EP1092081A1 - Rotor for a turbomachine - Google Patents

Rotor for a turbomachine

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Publication number
EP1092081A1
EP1092081A1 EP99939943A EP99939943A EP1092081A1 EP 1092081 A1 EP1092081 A1 EP 1092081A1 EP 99939943 A EP99939943 A EP 99939943A EP 99939943 A EP99939943 A EP 99939943A EP 1092081 A1 EP1092081 A1 EP 1092081A1
Authority
EP
European Patent Office
Prior art keywords
flange
rotor according
disk
bolts
rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP99939943A
Other languages
German (de)
French (fr)
Other versions
EP1092081B1 (en
Inventor
Hermann Klingels
Martin Fischer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP1092081A1 publication Critical patent/EP1092081A1/en
Application granted granted Critical
Publication of EP1092081B1 publication Critical patent/EP1092081B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the invention relates to a rotor for a turbomachine, with at least two bladed stages, the disks are releasably connected to one another.
  • Turbomachine rotors generally have several stages provided with blades, the disks of which are different, e.g. by welding or releasably by screwing together. In the present case, only stages that are releasably connected are considered.
  • the disks In the case of a known rotor, the disks have cylindrical or conical shells which extend essentially in the axial direction, at the end sections of which disk-ring-shaped flanges are provided, on which adjacent disks are connected with screws, stud bolts or the like. If an intermediate stage seal is not integrated in the shells, it is clamped between the flanges.
  • Such a type of connection can only be used for components with a relatively low peripheral speed, e.g. Use long-running low-pressure turbines, since the centrifugal forces that occur in the case of disks designed for high circumferential speeds produce excessive circumferential stresses in the flange connection.
  • the holes in the flanges represent notch points that cause local stress increases and severely limit the cyclical life of the component.
  • a disk has bores by means of which it is screwed to adjacent disks which have cylindrical or conical shells with flanges.
  • the washer body limits the radial expansion of the connection point due to centrifugal force. It is problematic, however, that the bores in the heavily loaded disc body represent life-limiting notches.
  • a connection of rotor elements of a gas turbine is known from US Pat. No. 4,844,694, in which the disk located at the connection point has a bore for inserting a bolt, the bores in the highly loaded disk body representing notch points which limit the service life.
  • the last-mentioned disadvantage is also present in the pin connection between rotor elements of a gas turbine disclosed in US Pat. No. 5,052,891, in which a hole is provided for the pin connection in the disk located at the connection point.
  • the invention has for its object to provide a rotor for a turbomachine of the type described in the opening paragraph, in which the disks are detachably connected to one another without extreme increases in tension due to notches in the disk occurring.
  • a first disk has at least one of its two side surfaces a first flange which is connected or clamped to a second flange of an adjacent disk by bolts.
  • the first flange preferably extends radially inward at an axial distance from the side face of the first disk, forming an intermediate space.
  • the first flange is designed as a disk ring which has cutouts along its inner end or peripheral edge.
  • the cutouts are preferably opened inwards so that the centrifugal force generated by the bolts can be absorbed by the edge surface of the cutouts.
  • the recesses are arranged equidistantly along the peripheral edge.
  • a hole, an elongated hole or a further recess can be provided between the recesses.
  • a flange section of an intermediate stage seal is most preferably clamped between the first and second flange, the flange section of the intermediate stage seal preferably having bores which are aligned with the cutouts of the first flange and fix the bolts in the radial direction during assembly.
  • the bolts at their ends facing the first disk have a transverse section extending at right angles to their longitudinal axis, with which they are supported on an inner side surface of the first flange a.
  • the bolts are preferably T-head bolts.
  • the distance between the first flange and the side surface of the first disk is preferably as small as possible, but larger than the thickness of the transverse section of the bolt, in order to avoid a pressure point on the highly loaded first disk.
  • the flange of an adjacent washer has at its radially inner end an essentially axially extending support section on which the transverse section of the bolts is supported in order to secure the bolts against rotation.
  • the first disk has a first flange on both side surfaces, so that the disks of rotors can also be detachably connected with more than two stages in this way.
  • FIG. 1 is a view in longitudinal section of an embodiment of the rotor according to the invention, which has no hatching for a better overview.
  • Fig. 2 is a broken cross-sectional view along line II-II of Fig. 1 and
  • FIG. 3 shows a broken view in longitudinal section of a further exemplary embodiment of the rotor according to the invention.
  • Fig. 1 shows a longitudinal section of an embodiment of the rotor according to the invention for a turbomachine, which has three stages.
  • the steps are each provided with a shovel 1, 2 and 3 and a first disk 4 and two adjacent disks 5, 6.
  • the first disc 4 has a flange 9 and 10 on its two side surfaces 7, 8.
  • the flanges 9, 10 extend at an axial distance A from their inner side surfaces 11, 12 to the side surfaces 7, 8 the first disc 4. In this way, between the first disc 4 and the flanges 9, 10 there is an intermediate space Z which is open inwards in the radial direction.
  • the distance A is to be kept as small as possible in order to begin with the radial expansion of the flanges 9, 10 or the flange connection through the body of the disk 4.
  • a transverse section 13 engages a (screw) bolt 14 in the intermediate space Z and is supported on the inner side surface, e.g. 12, the flange 10.
  • the disks 5, 6 adjacent to the middle, first disk 4 each have cylindrical shells 16 which extend essentially in the axial direction and which can also be conical.
  • the shells 16 have at their ends remote from the disks 5, 6 each a second flange 17, which is connected to the flanges 9, 10 of the first disk 4 by means of (screw) bolts 14 or the like. is firmly clamped.
  • At the second flanges 17 of the disks 5,6 each adjoins a substantially axially extending support section 18, on which the transverse sections 13 of the bolts 14 can be supported, thereby preventing the bolts 14 from rotating. This ensures that no pressure points occur on the highly loaded, first disks 4 when mounting or tightening the (screw) bolts 14.
  • an intermediate stage seal 19 with its flange section 20 is clamped and releasably attached.
  • the intermediate stage seals 19 can alternatively also be arranged integrally on the disks 5, 6 or their shells 16.
  • FIG. 2 shows a cut out and broken cross-sectional view according to line II-II from FIG. 1, in the upper partial section of which the flange 9 is shown in a top view.
  • the flange 9 is designed as a disk ring, on the inner end face or peripheral edge 21 of which is open in the radial direction and slit-like Recesses 15 are provided.
  • a (screw) bolt 14 is inserted, the cross section 13 is shown in dashed lines. After mounting, it is supported on the inner side surface 11 of the flange 9.
  • its transverse section 13 is also supported on the support section 18 of the shell 16 of the adjacent disk 5.
  • the bores 22 can also be used as elongated holes, further cutouts or the like. be trained.
  • the disk-ring-shaped flange section 20 of the intermediate stage seal 19 is shown, which has bores 23.
  • the bores 23 are aligned with the cutouts 15 in the flanges 9, 10 of the first disk 4, as are corresponding bores 24 in the second flanges 17 from the disks 5, 6 adjacent to the first disk 4.
  • the bores 23 in the flange section 20 of the intermediate stage seal 19 are opened radially inward, their opening dimension being smaller than their diameter, so as to radially fix the (screw) bolts 14 during assembly guarantee.
  • the bores 23 can also be designed as closed bores.
  • every second stage is provided with a first disc 4 having at least one flange 9 or 10.
  • Fig. 3 shows a further embodiment of the rotor according to the invention, in which the radius R at the transition between the inner side surface 8 of the first disc 4 and the flange 10 or its inner side surface 12 is increased for reasons of strength.
  • the distance A between the side surface 8 of the first disk 4 and the inner side surface 12 of the flange 10 is greater, the (screw) bolt 14 has a shear ring or collar 25 which rests on an outer side surface 26 of the flange 10 and prevents axial displacement of the (screw) bolt 14, so that the cross sections 13 during assembly not be pressed against the first disc 4 and lose their security against twisting.

Landscapes

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

Abstract

The invention relates to a rotor for a turbomachine comprising at least two bladed steps whose discs (4, 5, 6) are detachably connected to one another. A first disc (4) comprises at least one first flange (9, 10) on a lateral surface (7, 8) in order to avoid notch positions in the highly stressed discs. Said flange is connected to or braced against a second flange (17) of an adjacent disc (5, 6) by bolts (14).

Description

Rotor für eine Turbomaschine Rotor for a turbo machine
Die Erfindung betrifft einen Rotor für eine Turbomaschine, mit wenigstens zwei beschaufelten Stufen, deren Scheiben lösbar miteinander verbu nden sind.The invention relates to a rotor for a turbomachine, with at least two bladed stages, the disks are releasably connected to one another.
Rotoren von Turbomaschinen weisen im allgemeinen mehrere, mit Schaufeln vers e- hene Stufen auf, deren Scheiben auf unterschiedliche Weise, z.B. durch Schweißen oder lösbar durch Verschrauben, miteinander verbunden sind. Vorliegend werden lediglich lösbar miteinander verbundene Stufen betrachtet.Turbomachine rotors generally have several stages provided with blades, the disks of which are different, e.g. by welding or releasably by screwing together. In the present case, only stages that are releasably connected are considered.
Bei einem bekannten Rotor weisen die Scheiben sich im wesentlichen in Axialrichtung erstreckende, zylindrische oder kegelförmige Schalen auf, an deren Enda b- schnitten jeweils scheibenringförmige Flansche vorgesehen sind, an welchen b e- nachbarte Scheiben mit Schrauben, Stehbolzen od. dgl. verbunden sind. Sofern eine Zwischenstufendichtung nicht in den Schalen integriert ist, wird sie jeweils zwischen den Flanschen eingeklemmt. Eine derartige Verbindungsart läßt sich lediglich bei Komponenten mit verhältnismäßig niedriger Umfangsgeschwindigkeit, wie z.B. lan g- sam laufende Niederdruckturbinen, einsetzen, da die auftretenden Fliehkräfte bei für hohe Umfangsgeschwindigkeiten ausgelegten Scheiben zu hohe Umfangsspannu n- gen in der Flanschverbindung erzeugen. Die Bohrungen in den Flanschen stellen I o- kale Spannungserhöhungen verursachende Kerbstellen dar und schränken die zykl i- sche Lebensdauer des Bauteils stark ein.In the case of a known rotor, the disks have cylindrical or conical shells which extend essentially in the axial direction, at the end sections of which disk-ring-shaped flanges are provided, on which adjacent disks are connected with screws, stud bolts or the like. If an intermediate stage seal is not integrated in the shells, it is clamped between the flanges. Such a type of connection can only be used for components with a relatively low peripheral speed, e.g. Use long-running low-pressure turbines, since the centrifugal forces that occur in the case of disks designed for high circumferential speeds produce excessive circumferential stresses in the flange connection. The holes in the flanges represent notch points that cause local stress increases and severely limit the cyclical life of the component.
Die DE 196 27 386 A1 offenbart eine Verbindungs-Anordnung für zwei Turbinen- Laufradscheiben, die jeweils Scheiben-Verbindungsarme mit Durchsteckbohrungen aufweisen, in welche besonders ausgestaltete Gewindebolzen zur Verbindung der Laufradscheiben eingesetzt werden. Insbesondere bei hohen Umfangsgeschwindi g- keiten erweist sich als nachteilig, daß eine radiale Aufweitung der Flanschverbindung infolge der Fliehkraftwirkung auftritt.DE 196 27 386 A1 discloses a connecting arrangement for two turbine impeller disks, each having disk connecting arms with push-through bores, into which specially designed threaded bolts are used to connect the impeller disks. In particular at high peripheral speeds, it proves disadvantageous that a radial expansion of the flange connection occurs as a result of the centrifugal force effect.
Bei schnellaufenden Niederdruckturbinen sind bspw. an den Zwischenstufendichtungen zusätzliche, sich radial nach innen erstreckende Scheiben vorgesehen worden. Auf diese Weise soll die radiale Aufweitung so begrenzt werden, daß die entstehe n- den Umfangsspannungen infolge der Fliehkraftwirkungen auf einem niedrigen Niveau gehalten werden und die geforderte zyklische Lebensdauer erreicht wird. Die zusät zlichen Scheiben führen jedoch zu erheblichen Gewichtsnachteilen und Problemen bei der Montage.In high-speed low-pressure turbines, for example, additional, radially inwardly extending disks have been provided on the intermediate stage seals. In this way, the radial expansion should be limited in such a way that the resulting circumferential stresses due to the effects of centrifugal forces are kept at a low level and the required cyclical service life is achieved. However, the additional disks lead to considerable weight disadvantages and problems during assembly.
Bei einem weiteren bekannten Rotor weist eine Scheibe Bohrungen auf, durch we I- che sie mit benachbarten Scheiben, die zylindrische oder kegelförmige Schalen mit Flanschen aufweisen, durch Verschrauben verbunden wird. Der Scheibenkörper b e- grenzt die radiale Aufweitung der Verbindungsstelle infolge von Fliehkraftwirkung. Problematisch ist jedoch, daß die Bohrungen in dem hochbelasteten Scheibenkörper lebensdauerbegrenzende Kerbstellen da rstellen.In a further known rotor, a disk has bores by means of which it is screwed to adjacent disks which have cylindrical or conical shells with flanges. The washer body limits the radial expansion of the connection point due to centrifugal force. It is problematic, however, that the bores in the heavily loaded disc body represent life-limiting notches.
Aus der US 4,844,694 ist eine Verbindung von Rotorelementen einer Gasturbine bekannt, bei der die an der Verbindungsstelle liegende Scheibe eine Bohrung zum Einsetzen eines Bolzens aufweist, wobei die Bohrungen in dem hochbelasteten Scheibenkörper lebensdauerbegrenzende Kerbstellen darstellen. Letztgenannter Nachteil ist auch bei der in der US 5,052,891 offenbarten Bolzenverbindung zwischen Rotorelementen einer Gasturbine gegeben, bei welcher in der an der Verbi n- dungsstelle liegenden Scheibe eine Bohrung für die Bolzenverbindung vorgesehen ist.A connection of rotor elements of a gas turbine is known from US Pat. No. 4,844,694, in which the disk located at the connection point has a bore for inserting a bolt, the bores in the highly loaded disk body representing notch points which limit the service life. The last-mentioned disadvantage is also present in the pin connection between rotor elements of a gas turbine disclosed in US Pat. No. 5,052,891, in which a hole is provided for the pin connection in the disk located at the connection point.
Der Erfindung liegt die Aufgabe zugrunde, einen Rotor für eine Turbomaschine der eingangs beschriebenen Gattung zu schaffen, bei dem die Scheiben lösbar miteina n- der verbunden werden, ohne daß extreme Spannungserhöhungen durch Kerbstellen in der Scheibe auftreten.The invention has for its object to provide a rotor for a turbomachine of the type described in the opening paragraph, in which the disks are detachably connected to one another without extreme increases in tension due to notches in the disk occurring.
Die Lösung der Aufgabe ist erfindungsgemäß dadurch gekennzeichnet, daß eine e rste Scheibe an wenigstens einer ihrer beiden Seitenflächen einen ersten Flansch aufweist, der mit einem zweiten Flansch einer benachbarten Scheibe durch Bolzen verbunden bzw. verspannt ist. Der Vorteil einer solchen Ausgestaltung besteht darin, daß die radiale Aufweitung der Flanschverbindung durch den Scheibenkörper begrenzt wird, die Scheibe selbst jedoch keine Bohrungen bzw. Kerbstellen aufweist, welche die zum Teil extrem h o- hen, lokalen Spannungserhöhungen verursachen.The solution to the problem is characterized in that a first disk has at least one of its two side surfaces a first flange which is connected or clamped to a second flange of an adjacent disk by bolts. The advantage of such a configuration is that the radial expansion of the flange connection is limited by the washer body, but the washer itself does not have any bores or notches, which in some cases cause extremely high, local stress increases.
Bevorzugt erstreckt sich der erste Flansch mit axialem Abstand zur Seitenfläche der ersten Scheibe unter Bildung eines Zwischenraums radial nach innen.The first flange preferably extends radially inward at an axial distance from the side face of the first disk, forming an intermediate space.
In einer bevorzugten Ausgestaltung ist der erste Flansch als Scheibenring ausgebi I- det, der entlang seiner inneren Stirn- bzw. Umfangskante Aussparungen au fweist.In a preferred embodiment, the first flange is designed as a disk ring which has cutouts along its inner end or peripheral edge.
Bevorzugt sind die Aussparungen nach innen geöffnet, damit die durch die Bolzen erzeugte Fliehkraft durch die Randfläche der Aussparungen aufgenommen werden kann.The cutouts are preferably opened inwards so that the centrifugal force generated by the bolts can be absorbed by the edge surface of the cutouts.
Femer ist vorteilhaft, daß die Aussparungen äquidistant entlang der Umfangskante angeordnet sind.It is also advantageous that the recesses are arranged equidistantly along the peripheral edge.
Zur Reduzierung der Kerbwirkung kann zwischen den Aussparungen jeweils eine Bohrung, ein Langloch oder eine weitere Aussparung vorgesehen werden.To reduce the notch effect, a hole, an elongated hole or a further recess can be provided between the recesses.
Höchst bevorzugt ist ein Flanschabschnitt einer Zwischenstufendichtung jeweils zwischen dem ersten und zweiten Flansch eingeklemmt, wobei der Flanschabschnitt der Zwischenstufendichtung bevorzugt zu den Aussparungen des ersten Flansches fluchtende Bohrungen aufweist, welche die Bolzen in Radialrichtung bei der Montage fixieren.A flange section of an intermediate stage seal is most preferably clamped between the first and second flange, the flange section of the intermediate stage seal preferably having bores which are aligned with the cutouts of the first flange and fix the bolts in the radial direction during assembly.
Es ist ferner zweckmäßig, daß die Bolzen an ihren der ersten Scheibe zugewandten Enden einen sich rechtwinklig zu ihrer Längsachse erstreckenden Querabschnitt aufweisen, mit dem sie sich an einer inneren Seitenfläche des ersten Flansches a b- stützen. Bevorzugt sind die Bolzen T-Kopf-Bolzen. Bevorzugt ist der Abstand des ersten Flansches zur Seitenfläche der ersten Scheibe möglichst gering, jedoch größer als die Stärke des Querabschnitts des Bolzens, um eine Druckstelle an der hochbelasteten, ersten Scheibe zu vermeiden.It is furthermore expedient that the bolts at their ends facing the first disk have a transverse section extending at right angles to their longitudinal axis, with which they are supported on an inner side surface of the first flange a. The bolts are preferably T-head bolts. The distance between the first flange and the side surface of the first disk is preferably as small as possible, but larger than the thickness of the transverse section of the bolt, in order to avoid a pressure point on the highly loaded first disk.
Höchst bevorzugt weist der Flansch einer benachbarten Scheibe an seinem radial inneren Ende einen sich im wesentlichen in Axialrichtung erstreckender Stützabschnitt auf, an dem sich der Querabschnitt der Bolzen abstützt, um so eine Verdrehsicherung der Bolzen zu schaffen.Most preferably, the flange of an adjacent washer has at its radially inner end an essentially axially extending support section on which the transverse section of the bolts is supported in order to secure the bolts against rotation.
In einer bevorzugten Ausgestaltung weist die erste Scheibe an beiden Seitenflächen einen ersten Flansch auf, so daß sich auf diese Weise auch die Scheiben von Rot o- ren mit mehr als zwei Stufen lösbar verbinden lassen.In a preferred embodiment, the first disk has a first flange on both side surfaces, so that the disks of rotors can also be detachably connected with more than two stages in this way.
Weitere Ausgestaltungen der Erfindung sind in den Unteransprüchen beschrieben.Further refinements of the invention are described in the subclaims.
Im folgenden wird die Erfindung unter Bezugnahme auf eine Zeichnung anhand von Ausführungsbeispielen näher erläutert. Es zeigt:The invention is explained in more detail below with reference to a drawing using exemplary embodiments. It shows:
Fig. 1 eine Ansicht im Längsschnitt eines Ausführungsbeispiels des erfindungs- gemäßen Rotors, die zur besseren Übersicht keine Schraffur aufweist.1 is a view in longitudinal section of an embodiment of the rotor according to the invention, which has no hatching for a better overview.
Fig. 2 eine gebrochene Querschnittsansicht gemäß Linie ll-ll aus Fig. 1 undFig. 2 is a broken cross-sectional view along line II-II of Fig. 1 and
Fig. 3 eine gebrochene Ansicht im Längsschnitt eines weiteren Ausführungs- beispiels des erfindungsgemäßen Rotors.3 shows a broken view in longitudinal section of a further exemplary embodiment of the rotor according to the invention.
Fig. 1 zeigt einen Längsschnitt eines Ausführungsbeispiels des erfindungsgemäßen Rotors für eine Turbomaschine, der drei Stufen aufweist. Die Stufen sind jeweils mit einer Schaufel 1, 2 und 3 sowie einer ersten Scheibe 4 und zwei benachbarten Scheiben 5,6 versehen. Die erste Scheibe 4 weist an ihren beiden Seitenflächen 7,8 jeweils einen Flansch 9 bzw. 10 auf. Die Flansche 9, 10 erstrecken sich mit einem axialen Abstand A von ihren inneren Seitenflächen 1 1 , 12 zu den Seitenflächen 7,8 der ersten Scheibe 4. Auf diese Weise ist zwischen der ersten Scheibe 4 und den Flanschen 9, 10 ein Zwischenraum Z, der in Radialrichtung nach innen geöffnet ist. Der Abstand A ist möglichst klein zu halten, um die radiale Aufweitung der Flansche 9, 10 bzw. der Flanschverbindung durch den Körper der Scheibe 4 zu begre nzen.Fig. 1 shows a longitudinal section of an embodiment of the rotor according to the invention for a turbomachine, which has three stages. The steps are each provided with a shovel 1, 2 and 3 and a first disk 4 and two adjacent disks 5, 6. The first disc 4 has a flange 9 and 10 on its two side surfaces 7, 8. The flanges 9, 10 extend at an axial distance A from their inner side surfaces 11, 12 to the side surfaces 7, 8 the first disc 4. In this way, between the first disc 4 and the flanges 9, 10 there is an intermediate space Z which is open inwards in the radial direction. The distance A is to be kept as small as possible in order to begin with the radial expansion of the flanges 9, 10 or the flange connection through the body of the disk 4.
Zur lösbaren Verbindung benachbarter Scheiben 5,6 greift ein Querabschnitt 13 e i- nes (Schrauben-)Bolzens 14 in den Zwischenraum Z ein und stützt sich nach dem Verspannen/Verschrauben jeweils an der inneren Seitenfläche, wie z.B. 12, des Flansches 10 ab.For the releasable connection of adjacent disks 5, 6, a transverse section 13 engages a (screw) bolt 14 in the intermediate space Z and is supported on the inner side surface, e.g. 12, the flange 10.
Die zur mittleren, ersten Scheibe 4 benachbarten Scheiben 5,6 weisen jeweils sich im wesentlichen in Axialrichtung erstreckende, zylindrische Schalen 16 auf, die auch kegelförmig ausgebildet sein können. Die Schalen 16 besitzen an Ihren zu den Scheiben 5,6 entfernten Enden jeweils einen zweiten Flansch 17, der jeweils mit den Flanschen 9,10 der ersten Scheibe 4 durch (Schrauben-)Bolzen 14 od.dgl. fest verspannt wird. An die zweiten Flansche 17 der Scheiben 5,6 schließt sich jeweils ein im wesentlichen in Axialrichtung verlaufender Stützabschnitt 18 an, an dem sich die Querabschnitte 13 der Bolzen 14 abstützen können, wodurch ein Verdrehen der Bo lzen 14 verhindert wird. So wird sichergestellt, daß beim Montieren bzw. Anziehen der (Schrauben-)Bolzen 14 keine Druckstellen an den hochbelasteten, ersten Scheiben 4 auftreten.The disks 5, 6 adjacent to the middle, first disk 4 each have cylindrical shells 16 which extend essentially in the axial direction and which can also be conical. The shells 16 have at their ends remote from the disks 5, 6 each a second flange 17, which is connected to the flanges 9, 10 of the first disk 4 by means of (screw) bolts 14 or the like. is firmly clamped. At the second flanges 17 of the disks 5,6 each adjoins a substantially axially extending support section 18, on which the transverse sections 13 of the bolts 14 can be supported, thereby preventing the bolts 14 from rotating. This ensures that no pressure points occur on the highly loaded, first disks 4 when mounting or tightening the (screw) bolts 14.
Zwischen den Flanschen 9, 10 der ersten Scheibe 4 und den Flanschen 17 der be i- den benachbarten Scheiben 5,6 ist jeweils eine Zwischenstufendichtung 19 mit ih- rem Flanschabschnitt 20 eingespannt und lösbar befestigt. Die Zwischenstufendichtungen 19 können alternativ auch integral an den Scheiben 5,6 oder deren Schalen 16 angeordnet sein.Between the flanges 9, 10 of the first disk 4 and the flanges 17 of the two adjacent disks 5, 6, an intermediate stage seal 19 with its flange section 20 is clamped and releasably attached. The intermediate stage seals 19 can alternatively also be arranged integrally on the disks 5, 6 or their shells 16.
Fig. 2 zeigt eine ausgeschnittene und gebrochene Querschnittsansicht gemäß Linie ll-ll aus Fig. 1, in deren oberem Teilausschnitt der Flansch 9 in einer Draufsicht dargestellt ist. Der Flansch 9 ist als Scheibenring ausgebildet, an dessen innerer Stir nfläche bzw. Umfangskante 21 in Radialrichtung nach innen geöffnete, schlitzartige Aussparungen 15 vorgesehen sind. In eine Aussparung 15 ist ein (Schrauben-)Bolzen 14 eingesetzt, dessen Querabschnitt 13 gestrichelt dargestellt ist. Nach dem Mo n- tieren stützt sich dieser an der inneren Seitenfläche 1 1 des Flansches 9 ab. Um ein Verdrehen des (Schrauben-)Bolzens 14 bei der Montage zu verhindern, stützt sich dessen Querabschnitt 13 zudem an dem Stützabschnitt 18 der Schale 16 der b e- nachbarten Scheibe 5 ab. Zwischen den Aussparungen 15 ist jeweils eine Bohrung 22 zur Entlastung vorgesehen, welche den Kerbfaktor infolge der Aussparung 15 herabsetzt. Alternativ können die Bohrungen 22 auch als Langlöcher, weitere Au s- sparungen od.dgl. ausgebildet sein.FIG. 2 shows a cut out and broken cross-sectional view according to line II-II from FIG. 1, in the upper partial section of which the flange 9 is shown in a top view. The flange 9 is designed as a disk ring, on the inner end face or peripheral edge 21 of which is open in the radial direction and slit-like Recesses 15 are provided. In a recess 15, a (screw) bolt 14 is inserted, the cross section 13 is shown in dashed lines. After mounting, it is supported on the inner side surface 11 of the flange 9. In order to prevent the (screw) bolt 14 from rotating during assembly, its transverse section 13 is also supported on the support section 18 of the shell 16 of the adjacent disk 5. Between the cutouts 15 there is a bore 22 for relief, which reduces the notch factor as a result of the cutout 15. Alternatively, the bores 22 can also be used as elongated holes, further cutouts or the like. be trained.
In dem unteren Teilausschnitt aus Fig. 2 ist der scheibenringförmig ausgebildete Flanschabschnitt 20 der Zwischenstufendichtung 19 dargestellt, der Bohrungen 23 aufweist. Die Bohrungen 23 fluchten mit den Aussparungen 15 in den Flanschen 9, 10 der ersten Scheibe 4 ebenso wie entsprechende Bohrungen 24 in den zweiten Flanschen 17 von den zur ersten Scheibe 4 benachbarten Scheiben 5,6. Wie in Fig. 2 zu erkennen ist, sind die Bohrungen 23 in dem Flanschabschnitt 20 der Zwischenstufendichtung 19 radial nach innen geöffnet, wobei ihr Öffnungsmaß kleiner als ihr Durchmesser ist, um so eine radiale Fixierung der (Schrauben-)Bolzen 14 bei der Montage zu gewährleisten. Alternativ können die Bohrungen 23 auch als geschlos- sene Bohrungen ausgebildet sein.In the lower partial section from FIG. 2, the disk-ring-shaped flange section 20 of the intermediate stage seal 19 is shown, which has bores 23. The bores 23 are aligned with the cutouts 15 in the flanges 9, 10 of the first disk 4, as are corresponding bores 24 in the second flanges 17 from the disks 5, 6 adjacent to the first disk 4. As can be seen in FIG. 2, the bores 23 in the flange section 20 of the intermediate stage seal 19 are opened radially inward, their opening dimension being smaller than their diameter, so as to radially fix the (screw) bolts 14 during assembly guarantee. Alternatively, the bores 23 can also be designed as closed bores.
Weist ein Rotor mehr als drei Stufen auf, so wird jede zweite Stufe mit einer weni g- stens einen Flansch 9 bzw. 10 aufweisenden ersten Scheibe 4 versehen.If a rotor has more than three stages, every second stage is provided with a first disc 4 having at least one flange 9 or 10.
Fig. 3 zeigt ein weiteres Ausführungsbeispiel des erfindungsgemäßen Rotors, bei dem der Radius R an dem Übergang zwischen der inneren Seitenfläche 8 der ersten Scheibe 4 und dem Flansch 10 bzw. dessen innerer Seitenfläche 12 aus Festigkeit sgründen vergrößert ist. Da als Folge der Abstand A zwischen der Seitenfläche 8 der ersten Scheibe 4 und der inneren Seitenfläche 12 des Flansches 10 größer ist, weist der (Schrauben-)Bolzen 14 einen Scherungsring oder Bund 25 auf, der auf einer äußeren Seitenfläche 26 des Flansches 10 aufliegt und eine axiale Verschiebung des (Schrauben-)Bolzens 14 verhindert, damit die Querabschnitte 13 bei der Montage nicht gegen die erste Scheibe 4 gedrückt werden und ihre Sicherung gegen Verdr ehen verlieren. Fig. 3 shows a further embodiment of the rotor according to the invention, in which the radius R at the transition between the inner side surface 8 of the first disc 4 and the flange 10 or its inner side surface 12 is increased for reasons of strength. As a result, the distance A between the side surface 8 of the first disk 4 and the inner side surface 12 of the flange 10 is greater, the (screw) bolt 14 has a shear ring or collar 25 which rests on an outer side surface 26 of the flange 10 and prevents axial displacement of the (screw) bolt 14, so that the cross sections 13 during assembly not be pressed against the first disc 4 and lose their security against twisting.

Claims

Patentansprüche claims
1. Rotor für eine Turbomaschine, mit wenigstens zwei beschaufelten Stufen, deren Scheiben (4, 5, 6) lösbar miteinander verbunden sind, dadurch gekennzeichnet, daß eine erste Scheibe (4) wenigstens an einer Seitenfläche (7, 8) einen mit se i- ner inneren Seitenfläche (1 1,12) möglichst gering dazu beabstandeten, ersten Flansch (9, 10) aufweist, der mit einem zweiten Flansch ( 17) einer benachbarten Scheibe (5, 6) durch jeweils einen Querabschnitt (13) aufweisende Bolzen (14) verbunden ist, wobei sich die Querabschnitte (13) nach dem Montieren an der i n- neren Seitenfläche ( 1 1, 12) des ersten Flansches (9,10) a bstützen.1. Rotor for a turbomachine, with at least two bladed stages, the disks (4, 5, 6) are detachably connected to each other, characterized in that a first disk (4) at least on one side surface (7, 8) one with se i - Has an inner side surface (1, 1, 12) spaced as small as possible from the first flange (9, 10), which has a second flange (17) of an adjacent washer (5, 6) with a cross section (13) each having bolts ( 14) is connected, the cross sections (13) being supported on the inner side surface (11, 12) of the first flange (9, 10) after mounting.
2. Rotor nach Anspruch 1, dadurch gekennzeichnet, daß sich der erste Flansch (9, 10) mit axialem Abstand (A) zur Seitenfläche (7,8) der ersten Scheibe (4) radial nach innen erstreckt.2. Rotor according to claim 1, characterized in that the first flange (9, 10) with an axial distance (A) to the side surface (7,8) of the first disc (4) extends radially inwards.
3. Rotor nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß der erste Flansch (9,10) als Scheibenring ausgebildet ist, der entlang seiner inneren Umfangskante (21) Aussparungen ( 15) aufweist.3. Rotor according to claim 1 or 2, characterized in that the first flange (9, 10) is designed as a disk ring which has cutouts (15) along its inner peripheral edge (21).
4. Rotor nach Anspruch 3, dadurch gekennzeichnet, daß die Aussparungen (15) radial nach innen geöffnet sind.4. Rotor according to claim 3, characterized in that the recesses (15) are opened radially inwards.
5. Rotor nach Anspruch 3 oder 4, dadurch gekennzeichnet, daß die Aussparungen (15) äquidistant angeordnet sind.5. Rotor according to claim 3 or 4, characterized in that the recesses (15) are arranged equidistantly.
6. Rotor nach einem oder mehreren der Ansprüche 3 bis 5, dadurch gekennzeichnet, daß der Scheibenring (9, 10) zwischen den Aussparungen ( 15) jeweils eine Bo Irrung oder Aussparung (22) aufweist. 6. Rotor according to one or more of claims 3 to 5, characterized in that the disc ring (9, 10) between the recesses (15) each has a Bo error or recess (22).
7. Rotor nach einem oder mehreren der Ansprüche 3 bis 6, dadurch gekennzeichnet, daß der zweite Flansch (17) einer benachbarten Scheibe (5,6) zu den Aussparu n- gen (15) des ersten Flansches (9, 10) fluchtende Bohrungen (24) aufweist.7. Rotor according to one or more of claims 3 to 6, characterized in that the second flange (17) of an adjacent disk (5, 6) to the recesses (15) of the first flange (9, 10) are aligned bores (24).
8. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g e- kennzeichnet, daß ein Flanschabschnitt (20) einer Zwischenstufendichtung (19) jeweils zwischen dem ersten und zweiten Flansch (9, 10 bzw. 17) eingeklemmt ist.8. Rotor according to one or more of the preceding claims, characterized in that a flange section (20) of an interstage seal (19) is in each case clamped between the first and second flange (9, 10 and 17).
9. Rotor nach Anspruch 8, dadurch gekennzeichnet, daß der Flanschabschnitt (20) der Zwischenstufendichtung (19) zu den Aussparungen (15) des ersten Flansches (9, 10) fluchtende Bohrungen (23) aufweist.9. Rotor according to claim 8, characterized in that the flange portion (20) of the intermediate stage seal (19) to the recesses (15) of the first flange (9, 10) has aligned bores (23).
10. Rotor nach Anspruch 9, dadurch gekennzeichnet, daß die Bohrungen (23) die Bolzen ( 14) in Radialrichtung fixieren.10. Rotor according to claim 9, characterized in that the bores (23) fix the bolts (14) in the radial direction.
1 1. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g ekennzeichnet, daß die Bolzen (14) an ihren der ersten Scheibe (4) zugewandten Enden einen sich rechtwinklig zu ihrer Längsachse erstreckenden Querabschnitt (13) aufweisen.1 1. Rotor according to one or more of the preceding claims, characterized in that the bolts (14) at their ends facing the first disc (4) have a cross section (13) extending at right angles to their longitudinal axis.
12. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g e- kennzeichnet, daß die Bolzen ( 14) T-Kopfbolzen sind.12. Rotor according to one or more of the preceding claims, characterized in that the bolts (14) are T-head bolts.
13. Rotor nach Anspruch 1 1 oder 12, dadurch gekennzeichnet, daß der Abstand (A) des ersten Flansches (9, 10) zur Seitenfläche (7,8) der ersten Scheibe (4) größer als die Stärke des Querabschnitts (13) ist.13. A rotor according to claim 1 1 or 12, characterized in that the distance (A) of the first flange (9, 10) to the side surface (7,8) of the first disc (4) is greater than the thickness of the transverse section (13) .
14. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g ekennzeichnet, daß der zweite Flansch (17) einer benachbarten Scheibe (5,6) ein sich im wesentlichen in Axialrichtung erstreckenden Stützabschnitt (18) aufweist. 14. Rotor according to one or more of the preceding claims, characterized in that the second flange (17) of an adjacent disk (5, 6) has a support section (18) extending essentially in the axial direction.
15. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g ekennzeichnet, daß der Bolzen (14) einen Bund (25) aufweist, der sich an eine ä u- ßere Seitenfläche (26) des ersten Flansches (9,10) abstützt.15. Rotor according to one or more of the preceding claims, characterized in that the bolt (14) has a collar (25) which is supported on an outer side surface (26) of the first flange (9, 10).
16. Rotor nach einem oder mehreren der vorhergehenden Ansprüche, dadurch g e- kennzeichnet, daß die erste Scheibe (4) an beiden Seitenflächen (7,8) einen e r- sten Flansch (9,10) aufweist. 16. Rotor according to one or more of the preceding claims, characterized in that the first disk (4) has a first flange (9, 10) on both side surfaces (7, 8).
EP99939943A 1998-06-27 1999-06-24 Rotor for a turbomachine Expired - Lifetime EP1092081B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19828817A DE19828817C2 (en) 1998-06-27 1998-06-27 Rotor for a turbo machine
DE19828817 1998-06-27
PCT/DE1999/001840 WO2000000719A1 (en) 1998-06-27 1999-06-24 Rotor for a turbomachine

Publications (2)

Publication Number Publication Date
EP1092081A1 true EP1092081A1 (en) 2001-04-18
EP1092081B1 EP1092081B1 (en) 2003-07-30

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EP99939943A Expired - Lifetime EP1092081B1 (en) 1998-06-27 1999-06-24 Rotor for a turbomachine

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US (1) US6499957B1 (en)
EP (1) EP1092081B1 (en)
JP (1) JP2002519564A (en)
CA (1) CA2335964A1 (en)
DE (2) DE19828817C2 (en)
WO (1) WO2000000719A1 (en)

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Also Published As

Publication number Publication date
CA2335964A1 (en) 2000-01-06
WO2000000719A1 (en) 2000-01-06
DE19828817A1 (en) 1999-12-30
JP2002519564A (en) 2002-07-02
DE59906444D1 (en) 2003-09-04
US6499957B1 (en) 2002-12-31
DE19828817C2 (en) 2000-07-13
EP1092081B1 (en) 2003-07-30

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