WO2007065411A1 - Turbomachine having axial rotor blade securing - Google Patents

Turbomachine having axial rotor blade securing Download PDF

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Publication number
WO2007065411A1
WO2007065411A1 PCT/DE2006/002150 DE2006002150W WO2007065411A1 WO 2007065411 A1 WO2007065411 A1 WO 2007065411A1 DE 2006002150 W DE2006002150 W DE 2006002150W WO 2007065411 A1 WO2007065411 A1 WO 2007065411A1
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WO
WIPO (PCT)
Prior art keywords
rotor
axial direction
blade ring
base body
sealing element
Prior art date
Application number
PCT/DE2006/002150
Other languages
German (de)
French (fr)
Inventor
Wilfried Weidmann
Moritz Wirth
Original Assignee
Mtu Aero Engines 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 Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Priority to US12/096,759 priority Critical patent/US20090028712A1/en
Priority to EP06818118A priority patent/EP1957755A1/en
Publication of WO2007065411A1 publication Critical patent/WO2007065411A1/en

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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
    • F01D5/30—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of patent claim 1.
  • Turbomachines in particular gas turbines, have a plurality of rotor blades positioned one behind the other in the axial direction, both in the region of a turbine and in the region of a compressor, each rotor blade ring having an in particular disk-shaped rotor base body and a plurality of rotor blades rotating with the rotor base body.
  • the present invention relates to a turbomachine, in particular a gas turbine, in which the rotor blades of the rotor blade rings are fastened via their blade feet in grooves which run essentially in the axial direction of the basic rotor body, that is to say in so-called axial grooves.
  • the rotor blades of the rotor blade rings must be secured in their assembly position or their anchoring position in the axial grooves of the basic rotor body against displacement in the axial direction.
  • wire locks are usually used to axially secure the rotor blades of a rotor blade ring, which are fastened via their blade feet in axial grooves of a rotor base body.
  • a wire-shaped locking element is threaded into a groove which is formed between the blade roots of the rotor blades and the rotor base body, in order to secure the rotor blades against displacement in the axial direction.
  • a separate wire-shaped securing element is usually used for each rotor blade, which causes complex assembly of the wire securing devices.
  • wire fuses are subject to tolerances.
  • locking plates are used, which are also referred to as locking plates or locking plates.
  • Such locking plates are guided both in an annular groove of the basic rotor body and in an annular groove of the rotor blades anchored in the basic rotor body.
  • Such locking plates increase the load on the blade root of the moving blades and thus the edge loads that occur.
  • the present invention is based on the problem of creating a new type of turbomachine.
  • This problem is solved in that the turbomachine mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.
  • the rotor blades of at least one rotor blade ring have hook-like securing elements which, in the anchoring position, bear against the rotor base body of the rotor blade body in the anchoring position, the hook-like securing elements between the rotor base body of the rotor blade ring and a sealing element which is located between the rotor base body and a rotor base body Low pressure side adjoining blade ring extends, are fixed on both sides in the axial direction.
  • the rotor blades to be secured in their axial position have hook-like securing elements which are fixed on both sides between the rotor base body of the respective rotor blade ring and the sealing element by clamping.
  • This provides a completely new type of protection of rotor blades guided in axial grooves against unintentional displacement in the axial direction, which is characterized by simple assembly and disassembly and by means of which leakage flows in the radially inner region of the rotor blade rings can be minimized.
  • the axial securing of the rotor blades according to the invention does not increase the load acting on the blade roots of the rotor blades.
  • the sealing element is preferably fastened in a bayonet-like manner to the rotor base body of the rotor blade ring, the rotor blades of which are to be secured against displacement in the axial direction, via a section adjacent to the hook-like securing elements, this section of the sealing element fixing the hook-like securing elements of the rotor blades in the axial direction on both sides.
  • Fig. 2 a section of a gas turbine according to the invention according to a second embodiment of the invention.
  • FIG. 1 shows a section of a turbine 10 of a gas turbine according to the invention, namely a gas turbine aircraft engine, in the area of two rotating rotor blade rings 11, 12 arranged one behind the other in the axial direction, a fixed guide blade ring 13 being arranged between the two rotor blade rings 11, 12 shown.
  • the turbine 10 is flowed through in the direction of arrow 14 shown in FIG. 1 in the axial direction.
  • Each of the two rotor blade rings 11, 12 shown in FIG. 1 has a preferably disk-shaped rotor base body 15 or 16, with rotor blades 17 or 18 of the rotor blade rings 11 or 12 via blade feet 19 or 20 in so-called axial grooves of the respective rotor base body 15 or 16 are attached or anchored.
  • the axial grooves of the basic rotor bodies 15 and 16, in which the rotor blades 17 and 18 are anchored via their blade feet 19 and 20, run essentially in the axial direction of the turbine 10.
  • Radially close to the blade feet 19, 20 of the rotor blades 17, 18 External blades 21, 22, wherein blade root platforms 23, 24 are formed between the blade roots 19, 20 and the blade blades 21, 22 of the moving blades 17, 18.
  • the guide vane ring 13 positioned between the two rotor blade rings 11, 12 comprises a plurality of fixed guide vanes 25, a platform 27 being formed on a radially inner end of the airfoil blades 26 of the fixed guide vanes 25, on which a seal 28 in the form of the embodiment in FIG. 1 is formed a brush seal is attached, but other types of seals can be used.
  • the stator-side seal 28 interacts with a rotor-side sealing element 29 positioned between the two rotor blade rings 11, 12, so as to seal a radially inner gap between the rotating rotor blade rings 11, 12 and the fixed guide blade ring 13.
  • the rotor blades 17 of the rotor blade ring 11 are assigned hook-like securing elements 30, which in the anchoring position on a low-pressure side of the rotor blade ring 11 bear against the rotor base body 15 of the same.
  • the securing elements 30 are assigned to the blade feet 19 of the rotor blades 17 and rest with a radially inner section 31 on the rotor base body 15 of the rotor blade ring 11.
  • the hook-like securing elements 30 are axially secured on both sides in the axial direction between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29, which extends between the rotor base body 15 of the rotor blade ring 11 and the rotor base body 16 of the rotor blade ring 12 which adjoins on the low-pressure side. 1, the hook-like securing elements 30 are clamped on both sides between the rotor base body 15 of the rotor blade ring 11, which includes the rotor blades 17 to be secured with regard to their axial position, and the rotor-side sealing element 29.
  • the rotor-side sealing element 29 is fastened in a bayonet-like manner to the rotor base body 15 of the rotor blade ring 11 via a section 32, which is positioned adjacent to the hook-like securing elements 30 of the rotor blades 17.
  • the section 32 of the sealing element 29 has a nose-like projection 33, which can be inserted into a groove 34 of the basic rotor body 15 in the axial direction via an opening (not shown).
  • the sealing element 29 can be rotated in the circumferential direction, in order for the bayonet-type fastening of the sealing element 29 on the rotor base body 15 of the rotor blade ring 11, the rotor blades 17 of which to be displaced in the axial direction are to be secured.
  • the hook-like securing elements 30 are clamped between the rotor base body 15 and the sealing element 29, in order to fix the rotor blades 17 and 18 on both sides.
  • FIG. 2 shows a further exemplary embodiment of a gas turbine according to the invention, a section of a turbine 35 also being shown in the exemplary embodiment of FIG. 2.
  • the embodiment of FIG. 2 corresponds in many details to the embodiment of FIG. 1, so that the same reference numbers are used to avoid unnecessary repetitions for the same modules. In the following, only the details are dealt with, by which the embodiment of FIG. 2 differs from the embodiment of FIG. 1.
  • the rotor blades 17 have hook-like securing elements 30 which, in the anchoring position, bear against the rotor base body 15 on a low-pressure side of the rotor blade ring 11.
  • the hook-like securing elements 30 are in turn fixed between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29 in the axial direction, the sealing element 29 being located between the rotor base body 15 of the rotor blade ring 11, the rotor blades of which are to be secured against displacement in the axial direction, and the rotor base body 16 of the rotor blade ring 12 adjoining on the low pressure side extends.
  • the sealing element 29 is not connected in a bayonet-like manner to the basic rotor body 15 of the rotor blade ring 11, as in the exemplary embodiment in FIG. 1, rather a projection 36 of the sealing element 29 is between two flanges 37 and 38 of the basic rotor bodies 15 and 12 positioned one behind the other in the axial direction 16 fastened by screwing.
  • a section 39 of the sealing element 29 adjoining the projection 36 serves to fix the hook-like securing elements 30 on both sides between the rotor base body 15 and the sealing element 29, in order to prevent the blades 17 of the rotor blade ring 11 from being moved unintentionally in the axial direction.
  • rotor blades of rotor blade rings which are guided in axial grooves are thus secured against unwanted axial displacement by fixing hook-like securing elements associated with the blade roots of the rotor blades between the rotor base body of the rotor blade ring and a rotor-side sealing element of a so-called inner air seal seal, namely on both sides in the axial direction, with all the blades of two adjacent rotor blade rings 11 and 12 being axially secured by a component 29.
  • the sealing element is preferably attached to the corresponding rotor base body in a bayonet-like manner.
  • the invention has the advantage that rotor blades can be assembled and disassembled on the rotor base body relatively easily. All the blades of a blade ring can be fixed together in the axial direction using a sealing element.

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

Abstract

The rotor of a turbomachine, in particular a gas turbine rotor, is proposed, having a plurality of rotor blade rings (11, 12) which are positioned behind one another in the axial direction and are assigned to a turbine or a compressor, wherein each rotor blade ring has a rotor basic body (15, 16) having a plurality of rotor blades (17, 18), and wherein the rotor blades of a rotor blade ring are anchored via blade roots (19, 20) in axial grooves of the respective rotor basic body which extend substantially in the axial direction, and are secured in their anchoring position in the rotor basic body against a displacement in the axial direction. The rotor blades (17) of at least one rotor blade ring (11) have hook-like securing elements (30) which, in the anchoring position, bear against the rotor basic body (15) of the rotor blade ring (11) on a low-pressure side of said rotor blade ring (11), wherein the hook-like securing elements (30) are fixed on both sides in the axial direction between the rotor basic body (15) of the rotor blade ring (11) and a sealing element (29) which extends between the rotor basic body (15) and a rotor basic body (16) of a rotor blade ring (12) which adjoins it on the low-pressure side.

Description

TURBOMASCHINE MIT AXIALER LAUFSCHAUFELSICHERUNG  TURBO MACHINE WITH AXIAL BLADE LOCKER
Die Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, nach dem Oberbegriff des Patentanspruchs 1. The invention relates to a turbomachine, in particular a gas turbine, according to the preamble of patent claim 1.
Turbomaschinen, insbesondere Gasturbinen, weisen sowohl im Bereich einer Turbine als auch im Bereich eines Verdichters mehrere in Axialrichtung hintereinander positionierte Laufschaufelkränze auf, wobei jeder Lauf- schaufelkranz einen insbesondere scheibenförmigen Rotorgrundkörper und mehrere mit dem Rotorgrundkörper rotierende Laufschaufeln aufweist. Die hier vorliegende Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, bei welchem die Laufschaufeln der Laufschaufelkränze über ihre Schaufelfüße in Nuten, die im wesentlichen in Axialrichtung des Rotorgrundkörpers verlaufen, also in sogenannten Axialnuten, befestigt sind. Die Laufschaufeln der Laufschaufelkränze müssen dabei in ihrer Montageposition bzw. ihrer Verankerungsposition in den Axialnuten des Rotorgrundkörpers vor einer Verschiebung in Axialrichtung gesichert werden. Turbomachines, in particular gas turbines, have a plurality of rotor blades positioned one behind the other in the axial direction, both in the region of a turbine and in the region of a compressor, each rotor blade ring having an in particular disk-shaped rotor base body and a plurality of rotor blades rotating with the rotor base body. The present invention relates to a turbomachine, in particular a gas turbine, in which the rotor blades of the rotor blade rings are fastened via their blade feet in grooves which run essentially in the axial direction of the basic rotor body, that is to say in so-called axial grooves. The rotor blades of the rotor blade rings must be secured in their assembly position or their anchoring position in the axial grooves of the basic rotor body against displacement in the axial direction.
Zur Axialsicherung der über ihre Schaufelfüße in Axialnuten eines Rotorgrundkörpers befestigten Laufschaufeln eines Laufschaufelkranzes kommen in der Praxis üblicherweise sogenannte Drahtsicherungen zum Einsatz. Bei derartigen Drahtsicherungen wird ein drahtförmiges Sicherungselement in eine Nut, die zwischen den Schaufelfüßen der Laufschaufeln und dem Rotorgrundkörper ausgebildet ist, eingefädelt, um so die Laufschaufeln vor einer Verschiebung in Axialrichtung zu sichern. Je Laufschaufei kommt dabei üblicherweise ein separates drahtförmiges Sicherungselement zum Einsatz, wodurch eine aufwendige Montage der Drahtsicherungen verursacht wird. Des Weiteren sind Drahtsicherungen toleranzbehaftet. In practice, so-called wire locks are usually used to axially secure the rotor blades of a rotor blade ring, which are fastened via their blade feet in axial grooves of a rotor base body. In the case of such wire locks, a wire-shaped locking element is threaded into a groove which is formed between the blade roots of the rotor blades and the rotor base body, in order to secure the rotor blades against displacement in the axial direction. A separate wire-shaped securing element is usually used for each rotor blade, which causes complex assembly of the wire securing devices. Furthermore, wire fuses are subject to tolerances.
Bei einer weiteren aus dem Stand der Technik bekannten Variante zur Axialsicherung der Laufschaufeln finden sogenannte Sicherungsbleche Verwendung, die auch als Verschlussplättchen bzw. als locking plates bezeichnet werden. Derartige Sicherungsbleche sind sowohl in einer Ringnut des Rotorgrundkörpers als auch in einer Ringnut der im Rotorgrundkörper verankerten Laufschaufeln geführt. Derartige Sicherungsbleche erhöhen die Belastung auf den Schaufelfuß der Laufschaufeln und damit die auftretenden Randlasten. In a further variant known from the prior art for axially securing the rotor blades, so-called locking plates are used, which are also referred to as locking plates or locking plates. Such locking plates are guided both in an annular groove of the basic rotor body and in an annular groove of the rotor blades anchored in the basic rotor body. Such locking plates increase the load on the blade root of the moving blades and thus the edge loads that occur.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Turbomaschine zu schaffen. Dieses Problem wird dadurch gelöst, dass die eingangs genannte Turbomaschine durch die Merkmale des kennzeichnenden Teils des Patentanspruchs 1 weitergebildet ist. Erfindungsgemäß weisen die Laufschaufeln zumindest eines Laufschaufelkranzes hakenartige Sicherungselemente auf, die in der Verankerungsposition auf einer Niederdruckseite des Laufschaufelkranzes am Rotorgrundkörper desselben anliegen, wobei die hakenartigen Sicherungselemente zwischen dem Rotorgrundkörper des Laufschaufelkranzes und einem Dichtungselement, welches sich zwischen dem Rotorgrundkörper und einem Rotorgrundkörper eines sich auf der Niederdruckseite anschließenden Laufschaufelkranzes erstreckt, in Axialrichtung beidseitig fixiert sind. Proceeding from this, the present invention is based on the problem of creating a new type of turbomachine. This problem is solved in that the turbomachine mentioned at the outset is further developed by the features of the characterizing part of patent claim 1. According to the invention, the rotor blades of at least one rotor blade ring have hook-like securing elements which, in the anchoring position, bear against the rotor base body of the rotor blade body in the anchoring position, the hook-like securing elements between the rotor base body of the rotor blade ring and a sealing element which is located between the rotor base body and a rotor base body Low pressure side adjoining blade ring extends, are fixed on both sides in the axial direction.
Im Sinne der hier vorliegenden Erfindung verfügen die in ihrer Axialposition zu sichernden Laufschaufeln über hakenartige Sicherungselemente, die zwischen dem Rotorgrundkörper des jeweiligen Laufschaufelkranzes und dem Dichtungselement durch Klemmen beidseitig fixiert sind. Hierdurch wird eine völlig neuartige Sicherung von in Axialnuten geführten Laufschaufeln gegenüber einer unbeabsichtigten Verschiebung in Axialrichtung bereitgestellt, die durch eine einfache Montage sowie Demontage gekennzeichnet ist, und mit Hilfe derer weiterhin Leckageströmungen im radial innen liegenden Bereich der Laufschaufelkränze minimiert werden können. Des Weiteren wird durch die erfindungsgemäße Axialsicherung der Laufschaufeln die auf die Schaufelfüße derselben wirkende Belastung nicht erhöht. For the purposes of the present invention, the rotor blades to be secured in their axial position have hook-like securing elements which are fixed on both sides between the rotor base body of the respective rotor blade ring and the sealing element by clamping. This provides a completely new type of protection of rotor blades guided in axial grooves against unintentional displacement in the axial direction, which is characterized by simple assembly and disassembly and by means of which leakage flows in the radially inner region of the rotor blade rings can be minimized. Furthermore, the axial securing of the rotor blades according to the invention does not increase the load acting on the blade roots of the rotor blades.
Vorzugsweise ist das Dichtungselement über einen den hakenartigen Sicherungselementen benachbarten Abschnitt bajonettartig am Rotorgrundkörper des Laufschaufelkranzes, dessen Laufschaufeln vor einer Verschiebung in Axialrichtung zu sichern sind, befestigt, wobei dieser Abschnitt des Dichtungselements die hakenartigen Sicherungselemente der Laufschaufeln in Axialrichtung beidseitig fixiert. The sealing element is preferably fastened in a bayonet-like manner to the rotor base body of the rotor blade ring, the rotor blades of which are to be secured against displacement in the axial direction, via a section adjacent to the hook-like securing elements, this section of the sealing element fixing the hook-like securing elements of the rotor blades in the axial direction on both sides.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt: Preferred developments of the invention result from the subclaims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted to this. It shows:
Fig. 1: einen Ausschnitt aus einer erfindungsgemäßen Gasturbine nach einem ersten Ausführungsbeispiel der Erfindung; und1: a section of a gas turbine according to the invention according to a first embodiment of the invention; and
Fig. 2: einen Ausschnitt aus einer erfindungsgemäßen Gasturbine nach einem zweiten Ausführungsbeispiel der Erfindung. Fig. 2: a section of a gas turbine according to the invention according to a second embodiment of the invention.
Fig. 1 zeigt einen Ausschnitt aus einer Turbine 10 einer erfindungsgemäßen Gasturbine, nämlich eines Gasturbinenflugtriebwerks, im Bereich von zwei in Axialrichtung hintereinander angeordneten, rotierenden Laufschaufelkränzen 11, 12, wobei zwischen den beiden dargestellten Laufschaufelkränzen 11, 12 ein feststehender Leitschaufelkranz 13 angeordnet ist. Die Turbine 10 wird in Richtung des in Fig. 1 dargestellten Pfeils 14 in Axialrichtung durchströmt . 1 shows a section of a turbine 10 of a gas turbine according to the invention, namely a gas turbine aircraft engine, in the area of two rotating rotor blade rings 11, 12 arranged one behind the other in the axial direction, a fixed guide blade ring 13 being arranged between the two rotor blade rings 11, 12 shown. The turbine 10 is flowed through in the direction of arrow 14 shown in FIG. 1 in the axial direction.
Jeder der beiden in Fig. 1 dargestellten Laufschaufelkränze 11, 12 verfügt über einen vorzugsweise scheibenförmigen Rotorgrundkörper 15 bzw. 16, wobei Laufschaufeln 17 bzw. 18 der Laufschaufelkränze 11 bzw. 12 über Schaufelfüße 19 bzw. 20 in sogenannten Axialnuten des jeweiligen Rotorgrundkörpers 15 bzw. 16 befestigt bzw. verankert sind. Die Axialnuten der Rotorgrundkörper 15 bzw. 16, in welchen die Laufschaufeln 17 bzw. 18 über ihre Schaufelfüße 19 bzw. 20 verankert sind, verlaufen im Wesentlichen in Axialrichtung der Turbine 10. An die Schaufelfüße 19, 20 der Laufschaufeln 17, 18 schließen sich radial außen Schaufelblätter 21, 22 an, wobei zwischen den Schaufelfüßen 19, 20 und den Schaufelblättern 21, 22 der Laufschaufeln 17, 18 Schaufelfußplattformen 23, 24 ausgebildet sind. Each of the two rotor blade rings 11, 12 shown in FIG. 1 has a preferably disk-shaped rotor base body 15 or 16, with rotor blades 17 or 18 of the rotor blade rings 11 or 12 via blade feet 19 or 20 in so-called axial grooves of the respective rotor base body 15 or 16 are attached or anchored. The axial grooves of the basic rotor bodies 15 and 16, in which the rotor blades 17 and 18 are anchored via their blade feet 19 and 20, run essentially in the axial direction of the turbine 10. Radially close to the blade feet 19, 20 of the rotor blades 17, 18 External blades 21, 22, wherein blade root platforms 23, 24 are formed between the blade roots 19, 20 and the blade blades 21, 22 of the moving blades 17, 18.
Der zwischen den beiden Laufschaufelkränzen 11, 12 positionierte Leitschaufelkranz 13 umfasst mehrere feststehende Leitschaufeln 25, wobei an einem radial innen liegenden Ende von Schaufelblättern 26 der feststehenden Leitschaufeln 25 eine Plattform 27 ausgebildet ist, an welcher im Ausführungsbeispiel der Fig. 1 eine Dichtung 28 in Form einer Bürstendichtung befestigt ist, wobei auch anderen Dichtungsarten verwendbar sind. Die statorseitige Dichtung 28 wirkt gemäß Fig. 1 mit einem zwischen den beiden Laufschaufelkränzen 11, 12 positionierten, rotorseitigen Dichtungselement 29 zusammen, um so einen radial innen liegenden Spalt zwischen den rotierenden Laufschaufelkränzen 11, 12 und dem feststehenden Leitschaufelkranz 13 abzudichten. The guide vane ring 13 positioned between the two rotor blade rings 11, 12 comprises a plurality of fixed guide vanes 25, a platform 27 being formed on a radially inner end of the airfoil blades 26 of the fixed guide vanes 25, on which a seal 28 in the form of the embodiment in FIG. 1 is formed a brush seal is attached, but other types of seals can be used. According to FIG. 1, the stator-side seal 28 interacts with a rotor-side sealing element 29 positioned between the two rotor blade rings 11, 12, so as to seal a radially inner gap between the rotating rotor blade rings 11, 12 and the fixed guide blade ring 13.
Zur Sicherung der Laufschaufeln 17 des Laufschaufelkranzes 11 in ihrer Verankerungsposition in den Axialnuten des entsprechenden Rotorgrundkörpers 15 und demnach zur Sicherung derselben vor einer ungewollten Verschiebung in Axialrichtung sind den Laufschaufeln 17 des Laufschaufel- kranzes 11 hakenartige Sicherungselemente 30 zugeordnet, die in der Verankerungsposition auf einer Niederdruckseite des Laufschaufelkranzes 11 am Rotorgrundkörper 15 desselben anliegen. Wie Fig. 1 entnommen werden kann, sind die Sicherungselemente 30 den Schaufelfüßen 19 der Laufschaufeln 17 zugeordnet und liegen mit einem radial innen liegenden Abschnitt 31 am Rotorgrundkörper 15 des Laufschaufelkranzes 11 an. Die hakenartigen Sicherungselemente 30 sind zur Axialsicherung der Laufschaufeln 11 zwischen dem Rotorgrundkörper 15 des Laufschaufelkranzes 11 und dem Dichtungselement 29, welches sich zwischen dem Rotorgrundkörper 15 des Laufschaufelkranzes 11 und dem Rotorgrundkörper 16 des sich auf der Niederdruckseite anschließenden Laufschaufelkranzes 12 erstreckt, in Axialrichtung beidseitig fixiert. Gemäß Fig. 1 werden die hakenartigen Sicherungselemente 30 zwischen dem Rotorgrundkörper 15 des Laufschaufel- kranzes 11, der die hinsichtlich ihrer Axialposition zu sichernden Laufschaufeln 17 umfasst, und dem rotorseitigen Dichtungselement 29 beidseitig geklemmt. To secure the rotor blades 17 of the rotor blade ring 11 in their anchoring position in the axial grooves of the corresponding rotor base body 15 and accordingly to secure the rotor blades against undesired displacement in the axial direction, the rotor blades 17 of the rotor blade ring 11 are assigned hook-like securing elements 30, which in the anchoring position on a low-pressure side of the rotor blade ring 11 bear against the rotor base body 15 of the same. As can be seen in FIG. 1, the securing elements 30 are assigned to the blade feet 19 of the rotor blades 17 and rest with a radially inner section 31 on the rotor base body 15 of the rotor blade ring 11. The hook-like securing elements 30 are axially secured on both sides in the axial direction between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29, which extends between the rotor base body 15 of the rotor blade ring 11 and the rotor base body 16 of the rotor blade ring 12 which adjoins on the low-pressure side. 1, the hook-like securing elements 30 are clamped on both sides between the rotor base body 15 of the rotor blade ring 11, which includes the rotor blades 17 to be secured with regard to their axial position, and the rotor-side sealing element 29.
Im Ausführungsbeispiel der Fig. 1 ist das rotorseitige Dichtungselement 29 über einen Abschnitt 32, der benachbart zu den hakenartigen Sicherungselementen 30 der Laufschaufeln 17 positioniert ist, bajonettartig am Rotorgrundkörper 15 des LaufSchaufelkranzes 11 befestigt. Der Abschnitt 32 des Dichtungselements 29 verfügt über einen nasenartigen Vorsprung 33, der über eine nicht-dargestellte Öffnung in eine Nut 34 des Rotorgrundkörpers 15 in Axialrichtung einführbar ist. Nach Einführung des Vorsprungs 33 des Dichtungselements 29 über die Öffnung in die Nut 34 des Rotorgrundkörpers 15 ist das Dichtungselement 29 in Umfangsrichtung drehbar, um so die bajonettartige Befestigung des Dichtungselements 29 am Rotorgrundkörper 15 des Laufschaufelkranzes 11, dessen Laufschaufeln 17 vor einer Verschiebung in Axialrichtung zu sichern sind, zu befestigen. Bei Drehung in Umfangsrichtung zur bajonettartigen Befestigung des Dichtungselements 29 am Rotorgrundkörper 15 des Laufschaufelkranzes 11 werden die hakenartigen Sicherungselemente 30 zwischen dem Rotorgrundkörper 15 und dem Dichtungselement 29 geklemmt, um so die Laufschaufeln 17 und 18 beidseitig zu fixieren. Der Abschnitt 32 des Dichtungselements 29, welcher der bajonettartigen Befestigung des Dichtungselements 29 am Rotorgrundkörper 15 des Laufschaufelkranzes 11 dient, fixiert über die hakenartigen Sicherungselemente 30 die Laufschaufeln 11 beidseitig in Axialrichtung. In the exemplary embodiment in FIG. 1, the rotor-side sealing element 29 is fastened in a bayonet-like manner to the rotor base body 15 of the rotor blade ring 11 via a section 32, which is positioned adjacent to the hook-like securing elements 30 of the rotor blades 17. The section 32 of the sealing element 29 has a nose-like projection 33, which can be inserted into a groove 34 of the basic rotor body 15 in the axial direction via an opening (not shown). After the projection 33 of the sealing element 29 has been introduced via the opening into the groove 34 of the rotor base body 15, the sealing element 29 can be rotated in the circumferential direction, in order for the bayonet-type fastening of the sealing element 29 on the rotor base body 15 of the rotor blade ring 11, the rotor blades 17 of which to be displaced in the axial direction are to be secured. When rotating in the circumferential direction for the bayonet-like fastening of the sealing element 29 to the rotor base body 15 of the rotor blade ring 11, the hook-like securing elements 30 are clamped between the rotor base body 15 and the sealing element 29, in order to fix the rotor blades 17 and 18 on both sides. The section 32 of the sealing element 29, which is used for the bayonet-like fastening of the sealing element 29 to the rotor base body 15 of the rotor blade ring 11, fixes the rotor blades 11 on both sides in the axial direction via the hook-like securing elements 30.
Ein weiteres Ausführungsbeispiel einer erfindungsgemäßen Gasturbine zeigt Fig. 2, wobei auch im Ausführungsbeispiel der Fig. 2 ein Ausschnitt aus einer Turbine 35 gezeigt ist. Das Ausführungsbeispiel der Fig. 2 entspricht hinsichtlich vieler Details dem Ausführungsbeispiel der Fig. 1, so dass zur Vermeidung unnötiger Wiederholungen für gleiche Baugruppen gleiche BezugsZiffern verwendet werden. Nachfolgend wird nur auf die Details eingegangen, durch die sich das Ausführungsbeispiel der Fig. 2 vom Ausführungsbeispiel der Fig. 1 unterscheidet. Im Ausführungsbeispiel der Fig. 2 weisen die Laufschaufeln 17 ebenso wie im Ausführungsbeispiel der Fig. 1 hakenartige Sicherungselemente 30 auf, die in Verankerungsposition auf einer Niederdruckseite des Laufschaufelkranzes 11 am Rotorgrundkörper 15 desselben anliegen. Die hakenartigen Sicherungselemente 30 sind dabei wiederum zwischen dem Rotorgrundkörper 15 des Laufschaufelkranzes 11 und dem Dichtungselement 29 in Axialrichtung beidseitig fixiert, wobei sich das Dichtungselement 29 zwischen dem Rotorgrundkörper 15 des LaufSchaufelkranzes 11, dessen Laufschaufeln vor einer Verschiebung in Axialrichtung zu sichern sind, und dem Rotorgrundkörper 16 des sich auf der Niederdruckseite anschließenden Laufschaufelkranzes 12 erstreckt. FIG. 2 shows a further exemplary embodiment of a gas turbine according to the invention, a section of a turbine 35 also being shown in the exemplary embodiment of FIG. 2. The embodiment of FIG. 2 corresponds in many details to the embodiment of FIG. 1, so that the same reference numbers are used to avoid unnecessary repetitions for the same modules. In the following, only the details are dealt with, by which the embodiment of FIG. 2 differs from the embodiment of FIG. 1. In the exemplary embodiment in FIG. 2, as in the exemplary embodiment in FIG. 1, the rotor blades 17 have hook-like securing elements 30 which, in the anchoring position, bear against the rotor base body 15 on a low-pressure side of the rotor blade ring 11. The hook-like securing elements 30 are in turn fixed between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29 in the axial direction, the sealing element 29 being located between the rotor base body 15 of the rotor blade ring 11, the rotor blades of which are to be secured against displacement in the axial direction, and the rotor base body 16 of the rotor blade ring 12 adjoining on the low pressure side extends.
Im Ausführungsbeispiel der Fig. 2 ist das Dichtungselement 29 nicht wie im Ausführungsbeispiel der Fig. 1 bajonettartig mit dem Rotorgrundkörper 15 des Laufschaufelkranzes 11 verbunden, vielmehr ist ein Vorsprung 36 des Dichtungselements 29 zwischen zwei Flanschen 37 und 38 der in Axialrichtung hintereinander positionierten Rotorgrundkörper 15 und 16 durch Verschrauben befestigt. Ein sich an den Vorsprung 36 anschließender Abschnitt 39 des Dichtungselements 29 dient der beidseitigen Fixierung der hakenartigen Sicherungselemente 30 zwischen dem Rotorgrundkörper 15 und dem Dichtungselement 29, um so ein unbeabsichtigtes Verschieben der Laufschaufeln 17 des Laufschaufelkranzes 11 in Axialrichtung zu unterbinden. In the exemplary embodiment in FIG. 2, the sealing element 29 is not connected in a bayonet-like manner to the basic rotor body 15 of the rotor blade ring 11, as in the exemplary embodiment in FIG. 1, rather a projection 36 of the sealing element 29 is between two flanges 37 and 38 of the basic rotor bodies 15 and 12 positioned one behind the other in the axial direction 16 fastened by screwing. A section 39 of the sealing element 29 adjoining the projection 36 serves to fix the hook-like securing elements 30 on both sides between the rotor base body 15 and the sealing element 29, in order to prevent the blades 17 of the rotor blade ring 11 from being moved unintentionally in the axial direction.
Im Sinne der hier vorliegenden Erfindung werden demnach in Axialnuten geführte Laufschaufeln von Laufschaufelkränzen dadurch vor einer ungewollten Axialverschiebung gesichert, dass den Schaufelfüßen der Laufschaufeln zugeordnete hakenartige Sicherungselemente zwischen dem Rotorgrundkörper des Laufschaufelkranzes und einem rotorseitigen Dichtungselement einer sogenannten Inner-Air-Seal-Dichtung fixiert werden, nämlich beidseitig in Axialrichtung, wobei alle Schaufeln zweier benachbarter Laufschaufelkränze 11 und 12 durch ein Bauelement 29 axial gesichert werden. Dabei wird das Dichtungselement am entsprechenden Rotorgrundkörper vorzugsweise bajonettartig befestigt. Die Erfindung verfügt über den Vorteil, dass Lauf- schaufeln relativ einfach am Rotorgrundkörper montiert sowie demontiert werden können. Alle Laufschaufeln eines Laufschaufelkranzes können dabei gemeinsam über ein Dichtungselement in Axialrichtung fixiert werden. For the purposes of the present invention, rotor blades of rotor blade rings which are guided in axial grooves are thus secured against unwanted axial displacement by fixing hook-like securing elements associated with the blade roots of the rotor blades between the rotor base body of the rotor blade ring and a rotor-side sealing element of a so-called inner air seal seal, namely on both sides in the axial direction, with all the blades of two adjacent rotor blade rings 11 and 12 being axially secured by a component 29. The sealing element is preferably attached to the corresponding rotor base body in a bayonet-like manner. The invention has the advantage that rotor blades can be assembled and disassembled on the rotor base body relatively easily. All the blades of a blade ring can be fixed together in the axial direction using a sealing element.
* * * * * *

Claims

Patentansprüche  Claims
1. Turbomaschine, insbesondere Gasturbine, mit mehreren in Axialrichtung hintereinander positionierten, einer Turbine oder einem Verdichter zugeordneten Laufschaufelkränzen (11, 12), wobei jeder Laufschaufelkranz einen Rotorgrundkörper (15, 16) mit mehreren Laufschaufeln (17, 18) aufweist, und wobei die Laufschaufeln eines Laufschaufelkranzes über Schaufelfüße (19, 20) in sich im wesentlichen in Axialrichtung erstreckenden Axialnuten des jeweiligen Rotorgrundkörpers verankert und in ihrer Verankerungsposition im Rotorgrundkörper vor einer Verschiebung in Axialrichtung gesichert sind, dadurch gekennzeichnet, 1. turbomachine, in particular gas turbine, with a plurality of rotor blades (11, 12) positioned one behind the other in the axial direction and assigned to a turbine or a compressor, each rotor blade ring having a rotor base body (15, 16) with a plurality of rotor blades (17, 18), and wherein the Rotor blades of a rotor blade ring are anchored via blade roots (19, 20) in axial grooves of the respective rotor base body which extend essentially in the axial direction and are secured in their anchoring position in the rotor base body against displacement in the axial direction, characterized in that
dass die Laufschaufeln (17) zumindest eines Laufschaufelkranzes (11) hakenartige Sicherungselemente (30) aufweisen, die in der Verankerungsposition auf einer Niederdruckseite des Laufschaufelkranzes that the blades (17) of at least one blade ring (11) have hook-like securing elements (30) which, in the anchoring position, on a low-pressure side of the blade ring
(11) am Rotorgrundkörper (15) desselben anliegen, wobei die hakenartigen Sicherungselemente (30) zwischen dem Rotorgrundkörper (15) des Laufschaufelkranzes (11) und einem Dichtungselement (29), welches sich zwischen dem Rotorgrundkörper (15) und einem Rotorgrundkörper(11) abut the same on the rotor base body (15), the hook-like securing elements (30) between the rotor base body (15) of the rotor blade ring (11) and a sealing element (29) which is located between the rotor base body (15) and a rotor base body
(16) eines sich auf der Niederdruckseite anschließenden Laufschaufelkranzes (12) erstreckt, in Axialrichtung beidseitig fixiert sind. (16) of a rotor blade ring (12) which adjoins on the low pressure side and are fixed on both sides in the axial direction.
2. Turbomaschine nach Anspruch 1, 2. turbomachine according to claim 1,
dadurch gekennzeichnet,  characterized,
dass die hakenartigen Sicherungselemente (30) zwischen dem Rotorgrundkörper (15) des Laufschaufelkranzes (11) und einem Dichtungselement (19) in Axialrichtung beidseitig geklemmt sind.  that the hook-like securing elements (30) are clamped on both sides in the axial direction between the basic rotor body (15) of the rotor blade ring (11) and a sealing element (19).
3. Turbomaschine nach Anspruch 1 oder 2, 3. Turbo machine according to claim 1 or 2,
dadurch gekennzeichnet,  characterized,
dass das Dichtungselement (29) über einen den hakenartigen Sicherungselementen (30) benachbarten Abschnitt (32) bajonettartig am Rotorgrundkörper (15) des Laufschaufelkranzes (11), dessen Laufschaufeln (17) vor einer Verschiebung in Axialrichtung zu sichern sind, befestigt ist.  that the sealing element (29) is fastened via a section (32) adjacent to the hook-like securing elements (30) in a bayonet-like manner on the rotor base body (15) of the rotor blade ring (11), the rotor blades (17) of which are to be secured against displacement in the axial direction.
4. Turbomaschine nach Anspruch 3, 4. turbomachine according to claim 3,
dadurch gekennzeichnet,  characterized,
dass der Abschnitt (32) des Dichtungselements (29) die hakenartigen Sicherungselemente (30) der Laufschaufeln (17) in Axialrichtung beidseitig fixiert. that the section (32) of the sealing element (29) fixes the hook-like securing elements (30) of the rotor blades (17) on both sides in the axial direction.
5. Turbomaschine nach Anspruch 3 oder 4, 5. Turbo machine according to claim 3 or 4,
dadurch gekennzeichnet,  characterized,
dass der Abschnitt (32) des Dichtungselements (29) einen Vorsprung (33) aufweist, der über eine Öffnung in eine Nut (34) des Rotorgrundkörpers (15) in Axialrichtung einführbar ist, wobei das Dich- tungselement (29) anschließend zur bajonettartig Befestigung desselben in Urαfangrichtung drehbar ist.  that the section (32) of the sealing element (29) has a projection (33) which can be introduced in the axial direction via an opening into a groove (34) of the rotor base body (15), the sealing element (29) subsequently for bayonet-type fastening the same is rotatable in the original direction.
6. Turbomaschine nach Anspruch 1 oder 2, 6. turbomachine according to claim 1 or 2,
dadurch gekennzeichnet,  characterized,
dass das Dichtungselement (29) über einen Vorsprung (36) zwischen Flanschen (37, 38) der Rotorgrundkörper (15, 16), zwischen welchen sich das Dichtungselement (29) erstreckt, befestigt ist.  that the sealing element (29) is fastened via a projection (36) between flanges (37, 38) of the basic rotor bodies (15, 16), between which the sealing element (29) extends.
7. Turbomaschine nach Anspruch 6, 7. turbomachine according to claim 6,
dadurch gekennzeichnet,  characterized,
dass ein zum Vorsprung (36) benachbarter Abschnitt (39) des Dichtungselements (29) die hakenartigen Sicherungselemente (30) der Laufschaufeln (17) in Axialrichtung beidseitig fixiert.  that a section (39) of the sealing element (29) adjacent to the projection (36) fixes the hook-like securing elements (30) of the rotor blades (17) on both sides in the axial direction.
PCT/DE2006/002150 2005-12-10 2006-12-05 Turbomachine having axial rotor blade securing WO2007065411A1 (en)

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US20090028712A1 (en) 2009-01-29
DE102005059084A1 (en) 2007-06-14

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