplatten U-formig ein. Dadurch wird eine besonders effiziente Verteilung der an den axial hervorstehenden Bodenplatten ausgeübten Kräfte und eine weitere Homogenisierung der mechanischen Spannungen im Bereich des Schaufelblattansatzes erzielt, insbesondere wenn die Neigung der zwei axial hervorstehenden Bodenplatten symmetrisch ist.In a further embodiment of the invention, the paddle table opens into the two protruding bottom plates U-shaped. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the two axially protruding bottom plates is symmetrical.

In einem anderen vorteilhaften Ausführungsbeispiel der Erfindung wird der Schaufelfußtisch gerade, geneigt oder gewölbt ausgebildet. Eine gerade Konfiguration des Schaufelfußtisches ist besonders vorteilhaft, wenn die in axialer Richtung hervorstehenden Bodenplatten ebenfalls gerade und in der gleichen Ebene ausgebildet sind, und insbesondere dann wenn die Strömungsmaschine einen konstanten Strömungsquerschnitt aufweist. Eine geneigte Konfiguration des Schaufelfußtisches ist besonders vorteilhaft wenn die in axialer Richtung hervorstehenden Bodenplatten unterschiedliche Neigungen aufweisen und/oder wenn der Strömungsquerschnitt der Strömungsmaschine sich ändert. Eine gewölbte Konfiguration des Schaufelfußtisches ist besonders vorteilhaft, um in speziellen Konfigurationen der Bodenplatten und/oder der Schottwände die Verbindungsstellen optimal zu verstärken.In another advantageous embodiment of the invention, the Schaufelfußtisch is formed straight, inclined or curved. A straight configuration of the blade root table is particularly advantageous if the bottom plates protruding in the axial direction are likewise formed straight and in the same plane, and in particular if the turbomachine has a constant flow cross section. An inclined configuration of the blade root table is particularly advantageous if the bottom plates projecting in the axial direction have different inclinations and / or if the flow cross section of the Turbomachine changes. A domed configuration of the blade root table is particularly advantageous for optimally reinforcing the joints in particular configurations of the floor panels and / or the bulkhead walls.

In einem anderen vorteilhaften Ausführungsbeispiel der Erfindung sind die Schaufel und die Abdichtvorrichtung einstückig ausgebildet. Dies hat den Vorteil, dass keine Befestigungsschlitze, weder am Schaufelschaft noch an der Rotorstufe mit äußerst geringen Toleranzen, für das Einklinken von seitlichen Abdichtplatten, die ebenfalls mit äußerst geringen Toleranzen hergestellt werden müssten, notwendig sind. Ein weiterer Vorteil besteht darin, dass bei der Montage nur noch ein einziges Bauteil an der Rotorstufe angeordnet werden muss, um eine in Umfangsrichtung doppelwandige Dichtung bereitzustellen.In another advantageous embodiment of the invention, the blade and the sealing device are integrally formed. This has the advantage that no mounting slots, neither on the blade shank nor on the rotor stage with extremely small tolerances, for the engagement of lateral sealing plates, which would also have to be produced with extremely low tolerances, are necessary. Another advantage is that only a single component at the rotor stage must be arranged during assembly in order to provide a double-walled seal in the circumferential direction.

In einem anderen vorteilhaften Ausführungsbeispiel der Erfindung bilden die Schaufel und die Abdichtvorrichtung zwei getrennte Bauteile, welche aneinander angeordnet werden. Die getrennt hergestellten Bauteile können beispielsweise durch Schweißen miteinander verbunden werden und die Abdichtvorrichtung mit einer reibungsmindernden Beschichtung beschichtet sein.In another advantageous embodiment of the invention, the blade and the sealing device form two separate components, which are arranged against one another. The separately produced components can be connected to one another by welding, for example, and the sealing device can be coated with a friction-reducing coating.

Die erfindungsgemäße Vorrichtung zum Abdichten des Strömungsquerschnitts eines Rotors findet sowohl in Turbinen als auch in Verdichtern von Gasturbinenanlagen und im Allgemeinen in Strömungsmaschinen Verwendung.The device according to the invention for sealing the flow cross-section of a rotor is used both in turbines and in compressors of gas turbine plants and generally in turbomachines.

Vorteilhafte Ausführungsbeispiele der Erfindung werden zusammen mit den Zeichnungen dargestellt und im folgenden näher beschrieben.Advantageous embodiments of the invention will be illustrated together with the drawings and described in more detail below.

Es zeigt:

Fig. 1
einen schematischen Längsschnitt durch einen Abschnitt einer Rotorstufe 5, die eine Abdichtvorrichtung 2 gemäß der vorliegenden Erfindung enthält;
Fig. 2
einen schematischen Längsschnitt durch die Abdichtvorrichtung 2 gemäß dem ersten vorteilhaften Ausführungsbeispiel der Erfindung;
Fig. 3
einen schematischen Längsschnitt durch die Abdichtvorrichtung 2 gemäß dem zweiten vorteilhaften Ausführungsbeispiel der Erfindung;
Fig. 4
einen schematischen Längsschnitt durch die Abdichtvorrichtung 2 gemäß dem dritten vorteilhaften Ausführungsbeispiel der Erfindung.
It shows:
Fig. 1
a schematic longitudinal section through a portion of a rotor stage 5, which includes a sealing device 2 according to the present invention;
Fig. 2
a schematic longitudinal section through the sealing device 2 according to the first advantageous embodiment of the invention;
Fig. 3
a schematic longitudinal section through the sealing device 2 according to the second advantageous embodiment of the invention;
Fig. 4
a schematic longitudinal section through the sealing device 2 according to the third advantageous embodiment of the invention.

Fig. 1 zeigt einen Teil eines Rotors, an dem eine Schaufel angeordnet ist, welche eine bevorzugte Ausführungsform der Erfindung enthält Wegen der Übersichtlichkeit wird im folgenden nur auf den abgebildeten Ausschnitt eingegangen, der sich aber über den ganzen Umfang des Rotors wiederholt. Die neben der Rotorwelle seitlich angedeuteten Bauteile 11 weisen abgerundete Ecken auf und definieren jeweils Ausdehnungsschlitze 3 für die Aufnahme der in axialer Richtung hervorstehenden Bodenplatte 6 des Abdichtelements 1. Jedes Abdichtelement weist dabei einen Schaufelfußtisch 8 mit zwei in axialer Richtung hervorstehenden Bodenplatten 6 und zwei zum Zentrum des Rotors 5 gerichteten und mit der in axialer Richtung hervorstehenden Bodenplatte 6 verbundene parabolisch ausgebildeten Schottwand 7, 7' auf. Die Abdichtelemente 1 können dabei als Segmente eines Rings angesehen werden, bei denen die Schaufelfußtische 8 radial angeordnet sind, und bei denen die Schottwände 7,7' eine doppelwandige Dichtungsringscheibe definieren. Die Dichtungsringscheibensegmente werden stark zusammengepresst, so dass sich zwischen den aneinander angrenzenden Enden der einzelnen Segmente keine Leckströmung ausbilden kann. Gleichzeitig wird genügend Raum für die durch die Betriebstemperatur verursachte Ausdehnung in Umfangsrichtung der Abdichtelemente 1 gelassen. In dem in Fig. 1 dargestellten Ausführungsbeispiel ist außerdem angedeutet, wie jede in axialer Richtung hervorstehende Bodenplatte 6 in einem radial und in Umfangsrichtung verlaufenden Ausdehnungsschlitz 3 untergebracht ist, welcher durch an der Rotorwelle 5 seitlich angeordnete Bauteile 11 gebildet ist. Dadurch wird bereits die Leckströmung, wegen der verkleinerten offenen Fläche, reduziert. Die Vorrichtung weist eine Abdichtvorrichtung 2 auf, welche zwei parabolisch ausgebildete Schottwände 7, 7' enthält, die bezüglich des Schaufelfußrandes 14, 14' in axialer Richtung zueinander hin versetzt sind. Durch den Versatz 12 der zwei Schottwände 7, 7' bezüglich des Schaufelfußrandes 14, 14'in Richtung der radialen Längsachse 13 des Schaufelschafts 4 werden die Spannungsspitzen an den Enden der Schottwände 7, 7' am Schaufelschaft 4 erheblich verringert. Durch die optimierte parabolische Ausbildung der Abdichtvorrichtung 2 im unteren Bereich des Schaufelschafts 4, wird eine stabile Abdichtung geschaffen, die in die Schaufel integriert ist und die weiterhin nicht als eine Befestigung der Schaufel am Rotor verwendet wird, so dass die Abdichtvorrichtung 2, abgesehen von der durch die Betriebstemperatur und von den Zentrifugalkräften verursachte Ausdehnung, keinen zusätzlichen mechanischen Beanspruchungen ausgesetzt wird. Fig. 1 shows a part of a rotor, on which a blade is arranged, which contains a preferred embodiment of the invention For the sake of clarity, the following is only the excerpt shown, but repeated over the entire circumference of the rotor. The laterally indicated adjacent to the rotor shaft components 11 have rounded corners and define respective expansion slots 3 for receiving the axially protruding bottom plate 6 of the sealing element 1. Each sealing element has a Schaufelfußtisch 8 with two axially projecting bottom plates 6 and two to the center directed to the rotor 5 and connected to the axially projecting bottom plate 6 connected parabolic partition wall 7, 7 '. The sealing elements 1 can be regarded as segments of a ring in which the blade root tables 8 are arranged radially, and in which the bulkheads 7,7 'define a double-walled sealing ring disc. The sealing ring disc segments are strongly compressed so that no leakage flow can form between the adjacent ends of the individual segments. At the same time, enough space for the expansion caused by the operating temperature in the circumferential direction of the sealing members 1 is left. In the in Fig. 1 illustrated embodiment is also indicated as each axially projecting bottom plate 6 is housed in a radially and extending in the circumferential direction of expansion slot 3, which is formed by arranged on the rotor shaft 5 laterally arranged components 11. This already reduces the leakage flow due to the reduced open area. The device has a sealing device 2, which contains two parabolic trained bulkheads 7, 7 ', which are offset with respect to the blade root edge 14, 14' in the axial direction to each other. By the offset 12 of the two bulkheads 7, 7 'with respect to Schaufelfußrandes 14, 14'in the direction of the radial longitudinal axis 13 of the blade shank 4, the stress peaks at the ends of the bulkheads 7, 7 'on the blade shank 4 are significantly reduced. Due to the optimized parabolic formation of the sealing device 2 in the lower region of the blade shank 4, a stable seal is created, which is integrated into the blade and which furthermore is not used as an attachment of the blade to the rotor, so that the sealing device 2, apart from the expansion caused by the operating temperature and centrifugal forces, is not exposed to additional mechanical stresses.

Fig. 2 zeigt einen Längsschnitt durch die Abdichtvorrichtung 2, gemäß einer ersten bevorzugten Ausführungsform der Erfindung. Hier besitzen die in axialer Richtung hervorstehenden Bodenplatten 6 sowie der Schaufelfußtisch 8 die gleiche Neigung und liegen in der gleichen Ebene. Die sich nach unten und in radialer Richtung erstreckenden Schottwände 7, 7' bilden mit den hervorstehenden Bodenplatten 6 und mit dem Schaufelfußtisch 8 gerundete Verbindungen aus und laufen in Richtung der Rotorachse. In diesem Beispiel ist außerdem die Wandstärke des Schaufelfußtisches 8, der Bodenplatten 6 und der Schottwände 7, 7' gleich. Ferner weist die Abdichtvorrichtung 2 zwei unterschiedlich ausgebildete Schottwände 7, 7' auf. Die in der Zeichnungsebene rechte Schottwand 7' ist L-förmig ausgebildet und läuft parallel zu der Längsachse 13 des Schaufelschafts 4, während die in der Zeichnungsebene linke Schottwand 7 in Richtung der Längsachse 13 des Schaufelschafts 4 gerade zuläuft und bezüglich des Schaufelfußrandes 14 nach Innen versetzt ist. Durch den Versatz 12 der in der Zeichnungsebene linken Schottwand 7 bezüglich des Schaufelfußrandes 14 in Richtung der radialen Längsachse 13 des Schaufelschafts 4 werden die Spannungsspitzen an den Enden der Schottwände 7, 7' am Schaufelschaft 4 erheblich verringert. Fig. 2 shows a longitudinal section through the sealing device 2, according to a first preferred embodiment of the invention. Here, the axially protruding bottom plates 6 and the Schaufelfußtisch 8 have the same inclination and are in the same plane. The bulkheads 7, 7 'extending downwardly and radially form with the protruding bottom plates 6 and with the blade root table 8 rounded connections and run in the direction of the rotor axis. In this example, moreover, the wall thickness of the blade root table 8, the bottom plates 6 and the bulkheads 7, 7 'is the same. Furthermore, the sealing device 2 has two differently configured bulkheads 7, 7 '. The right in the plane of the bulkhead wall 7 'is L-shaped and runs parallel to the longitudinal axis 13 of the blade shank 4, while the left in the drawing plane bulkhead 7 in the direction of the longitudinal axis 13 of the blade shank 4 straight and offset with respect to the Schaufelfußrandes 14 inside is. By the offset 12 of the left in the plane of the bulkhead wall 7 with respect to the Schaufelfußrandes 14 in the direction of the radial longitudinal axis 13 of the blade shank 4, the voltage peaks at the ends of the bulkheads 7, 7 'on the blade shank 4 are significantly reduced.

Fig. 3 zeigt einen Längsschnitt durch die Abdichtvorrichtung 2, gemäß einer zweiten bevorzugten Ausführungsform der Erfindung. Hier besitzen die in axialer Richtung hervorstehenden Bodenplatten 6 sowie der Schaufelfußtisch 8 unterschiedliche Neigungen und liegen auf verschiedenen Ebenen. Die sich nach dem Rotorzentrum und in radialer Richtung erstreckenden parabolischen Schottwände 7, 7' bilden mit den hervorstehenden Bodenplatten 6 und mit dem Schaufelfußtisch 8 parabolische Verbindungen aus und verlaufen parabolisch in Richtung der Rotorachse und anschließend parallel zueinander. Der Schaufelfußtisch 8 mündet hier außerdem L-förmig in der Zeichnungsebene rechts dargestellten hervorstehenden Bodenplatte 6. In diesem Beispiel ist ferner die Wandstärke des Schaufelfußtisches 8 und der Bodenplatten 6 größer als die Wandstärke der Schottwände 7, 7'. Die in der Zeichnungsebene rechte Schottwand 7' ist außerdem in Richtung der Längsachse 13 des Schaufelschafts 4 zuerst parabelförmig und anschließend gerade ausgebildet und bezüglich des Schaufelfußrandes 14' nach Innen versetzt. Durch den Versatz 12 der in der Zeichnungsebene rechten Schottwand 7' bezüglich des Schaufelfußrandes 14' in Richtung der radialen Längsachse 13 des Schaufelschafts 4 werden die Spannungsspitzen an den Enden der Schottwände 7, 7' am Schaufelschaft 4 erheblich verringert, da hierdurch der Kraftfluss der eingeleiteten Kräfte optimiert wird. Fig. 3 shows a longitudinal section through the sealing device 2, according to a second preferred embodiment of the invention. Here, the bottom plates 6 protruding in the axial direction and the blade foot table 8 have different Inclinations and lie on different levels. The parabolic bulkheads 7, 7 'extending after the rotor center and in the radial direction form parabolic connections with the protruding bottom plates 6 and with the blade root table 8 and extend parabolically in the direction of the rotor axis and subsequently parallel to one another. The Schaufelfußtisch 8 also opens here L-shaped in the drawing plane right projecting bottom plate 6. In this example, the wall thickness of the blade root table 8 and the bottom plates 6 is also greater than the wall thickness of the bulkheads 7, 7 '. The right in the plane of the bulkhead wall 7 'is also in the direction of the longitudinal axis 13 of the blade shank 4 first parabolic and then straight and offset with respect to the Schaufelfußrandes 14' to the inside. Due to the offset 12 of the right in the plane of the bulkhead wall 7 'with respect to the Schaufelfußrandes 14' in the direction of the radial longitudinal axis 13 of the blade shank 4, the voltage peaks at the ends of the bulkheads 7, 7 'on the blade shank 4 are significantly reduced, as a result, the power flow of the introduced Forces is optimized.

Fig. 4 zeigt einen Längsschnitt durch die Abdichtvorrichtung 2, gemäß einer dritten bevorzugten Ausführungsform der Erfindung. Hier besitzen die in axialer Richtung hervorstehenden Bodenplatten 6 sowie der Schaufelfußtisch 8 zwar die gleiche Neigung, liegen jedoch auf unterschiedlichen Ebenen. Die sich nach dem Rotorzentrum und in radialer Richtung erstreckenden und parabolisch zulaufenden Schottwände 7, 7' bilden mit den hervorstehenden Bodenplatten 6 und mit dem Schaufelfußtisch 8 abgerundete Verbindungen aus und laufen parabolisch in Richtung der Rotorachse zu. In diesem Beispiel ist ferner die Wandstärke der Schottwände 7, 7' größer als die Wandstärke des Schaufelfußtisches 8 und der Bodenplatten 6. Die in der Zeichnungsebene rechte Schottwand 7' ist außerdem in Richtung der Längsachse 13 des Schaufelschafts 4, d.h. in radialer Richtung im Bezug auf die axiale Strömungsmaschine, zuerst parabelförmig und anschließend geradlinig ausgebildet. Dabei ist im vorliegenden Ausführungsbeispiel etwa das letzte Drittel als Gerade ausgebildet, während die ersten beiden Drittel des Schaufelschafts 4 in etwa eine Parabel bilden. Bezüglich des Schaufelfußrandes 14' ist die in der Zeichnungsebene rechte Schottwand 7' nach Innen versetzt. Durch den Versatz 12 der in der Zeichnungsebene rechten Schottwand 7' bezüglich des Schaufelfußrandes 14' in Richtung der radialen Längsachse 13 des Schaufelschafts 4 werden die Spannungsspitzen an den Enden der Schottwände 7, 7' am Schaufelschaft 4 erheblich verringert. Fig. 4 shows a longitudinal section through the sealing device 2, according to a third preferred embodiment of the invention. Although the bottom plates 6 projecting in the axial direction and the blade foot table 8 have the same inclination, they are located at different levels. The bulkheads 7, 7 ', which extend after the rotor center and in the radial direction and parabolically taper, form rounded connections with the protruding bottom plates 6 and with the blade root table 8 and run parabolically in the direction of the rotor axis. In this example, further, the wall thickness of the bulkheads 7, 7 'greater than the wall thickness of the blade root table 8 and the bottom plates 6. The right in the drawing plane bulkhead 7' is also in the direction of the longitudinal axis 13 of the blade shaft 4, ie in the radial direction with respect on the axial flow machine, first parabolic and then rectilinear. In this case, approximately the last third is formed as a straight line in the present embodiment, while the first two thirds of the blade shank 4 form approximately a parabola. With respect to the Schaufelfußrandes 14 'is in the plane of the drawing right bulkhead 7 'offset inside. By the offset 12 of the right in the plane of the bulkhead wall 7 'with respect to the Schaufelfußrandes 14' in the direction of the radial longitudinal axis 13 of the blade shank 4, the stress peaks at the ends of the bulkheads 7, 7 'on the blade shank 4 are significantly reduced.

Claims (9)

  1. Sealing apparatus (2) at a blade shaft (4) of a rotor stage of an axial turbomachine, wherein a plurality of blades is arranged next to each other on a rotor (5) in the circumferential direction, and wherein the sealing apparatus (2) has base plates (6) protruding in the axial direction on the blade shaft (4) and bulkheads (7, 7') extending in the radial direction along the blade shaft (4), which bulkheads form a double-walled seal (10) in the axial direction, wherein from the bottom plate (6) to the bulkhead (7, 7'), a rounded or a parabolic transitional cross section is provided, wherein at least one of the bulkheads (7, 7') is offset in relation to a blade root edge (14, 14') in the direction of the radial longitudinal axis (13) of the blade shaft (4), characterised in that at least one of the bulkheads (7, 7') is formed to be parabolic in the direction of the rotor axis.
  2. The sealing apparatus (2) as claimed in claim 1, characterised in that the wall thickness of the bottom plate (6) is greater than the wall thickness of the radial bulkheads (7, 7').
  3. The sealing apparatus (2) as claimed in any one of patent claims 1 to 2, characterised in that a blade root table (8) and at least one of the two bottom plates (6) have different inclinations.
  4. The sealing apparatus (2) as claimed in patent claim 3, characterised in that the transition of the blade root table (8) into at least one of the protruding bottom plates (6) is formed by a rounded L-shaped connection.
  5. The sealing apparatus (2) as claimed in any one of patent claims 3 to 4, characterised in that the transition of the blade root table (8) into the protruding bottom plates (6) is formed by a rounded U-shaped connection.
  6. The sealing apparatus (2) as claimed in any one of patent claims 3 to 5, characterised in that the blade root table (8) is formed to be straight, inclined or curved.
  7. The sealing apparatus (2) as claimed in any one of patent claims 1 to 6, characterised in that the sealing apparatus (2) is formed to be integral with the blade.
  8. The sealing apparatus (2) as claimed in any one of patent claims 1 to 7, characterised in that the sealing apparatus (2) and the blade are formed as two separate components.
  9. The use of the sealing apparatus (2) as claimed in any one of the preceding claims in a gas turbine.
EP10710168.5A 2009-02-05 2010-02-02 Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine and the use thereof Not-in-force EP2394028B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009007664A DE102009007664A1 (en) 2009-02-05 2009-02-05 Sealing device on the blade shank of a rotor stage of an axial flow machine
PCT/DE2010/000105 WO2010088881A1 (en) 2009-02-05 2010-02-02 Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine

Publications (2)

Publication Number Publication Date
EP2394028A1 EP2394028A1 (en) 2011-12-14
EP2394028B1 true EP2394028B1 (en) 2016-06-01

Family

ID=42126369

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10710168.5A Not-in-force EP2394028B1 (en) 2009-02-05 2010-02-02 Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine and the use thereof

Country Status (5)

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US (1) US8870542B2 (en)
EP (1) EP2394028B1 (en)
DE (1) DE102009007664A1 (en)
ES (1) ES2576125T3 (en)
WO (1) WO2010088881A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2597266B1 (en) 2011-11-22 2014-08-27 MTU Aero Engines GmbH Rotor blade and flow machine
FR2997723B1 (en) * 2012-11-06 2018-09-21 Safran Aircraft Engines AUBE AT FOOT WITH PORTIONS IN LOW
US9353629B2 (en) * 2012-11-30 2016-05-31 Solar Turbines Incorporated Turbine blade apparatus
FR3004484B1 (en) * 2013-04-11 2017-09-08 Snecma TURBOMACHINE DAWN COOPERATING WITH AUBES RETENTION DISC
ES2718127T3 (en) 2013-06-27 2019-06-27 MTU Aero Engines AG Turbine blade of turbomachine and respective turbomachine

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL192865A (en) * 1953-12-02
GB1148339A (en) * 1966-10-20 1969-04-10 Rolls Royce Compressors or turbines for gas turbine engines
GB1295003A (en) 1971-06-15 1972-11-01
FR2485632B1 (en) 1980-06-30 1985-07-05 Snecma IMPROVEMENT IN VENTILATION SYSTEMS OF BLADES AND TURBINE DISCS
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
FR2586061B1 (en) * 1985-08-08 1989-06-09 Snecma MULTIFUNCTIONAL LABYRINTH DISC FOR TURBOMACHINE ROTOR
DE3743253A1 (en) 1987-12-19 1989-06-29 Mtu Muenchen Gmbh AXIAL FLOWED BLADE BLADES FOR COMPRESSORS OR TURBINES
US5131814A (en) 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5443365A (en) 1993-12-02 1995-08-22 General Electric Company Fan blade for blade-out protection
JPH08121106A (en) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd Turbine moving blade
GB2302711A (en) 1995-06-26 1997-01-29 Bmw Rolls Royce Gmbh A turbine disc with blade seal plates
JP2002544430A (en) * 1999-05-14 2002-12-24 シーメンス アクチエンゲゼルシヤフト Fluid machinery with leak-proof device for rotor, especially gas turbine
EP1371814A1 (en) 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
US7244104B2 (en) * 2005-05-31 2007-07-17 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
US7334983B2 (en) * 2005-10-27 2008-02-26 United Technologies Corporation Integrated bladed fluid seal
DE102005059084A1 (en) * 2005-12-10 2007-06-14 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine
US7575416B2 (en) * 2006-05-18 2009-08-18 United Technologies Corporation Rotor assembly for a rotary machine
EP1898049B1 (en) 2006-09-11 2012-05-23 Siemens Aktiengesellschaft Turbine blade
US20080101937A1 (en) 2006-10-26 2008-05-01 General Electric Blade/disk dovetail backcut for blade/disk stress reduction (9FA, stage 1)
FR2918103B1 (en) * 2007-06-27 2013-09-27 Snecma DEVICE FOR COOLING ALVEOLES OF A TURBOMACHINE ROTOR DISK.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
ES2576125T3 (en) 2016-07-05
DE102009007664A1 (en) 2010-08-12
WO2010088881A1 (en) 2010-08-12
US20110293408A1 (en) 2011-12-01
US8870542B2 (en) 2014-10-28
EP2394028A1 (en) 2011-12-14

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