EP1931859B1 - Guide blade arrangement of a non-positive-displacement machine - Google Patents
Guide blade arrangement of a non-positive-displacement machine Download PDFInfo
- Publication number
- EP1931859B1 EP1931859B1 EP06793334A EP06793334A EP1931859B1 EP 1931859 B1 EP1931859 B1 EP 1931859B1 EP 06793334 A EP06793334 A EP 06793334A EP 06793334 A EP06793334 A EP 06793334A EP 1931859 B1 EP1931859 B1 EP 1931859B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vane
- pull
- axially
- pin
- vane
- 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.)
- Not-in-force
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Classifications
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- 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
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly methods
Definitions
- the present invention relates to a guide vane arrangement of a turbomachine, in particular a gas turbine.
- a typical vane assembly includes at least one vane support attached to a housing of a turbomachine. Such a vane assembly also includes a plurality of vanes mounted on the vane support and circumferentially juxtaposed.
- each vane has a platform having at least two latch portions circumferentially spaced from one another.
- Each latch portion has a tongue which projects circumferentially from the platform and extends in the axial direction.
- the vane support has at least two support portions which are circumferentially spaced from each other.
- Each support portion has a groove which is open in the circumferential direction and extends in the axial direction.
- the tongues of the locking portions and the grooves of the support portions are designed so that they have an axially pluggable and radially positive fastening between the vane support and the respective vane.
- a vane arrangement of this type provides the ability to assemble and disassemble individual vanes without disassembly of the entire vane support.
- the pluggable attachment between the vane support and the vanes becomes sluggish or blocked.
- the vanes e.g. For maintenance purposes, large axial forces must be introduced into the respective vane. If disassembly of the entire vane support is to be avoided, the required forces must be introduced into the airfoil airfoil. Pulling or pushing the vane on its airfoil increases the risk of damage to a thermal protection layer of the airfoil or the risk of deformation of the airfoil.
- the invention is based on the general idea of providing at least one of the guide vanes with a take-off device which is designed to introduce axially oriented withdrawal forces into the respective guide vane. through Such a withdrawal device, it is possible to initiate axially oriented forces outside the airfoil in the vane. Consequently, deformations of the airfoil and damage to the thermal protection layer can be avoided.
- the extraction device comprises at least one axially extending exhaust passage opening, which is provided with an internal thread.
- the vane support is provided with an abutment zone axially opposite said exhaust passage opening.
- a trigger tool provided with an external thread is inserted into the exhaust passage and screwed into the internal thread. By screwing the trigger tool comes into contact with the abutment zone. Further screwing the extraction tool into the exhaust passage opening introduces axial compressive forces in the vane. Since the extraction tool cooperates with the internal thread of the exhaust passage opening, an axially oriented tensile force is introduced into the guide blade in response to the withdrawal tool pressing against the guide blade carrier.
- the extraction device allows by means of said withdrawal tool the removal of the guide vane with very high withdrawal forces.
- the extraction device is preferably arranged and / or designed for introducing the withdrawal forces in the region of the fastening between the guide blade carrier and the respective guide blade.
- the trigger device is arranged to initiate the withdrawal forces parallel and preferably coaxially to the insertion direction of said attachment and / or formed.
- the take-off passage opening and the internal thread are formed on a trigger pin, which is a separate component with respect to the respective guide blade and with respect to the guide blade carrier. Because the vane and the Trigger pin are different components, the material of the trigger pin can be selected according to the requirements for the introduction of high tensile forces in the guide vane.
- a vane assembly 1 has at least one vane carrier 2 and a plurality of stator vanes 3.
- the vane arrangement 1 is part of a turbomachine 4.
- Said turbomachine 4 is in particular a gas turbine.
- the turbomachine can also be a steam turbine or a compressor.
- the vane arrangement 1 has the guide vanes 3 of a row of guide vanes of the turbomachine 4.
- the turbomachine 4 is equipped with a plurality of vane rows. In principle, each of these vane rows may comprise the vane arrangement 1 according to the invention.
- the guide blade carrier 2 is attached to a housing 5 of the turbomachine 4.
- the vanes 3 are attached to the vane carrier 2. In order to form the guide blade row, the guide vanes 3 are arranged next to one another in the circumferential direction.
- each vane 3 has a platform 6 and a flow profile 7 which projects radially and inwardly from the platform 6.
- the platform 6 has a first latch portion 8 located on the left side of FIG Fig. 1 and a second latch portion 9 on the right side of FIG Fig. 1 is shown.
- the locking portions 8, 9 are arranged at an axial distance from each other.
- the first locking portion 8 is arranged in the region of a downstream side 10 of the profile 7, while the second locking portion 9 is arranged in the region of an inflow side 11 of the profile 7.
- the guide blade carrier 2 has a first support section 12 and a second support section 13.
- the two support portions 12, 13 are also axially spaced apart from each other.
- Each latch section 8, 9 and the associated support section 12, 13 are designed such that they provide an axially pluggable and radially positive fastening between the guide blade carrier 2 and the respective vane 3.
- the cooperating latch sections 8, 9 and support sections 12, 13 open an axial push-in or pull-in movement and an axial pull-out or pull-away motion to disassemble the respective guide blade 3.
- the cooperating latch sections 8, 9 constitute the cooperating latch sections and support sections 12, 13 a radial fixation with a positive connection between the vane support 2 and the respective vane.
- the vane arrangement 1 has at least one securing element 14, which is fastened to the guide vane carrier 2.
- Said securing element 14 is designed such that it provides an axial fixation of at least one of the guide vanes 3.
- the vane 3 is axially fixed or secured in its assembled state by means of said securing element 14.
- each vane 3 is basically adjustable in the circumferential direction. Such adjustment may be advantageous to eliminate or reduce backlash between adjacent vanes 3.
- the first latch portion 8 and the second latch portion 9 are arranged at a radial distance from each other. This feature results in an axially compact structure of the vane assembly 1. This feature also reduces Production costs.
- the first support portion 12 and the second support portion 13 may be radially spaced from each other.
- the first support portion 12 preferably has an inner collar 15 which projects radially inwardly from the vane support 2 and extends in the circumferential direction.
- Said inner collar 15 is provided with an inner tongue 16 which extends axially and circumferentially.
- the first locking portion 8 has an inner groove 17.
- Said inner groove 17 is axially open and extends circumferentially.
- Said inner tongue 16 and said inner groove 17 are configured to provide a first tongue-and-groove joint 18 between the vane support 2 and the respective vane 3. In the mounted state, the inner tongue 16 projects axially into the inner groove 17 and engages radially on the platform 6.
- the second latch portion 9 has an outer collar 19 which projects radially outward from the platform 6 and extends in the circumferential direction.
- Said outer collar 19 is provided with an outer tongue 20 which extends in the axial direction and in the circumferential direction.
- the second support portion 13 is provided with an outer groove 21 which is axially open and extends circumferentially.
- Said outer tongue 20 and said outer groove 21 are configured to provide a second tongue-and-groove joint 22 between the vane support 2 and the respective vane 3. In the assembled state, the outer tongue 20 extends into the outer groove 21 and engages radially on the guide vane carrier 2.
- the vane 3 is circumferentially adjustable during assembly.
- a locking pin 23 is provided in order to fix a set position between the vane support 2 and the respective vane 3 circumferentially.
- Said locking pin 23 penetrates into a depression 24, which is recessed in the outer collar 19.
- Said locking pin 23 is inserted into a complementary pin receptacle 25 which is provided in the guide vane carrier 2.
- the locking pin 23 is a separate component with respect to the vane 3 and the vane support 2.
- the platform 6 preferably has a cavity 27 which is open towards the guide blade carrier 2. Said cavity 27 is bounded radially inwardly by a base 28 of the platform 6.
- the airfoil 7 projects radially inwardly from said base 28.
- the cavity 27 is axially and circumferentially bounded by walls 29. Said walls 29 are radially outwardly of the base 28.
- the cavity 27 forms a cooling gas distribution chamber.
- the airfoil 7 includes a cooling gas path 30 that is fluidically connected by the base 28 to the cavity 27.
- the vane support 2 is equipped with a common collection channel 31.
- Said common collecting channel 31 extends circumferentially and preferably extends along the entire guide plate carrier 2.
- the housing 5 is equipped with at least one cooling gas supply channel 32, which is fluidly connected to a not shown cooling gas supply device.
- Said cooling gas supply channel 32 is also fluidly connected to the common collection channel 31 and thus supplies the common collecting channel 31 with cooling gas.
- the cooling gas flow is symbolized by an arrow 33.
- the vane support 2 is additionally equipped with a plurality of connection openings 34. Each connection opening 34 fluidly connects the common collection channel 31 with one of the cavities 27. Accordingly, the Cavities 27 of the guide vanes 3 supplied from the common collecting channel 31 via the respective connection opening 34 with cooling gas.
- a baffle plate 26 may be arranged.
- a common collecting channel 31 for supplying a plurality or all of the guide vanes 3 with cooling gas which is preferably air or steam
- cooling gas which is preferably air or steam
- the at least one cooling gas supply passage 32 can be disposed within the housing 5 regardless of the position of the respective guide blade 3.
- the number of cooling gas supply passages 32 may be smaller than the number of guide vanes 3 to be supplied with cooling gas. The flexibility for designing the housing 5 is increased, thereby reducing the manufacturing cost of the housing 5.
- the other wall 29, which axially delimits the cavity 27 in the region of the inflow side 11 of the airfoil 7, is equipped with the second latch portion 9. Accordingly, the cavity 27 extends axially from the downstream side 10 to the inflow side 11. In the circumferential direction, said cavity 27 extends over the entire circumferential extent of the base 28th
- At least the illustrated vane 3 of the vane assembly 1 is equipped with a trigger 35.
- each vane 3 is the vane assembly 1 with such a take-off device 35 fitted.
- the extraction device 35 With the aid of said extraction device 35, the disassembly or removal of the guide vane 3 from the guide vane carrier 2 is simplified.
- the extraction device 35 allows the technician to apply very high axial tensile or withdrawal forces on the guide vane 3, without the risk of deformation of the airfoil 7 or the damage of a thermal protection layer of the airfoil 7.
- the trigger 35 comprises the locking pin 23, the recess 24 and the pin receptacle 25. Consequently, the locking pin 23 is also referred to below as the trigger pin 23.
- the extraction device 35 comprises at least one exhaust passage opening 36. This exhaust passage opening 36 extends in the axial direction and thus extends parallel to the mounting or plugging direction of the vane 3. Said passage opening 36 is provided with an internal thread 37, the entire passage opening 36 or - As in the example - only a portion of the through hole 36 covered.
- the extraction device 35 also comprises, for each exhaust passage opening 36, an abutment zone 38 which is axially opposite the exhaust passage opening 36 and which is formed on the guide blade carrier 2.
- the exhaust passage opening 36 is formed in the trigger pin 23 according to the illustrated example, and the abutment zone 38 is formed at an axial end or bottom of the pin receiver 25.
- the take-off device 35 is designed to remove the guide vane 3 from the vane carrier 2 for cooperation with a take-off tool 39.
- Said trigger tool 39 is with a Provided external thread 40 which is complementary to the internal thread 37 of the discharge passage opening 36. Consequently, the extraction tool 39 fits into the through hole 36.
- the extraction tool 39 is also provided with a drive portion 41 configured to introduce torque into the extraction tool 39.
- the extraction tool 39 is a special screw having a head with a hexagon.
- the trigger tool 39 is inserted or threaded into the vent port 36 until a leading end 42 of the trigger tool 39 contacts the abutment zone 38. Further insertion or screwing of the trigger tool 39 into the vent passage opening 36 leads to axial pressure between the trigger tool 39 and the abutment zone 38.
- the trigger tool 39 is supported via its external thread 40 and via the internal thread 37 at the passage opening 36 containing body.
- the take-off tool 39 is supported on the trigger pin 23, which bears against the guide blade 3, namely on a support contour 43 of the guide blade 3, which lies opposite the abutment zone 38. Consequently, the trigger tool 39 is indirectly supported on the vane 3, namely on the trigger pin 23rd
- the trigger pin 23 is attached to the guide blade 3 in a torque-proof manner.
- the trigger pin 23 is corresponding to the Fig. 5a to 5c provided with two outer surfaces 53 which are arranged on two diametrically opposite sides of the trigger pin 23.
- the two outer surfaces 23 are flat and extend parallel to each other. Inserted into the recess 24, the two outer surfaces 53 bear against two opposite walls of the recess 24.
- the withdrawal pin 23 is provided with at least one step 54 which rests against the support contour 43 of the guide blade 3.
- the trigger pin 23 is equipped with two stages 54.
- the trigger 35 includes the trigger pin 23, which also serves as a latch pin 23 for circumferentially securing the vane 3 on the vane carrier 2. Consequently, the locking pin 23 or trigger pin 23 is multifunctional and the trigger 35 can be realized in the vane assembly 1, apart from the trigger tool 39, without additional component.
- each individual vane 3 can be assembled and disassembled independently of other vanes 3.
- the guide blade carrier 2 does not have to be dismantled for the assembly and disassembly of the guide vanes 3.
- the locking pin or trigger pin 23 is mounted by insertion into the pin holder 35. Thereafter, the respective vane 3 is moved axially in accordance with an arrow 44. In an end phase of this axial movement, the two tongue and groove connections 18, 22 are produced by axial insertion of the tongues 16, 20 into the respective grooves 17, 21. After this insertion process, the respective guide blade 3 is fastened radially to the guide blade carrier 2 by means of the positive connection provided by the tongue and groove connections 18, 22.
- the securing element 14 is mounted on the vane carrier 2.
- the securing member 14 and the vane carrier 2 are provided with two tongue and groove connections 45 which are similar to the tongue and groove joints 18, 22 between the vane 3 and the vane carrier 2.
- the securing element 14 is fastened to the guide blade carrier 2 by means of at least one locking bolt 46 in connection with at least one inlet segment 47.
- Said inlet segment 47 is equipped with an external step 48.
- the platform 6 is provided with an inner step 49, which is arranged with respect to the mounting direction 44 at the rear end of the platform 6. Said mounting direction 44 is oriented parallel to the flow direction. In the assembled state accordingly Fig.
- the outer stage 48 of the inlet segment 47 with the inner stage 49 of the guide vane 3 is engaged.
- the inlet segment 47 is carried by the vane 3.
- the inlet segment 47 can additionally be fastened to the guide blade 2 by further fastening means (not shown).
- the locking bolt 46 penetrates the securing element 14 within a passage opening 50 and projects into the blind hole 51 which is formed on the guide blade carrier 2. When assembled, said locking bolt 46 is supported radially inwardly by the inlet segment 47. Radially outward, the locking bolt 46 is supported by the guide vane carrier 2 by means of a compression spring 52. The locking bolt 46 secures the axial position of the securing element 14 and the support between the two stages 48 and 49.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die vorliegende Erfindung betrifft eine Leitschaufel-Anordnung einer Strömungsmaschine, insbesondere einer Gasturbine.The present invention relates to a guide vane arrangement of a turbomachine, in particular a gas turbine.
Eine typische Leitschaufelanordnung umfasst zumindest einen Leitschaufelträger, der an einem Gehäuse einer Turbomaschine befestigt ist. Eine derartige Leitschaufelanordnung umfasst außerdem mehrere Leitschaufeln, die am Leitschaufelträger befestigt und in Umfangsrichtung nebeneinander angeordnet sind. Üblicherweise weist jede Leitschaufel eine Plattform auf, die zumindest zwei Riegelabschnitte aufweist, die umfangsmäßig voneinander beabstandet sind. Jeder Riegelabschnitt weist eine Zunge auf, die in Umfangsrichtung von der Plattform absteht und sich in axialer Richtung erstreckt. Der Leitschaufelträger weist zumindest zwei Tragabschnitte auf, die in Umfangsrichtung voneinander beabstandet sind. Jeder Tragabschnitt weist eine Nut auf, die in Umfangsrichtung offen ist und sich in axialer Richtung erstreckt. Die Zungen der Riegelabschnitte und die Nuten der Tragabschnitte sind so ausgestaltet, dass sie eine axial steckbare und radial formschlüssige Befestigung zwischen dem Leitschaufelträger und der jeweiligen Leitschaufel bereitstellen. Eine Leitschaufelanordnung dieser Art gibt die Möglichkeit, einzelne Leitschaufeln ohne Zerlegung des ganzen Leitschaufelträgers zu montieren und zu demontieren.A typical vane assembly includes at least one vane support attached to a housing of a turbomachine. Such a vane assembly also includes a plurality of vanes mounted on the vane support and circumferentially juxtaposed. Typically, each vane has a platform having at least two latch portions circumferentially spaced from one another. Each latch portion has a tongue which projects circumferentially from the platform and extends in the axial direction. The vane support has at least two support portions which are circumferentially spaced from each other. Each support portion has a groove which is open in the circumferential direction and extends in the axial direction. The tongues of the locking portions and the grooves of the support portions are designed so that they have an axially pluggable and radially positive fastening between the vane support and the respective vane. A vane arrangement of this type provides the ability to assemble and disassemble individual vanes without disassembly of the entire vane support.
Aufgrund der hohen Temperaturen und Kräfte und aufgrund von Verunreinigungen, die während des Betriebs der Turbomaschine auftreten, wird die steckbare Befestigung zwischen dem Leitschaufelträger und den Leitschaufeln schwergängig oder blockiert. Um die Leitschaufeln, z.B. für Wartungszwecke, zu entfernen, müssen große Axialkräfte in die jeweilige Leitschaufel eingeleitet werden. Falls ein Auseinanderbauen des gesamten Leitschaufelträgers vermieden werden soll, müssen die erforderlichen Kräfte in das Strömungsprofil der Leitschaufel eingeleitet werden. Ziehen oder Drücken der Leitschaufel an ihrem Strömungsprofil erhöht die Gefahr einer Beschädigung einer thermischen Schutzschicht des Strömungsprofils oder die Gefahr einer Verformung des Strömungsprofils.Due to the high temperatures and forces and contaminants that occur during operation of the turbomachine, the pluggable attachment between the vane support and the vanes becomes sluggish or blocked. Around the vanes, e.g. For maintenance purposes, large axial forces must be introduced into the respective vane. If disassembly of the entire vane support is to be avoided, the required forces must be introduced into the airfoil airfoil. Pulling or pushing the vane on its airfoil increases the risk of damage to a thermal protection layer of the airfoil or the risk of deformation of the airfoil.
Eine Leitschaufel-Anordnung gemäß dem Stand der Technik ist aus dem Dokument
Es ist eine Aufgabe der vorliegenden Erfindung, eine verbesserte Leitschaufelanordnung bereitzustellen, welche die Demontage einzelner Leitschaufeln vereinfacht. Dieses Problem ist durch den unabhängigen Anspruch gelöst. Bevorzugte Ausführungsformen sind in den abhängigen Ansprüchen gezeigt.It is an object of the present invention to provide an improved vane assembly that facilitates disassembly of individual vanes. This problem is solved by the independent claim. Preferred embodiments are shown in the dependent claims.
Die Erfindung beruht auf dem allgemeinen Gedanken, zumindest eine der Leitschaufeln mit einer Abzugseinrichtung zu versehen, die zum Einleiten axial orientierter Abzugskräfte in die jeweilige Leitschaufel ausgestaltet ist. Mittels einer derartigen Abzugseinrichtung ist es möglich, axial orientierte Kräfte außerhalb des Strömungsprofils in die Leitschaufel einzuleiten. Folglich können Verformungen des Strömungsprofils und Beschädigungen der thermischen Schutzschicht vermieden werden.The invention is based on the general idea of providing at least one of the guide vanes with a take-off device which is designed to introduce axially oriented withdrawal forces into the respective guide vane. through Such a withdrawal device, it is possible to initiate axially oriented forces outside the airfoil in the vane. Consequently, deformations of the airfoil and damage to the thermal protection layer can be avoided.
Zu diesem Zweck umfasst die Abzugseinrichtung zumindest eine sich axial erstreckende Abzugsdurchgangsöffnung, die mit einem Innengewinde versehen ist. Zusätzlich ist der Leitschaufelträger mit einer Widerlagerzone ausgestattet, die besagter Abzugsdurchgangsöffnung axial gegenüber liegt. Um eine Leitschaufel vom Leitschaufelträger abzuziehen, wird ein Abzugswerkzeug, das mit einem Außengewinde versehen ist, in die Abzugsdurchgangsöffnung eingesetzt und in das Innengewinde eingeschraubt. Durch Einschrauben kommt das Abzugswerkzeug in Kontakt mit der Widerlagerzone. Weiteres Einschrauben des Abzugswerkzeugs in die Abzugsdurchgangsöffnung leitet axiale Druckkräfte in die Leitschaufel ein. Da das Abzugswerkzeug mit dem Innengewinde der Abzugsdurchgangsöffnung zusammenwirkt, wird als Reaktion auf das gegen den Leitschaufelträger pressende Abzugswerkzeug eine axial orientierte Zugkraft in die Leitschaufel eingeleitet. Die Abzugseinrichtung ermöglicht mittels dem besagten Abzugswerkzeug das Abziehen der Leitschaufel mit sehr hohen Abzugskräften. Vorzugsweise ist die Abzugseinrichtung zum Einleiten der Abzugskräfte im Bereich der Befestigung zwischen dem Leitschaufelträger und der jeweilige Leitschaufel angeordnet und/oder ausgebildet. Vorzugsweise ist die Abzugseinrichtung zum Einleiten der Abzugskräfte parallel und vorzugsweise koaxial zur Steckrichtung besagter Befestigung angeordnet und/oder ausgebildet.For this purpose, the extraction device comprises at least one axially extending exhaust passage opening, which is provided with an internal thread. In addition, the vane support is provided with an abutment zone axially opposite said exhaust passage opening. To withdraw a vane from the vane support, a trigger tool provided with an external thread is inserted into the exhaust passage and screwed into the internal thread. By screwing the trigger tool comes into contact with the abutment zone. Further screwing the extraction tool into the exhaust passage opening introduces axial compressive forces in the vane. Since the extraction tool cooperates with the internal thread of the exhaust passage opening, an axially oriented tensile force is introduced into the guide blade in response to the withdrawal tool pressing against the guide blade carrier. The extraction device allows by means of said withdrawal tool the removal of the guide vane with very high withdrawal forces. The extraction device is preferably arranged and / or designed for introducing the withdrawal forces in the region of the fastening between the guide blade carrier and the respective guide blade. Preferably, the trigger device is arranged to initiate the withdrawal forces parallel and preferably coaxially to the insertion direction of said attachment and / or formed.
Entsprechend einer bevorzugten Ausführungsform sind die Abzugsdurchgangsöffnung und das Innengewinde an einem Abzugsstift ausgebildet, der bezüglich der jeweiligen Leitschaufel und bezüglich des Leitschaufelträgers ein separates Bauteil ist. Da die Leitschaufel und der Abzugsstift verschiedene Bauteile sind, kann der Werkstoff des Abzugsstifts entsprechend den Anforderungen für das Einleiten hoher Zugkräfte in die Leitschaufel ausgewählt werden.According to a preferred embodiment, the take-off passage opening and the internal thread are formed on a trigger pin, which is a separate component with respect to the respective guide blade and with respect to the guide blade carrier. Because the vane and the Trigger pin are different components, the material of the trigger pin can be selected according to the requirements for the introduction of high tensile forces in the guide vane.
Andere Aufgaben und viele der begleitenden Vorteile der vorliegenden Erfindung werden leichter wahrgenommen und werden besser verstanden durch Bezugnahme auf die nachfolgende detaillierte Beschreibung, sofern diese in Verbindung mit den beigefügten Zeichnungen berücksichtigt wird.Other objects and many of the attendant advantages of the present invention will be more readily appreciated and become better understood by reference to the following detailed description, when taken in conjunction with the accompanying drawings.
Bevorzugte Ausführungsformen der Erfindung werden in den Zeichnungen dargestellt und werden in der folgenden Beschreibung näher erläutert. Auf Merkmal, die im wesentlichen oder funktionell gleich oder ähnlich sind, wird mit dem (den) gleichen Bezugszeichen Bezug genommen.
- Fig. 1
- zeigt einen vereinfachten, schematischen Axialschnitt einer Leitschaufelanordnung entsprechend einer Ausführungsform der Erfindung,
- Fig. 2
- zeigt eine Detailansicht gemäß Pfeil II in
Fig. 1 , - Fig. 3
- zeigt einen Schnitt eines Details der Leitschaufelanordnung gemäß Schnittlinien III in
Fig. 1 , - Fig. 4
- zeigt den Schnitt aus
Fig. 3 beim Demontieren der Leitschaufel, - Fig. 5a-c
- zeigen verschiedene Ansichten und einen Schnitt eines Abzugsstifts,
- Fig. 6
- zeigt eine Explosionsdarstellung der Leitschaufelanordnung gemäß
Fig. 1 .
- Fig. 1
- shows a simplified, schematic axial section of a vane assembly according to an embodiment of the invention,
- Fig. 2
- shows a detailed view according to arrow II in
Fig. 1 . - Fig. 3
- shows a section of a detail of the vane arrangement according to section lines III in
Fig. 1 . - Fig. 4
- shows the cut
Fig. 3 when dismantling the vane, - Fig. 5a-c
- show different views and a section of a trigger pin,
- Fig. 6
- shows an exploded view of the vane assembly according to
Fig. 1 ,
Entsprechend
Der Leitschaufelträger 2 ist an einem Gehäuse 5 der Strömungsmaschine 4 befestigt. Die Leitschaufeln 3 sind am Leitschaufelträger 2 befestigt. Um die Leitschaufelreihe auszubilden, sind die Leitschaufeln 3 in Umfangsrichtung nebeneinander angeordnet.The
Im gezeigten bevorzugten Ausführungsbeispiel weist jede Leitschaufel 3 eine Plattform 6 und ein Strömungsprofil 7 auf, das radial und nach innen von der Plattform 6 absteht. Die Plattform 6 weist einen ersten Riegelabschnitt 8, der auf der linken Seite von
Komplementär zu den Riegelabschnitten 8, 9 weist der Leitschaufelträger 2 einen ersten Tragabschnitt 12 und einen zweiten Tragabschnitt 13 auf. Die beiden Tragabschnitte 12, 13 sind ebenfalls zueinander axial beabstandet. Jeder Riegelabschnitt 8, 9 und der zugehörige Tragabschnitt 12, 13 sind so ausgestaltet, dass sie eine axial steckbare und radial formschlüssige Befestigung zwischen dem Leitschaufelträger 2 und der jeweiligen Leitschaufel 3 bereitstellen. Mit anderen Worten, die zusammenwirkenden Riegelabschnitte 8, 9 und Tragabschnitte 12, 13 eröffnen eine axiale Einsteck- oder Drückbewegung zum Montieren und eine axiale Aussteck- oder Zieh-Bewegung zum Demontieren der jeweiligen Leitschaufel 3. Im montierten Zustand begründen die zusammenwirkenden Riegelabschnitte 8, 9 und Tragabschnitte 12, 13 eine radiale Fixierung mit Formschluss zwischen dem Leitschaufelträger 2 und der jeweiligen Leitschaufel 3.Complementary to the
Zusätzlich weist die Leitschaufel-Anordnung 1 gemäß dieser Ausführungsform zumindest ein Sicherungselement 14 auf, das am Leitschaufelträger 2 befestigt ist. Besagtes Sicherungselement 14 ist so ausgestaltet, dass es eine axiale Fixierung wenigstens einer der Leitschaufeln 3 bereitstellt. Die Leitschaufel 3 ist in ihrem montierten Zustand mittels des besagten Sicherungselements 14 axial fixiert oder gesichert.In addition, the
Vorzugsweise erstrecken sich die Tragabschnitte 12, 13 und die Riegelabschnitte 8, 9 in Umfangsrichtung. Während der Montage ist grundsätzlich jede Leitschaufel 3 in Umfangsrichtung verstellbar. Eine solche Verstellung kann vorteilhaft sein, um Spiel zwischen benachbarten Leitschaufeln 3 zu eliminieren oder zu reduzieren. Entsprechend der bevorzugten Ausführungsform sind der erste Riegelabschnitt 8 und der zweite Riegelabschnitt 9 mit radialem Abstand zueinander angeordnet. Dieses Merkmal führt zu einer axial kompakten Struktur der Leitschaufel-Anordnung 1. Dieses Merkmal reduziert außerdem Herstellungskosten. Selbstverständlich können auch der erste Tragabschnitt 12 und der zweite Tragabschnitt 13 zueinander radial beabstandet sein.Preferably, the
Der erste Tragabschnitt 12 weist vorzugsweise einen Innenkragen 15 auf, der radial nach innen vom Leitschaufelträger 2 absteht und sich in Umfangsrichtung erstreckt. Besagter Innenkragen 15 ist mit einer Innenzunge 16 ausgestattet, die sich axial und umfangsmäßig erstreckt. Komplementär dazu weist der erste Riegelabschnitt 8 eine Innennut 17 auf. Besagte Innennut 17 ist axial offen und erstreckt sich umfangsmäßig. Besagte Innenzunge 16 und besagte Innennut 17 sind so ausgestaltet, dass sie eine erste Nut-Feder-Verbindung 18 zwischen dem Leitschaufelträger 2 und der jeweiligen Leitschaufel 3 bereitstellen. Im montierten Zustand ragt die Innenzunge 16 axial in die Innennut 17 hinein und greift radial an der Plattform 6 an.The
Der zweite Riegelabschnitt 9 weist einen Außenkragen 19 auf, der radial nach außen von der Plattform 6 absteht und sich in Umfangsrichtung erstreckt. Besagter Außenkragen 19 ist mit einer Außenzunge 20 ausgestattet, die sich in axialer Richtung und in Umfangsrichtung erstreckt. Dementsprechend ist der zweite Tragabschnitt 13 mit einer Außennut 21 ausgestattet, die axial offen ist und sich umfangsmäßig erstreckt. Besagte Außenzunge 20 und besagte Außennut 21 sind so ausgestaltet, dass sie eine zweite Nut-Feder-Verbindung 22 zwischen dem Leitschaufelträger 2 und der jeweiligen Leitschaufel 3 bereitstellen. Im montierten Zustand erstreckt sich die Außenzunge 20 in die Außennut 21 hinein und greift radial am Leitschaufelträger 2 an.The
Wie oben erwähnt, ist die Leitschaufel 3 während der Montage in Umfangsrichtung verstellbar. Um eine eingestellte Position zwischen dem Leitschaufelträger 2 und der jeweiligen Leitschaufel 3 umfangsmäßig zu fixieren, ist ein Riegelstift 23 vorgesehen. Besagter Riegelstift 23 dringt in eine Vertiefung 24 ein, die im Außenkragen 19 ausgespart ist. Besagter Riegelstift 23 ist in eine komplementäre Stiftaufnahme 25 eingesetzt, die im Leitschaufelträger 2 vorgesehen ist.As mentioned above, the
Dementsprechend ist der Riegelstift 23 bezüglich der Leitschaufel 3 und des Leitschaufelträgers 2 ein separates Bauteil.Accordingly, the locking
Entsprechend
Der Leitschaufelträger 2 ist mit einem gemeinsamen Sammelkanal 31 ausgestattet. Besagter gemeinsamer Sammelkanal 31 erstreckt sich umfangsmäßig und erstreckt sich vorzugsweise entlang des gesamten Leitschaufelträgers 2. Das Gehäuse 5 ist mit wenigstens einem Kühlgasversorgungskanal 32 ausgestattet, der mit einer nicht gezeigten Kühlgasversorgungseinrichtung fluidisch verbunden ist. Besagter Kühlgasversorgungskanal 32 ist außerdem mit dem gemeinsamen Sammelkanal 31 fluidisch verbunden und versorgt folglich den gemeinsamen Sammelkanal 31 mit Kühlgas. Die Kühlgasströmung ist mittels eines Pfeils 33 symbolisiert. Der Leitschaufelträger 2 ist zusätzlich mit mehreren Verbindungsöffnungen 34 ausgestattet. Jede Verbindungsöffnung 34 verbindet fluidisch den gemeinsamen Sammelkanal 31 mit einem der Hohlräume 27. Dementsprechend werden die Hohlräume 27 der Leitschaufeln 3 vom gemeinsamen Sammelkanal 31 über die jeweilige Verbindungsöffnung 34 mit Kühlgas versorgt. Im Hohlraum 27 kann eine Prallplatte 26 angeordnet sein.The
Die Verwendung eines gemeinsamen Sammelkanals 31 zur Versorgung mehrerer oder aller Leitschaufeln 3 mit Kühlgas, das vorzugsweise Luft oder Dampf ist, hat den Vorteil, dass die Kühlgasversorgung der jeweiligen Leitschaufel 3 aufgrund etwa gleicher Kühlgaspfadkonfigurationen zwischen dem gemeinsamen Sammelkanal 31 und den Hohlräumen 27 der jeweiligen Leitschaufeln 3 mit dem gleichen Druck bereitgestellt werden kann. Zusätzlich kann der wenigstens eine Kühlgasversorgungskanal 32 innerhalb des Gehäuses 5 unabhängig von der Position der jeweiligen Leitschaufel 3 angeordnet werden. Auch kann die Anzahl der Kühlgasversorgungskanäle 32 kleiner sein als die Anzahl der mit Kühlgas zu versorgenden Leitschaufeln 3. Die Flexibilität für die Auslegung des Gehäuses 5 ist erhöht, wodurch die Herstellungskosten für das Gehäuse 5 reduziert sind.The use of a
Eine der Wände 29, welche den Hohlraum 27 im Bereich der Abströmseite 10 des Strömungsprofils 7 axial begrenzt, ist mit dem ersten Riegelabschnitt 8 versehen. Die andere Wand 29, welche den Hohlraum 27 im Bereich der Anströmseite 11 des Strömungsprofils 7 axial begrenzt, ist mit dem zweiten Riegelabschnitt 9 ausgestattet. Dementsprechend erstreckt sich der Hohlraum 27 axial von der Abströmseite 10 bis zur Anströmseite 11. In Umfangsrichtung erstreckt sich besagter Hohlraum 27 über die gesamte Umfangserstreckung der Basis 28.One of the
Zumindest die dargestellte Leitschaufel 3 der Leitschaufel-Anordnung 1 ist mit einer Abzugseinrichtung 35 ausgestattet. Vorzugsweise ist jede Leitschaufel 3 der Leitschaufel-Anordnung 1 mit einer derartigen Abzugseinrichtung 35 ausgestattet. Mit Hilfe besagter Abzugseinrichtung 35 wird die Demontage oder das Abziehen der Leitschaufel 3 vom Leitschaufelträger 2 vereinfacht. Die Abzugseinrichtung 35 ermöglicht es dem Techniker, sehr hohe axiale Zug- oder Abzugskräfte auf die Leitschaufel 3 aufzubringen, ohne die Gefahr einer Verformung des Strömungsprofils 7 oder der Beschädigung einer thermischen Schutzschicht des Strömungsprofils 7.At least the
In der bevorzugten Ausführungsform, die in den Figuren dargestellt ist, umfasst die Abzugseinrichtung 35 den Riegelstift 23, die Aussparung 24 und die Stiftaufnahme 25. Folglich wird der Riegelstift 23 im Folgenden auch als Abzugsstift 23 bezeichnet. Die Abzugseinrichtung 35 umfasst zumindest eine Abzugsdurchgangsöffnung 36. Diese Abzugsdurchgangsöffnung 36 erstreckt sich in der axialen Richtung und erstreckt sich folglich parallel zur Montage- oder Steck-Richtung der Leitschaufel 3. Besagte Durchgangsöffnung 36 ist mit einem Innengewinde 37 versehen, das die gesamte Durchgangsöffnung 36 oder - wie im Beispiel - nur einen Abschnitt der Durchgangsöffnung 36 bedeckt.In the preferred embodiment, which is shown in the figures, the
Die Abzugseinrichtung 35 umfasst außerdem für jede Abzugsdurchgangsöffnung 36 eine Widerlagerzone 38, welche der Abzugsdurchgangsöffnung 36 axial gegenüberliegt und welche am Leitschaufelträger 2 ausgebildet ist.The
In der bevorzugten Ausführungsform ist die Abzugsdurchgangsöffnung 36 entsprechend dem dargestellten Beispiel im Abzugsstift 23 ausgebildet, und die Widerlagerzone 38 ist an einem axialen Ende oder Grund der Stiftaufnahme 25 ausgebildet.In the preferred embodiment, the exhaust passage opening 36 is formed in the
Entsprechend den
Wenn die Leitschaufel 3 demontiert werden muss, wird das Abzugswerkzeug 39 in die Abzugsdurchgangsöffnung 36 eingesetzt oder eingeschraubt, bis ein vorausgehendes Ende 42 des Abzugswerkzeugs 39 mit der Widerlagerzone 38 in Kontakt kommt. Weiteres Einführen oder Einschrauben des Abzugswerkzeugs 39 in die Abzugsdurchgangsöffnung 36 führt zu axialem Druck zwischen dem Abzugswerkzeug 39 und der Widerlagerzone 38. Das Abzugswerkzeug 39 ist über sein Außengewinde 40 und über das Innengewinde 37 an dem die Durchgangsöffnung 36 enthaltendem Körper abgestützt. Im Beispiel ist das Abzugswerkzeug 39 am Abzugsstift 23 abgestützt, der an der Leitschaufel 3 anliegt, nämlich an einer Abstützkontur 43 der Leitschaufel 3, die der Widerlagerzone 38 gegenüber liegt. Folglich ist das Abzugswerkzeug 39 indirekt an der Leitschaufel 3 abgestützt, nämlich über den Abzugsstift 23.When the
Die Aktion zum Einleiten hoher Axialkräfte in den Leitschaufelträger 2 mittels des Abzugswerkzeugs 39 führt zu der Reaktion korrespondierender hoher Abzugs- oder Zieh-Kräfte, die in die Leitschaufel 3 eingeleitet sind. Üblicherweise sind die Ziehkräfte, die mit Hilfe der Abzugseinrichtung 35 mittels dem Abzugswerkzeug 39 eingeleitet werden, groß genug, um die Leitschaufel 3 zu demontieren. Da die Abzugseinrichtung 35 außerhalb des Strömungsprofils 7, nämlich im Bereich der Befestigung zwischen der Leitschaufel 3 und dem Leitschaufelträger 2 angeordnet ist, können die Abzugskräfte keinen nachteiligen Effekt auf das Strömungsprofil 7 oder auf eine thermische Schutzschicht des Strömungsprofils 7 haben.The action for introducing high axial forces into the
Um eine Drehbewegung des Abzugsstifts 23 beim Einschrauben des Abzugswerkzeugs 39 in die Durchgangsöffnung 36 zu vermeiden, ist der Abzugsstift 23 drehfest an der Leitschaufel 3 angebracht. Zu diesem Zweck ist der Abzugsstift 23 entsprechend den
Um hohe Abzugskräfte vom Abzugswerkzeug 39 auf die Leitschaufel 3 übertragen zu können, ist der Abzugsstift 23 mit wenigstens einer Stufe 54 versehen, die an der Abstützkontur 43 der Leitschaufel 3 anliegt. Im gezeigten Beispiel ist der Abzugsstift 23 mit zwei Stufen 54 ausgestattet.In order to be able to transfer high withdrawal forces from the
Im bevorzugten Ausführungsbeispiel, das in den Figuren dargestellt ist, umfasst die Abzugseinrichtung 35 den Abzugsstift 23, der auch als Riegelstift 23 zum umfangsmäßigen sichern der Leitschaufel 3 am Leitschaufelträger 2 dient. Folglich ist der Riegelstift 23 oder Abzugsstift 23 multifunktionell und die Abzugseinrichtung 35 kann in der Leitschaufel-Anordnung 1, abgesehen vom Abzugswerkzeug 39, ohne zusätzliches Bauteil realisiert werden.In the preferred embodiment, which is shown in the figures, the
Alternativ ist es ebenso möglich, die Abzugseinrichtung 35 ohne den Abzugsstift 23 zu realisieren, indem die Leitschaufel 3 direkt mit der Abzugsdurchgangsöffnung 36 versehen wird.Alternatively, it is also possible to realize the take-
Entsprechend
Vor der Montage der Leitschaufel 3 am Leitschaufelträger 2 wird der Riegelstift oder Abzugsstift 23 durch Einsetzen in die Stiftaufnahme 35 montiert. Danach wird die jeweilige Leitschaufel 3 entsprechend einem Pfeil 44 axial bewegt. In einer Endphase dieser Axialbewegung werden durch axiales Einstecken der Zungen 16, 20 in die jeweiligen Nuten 17, 21 die beiden Nut-Feder-Verbindungen 18, 22 hergestellt. Nach diesem Einsteckvorgang ist die jeweilige Leitschaufel 3 mittels des durch die Nut-Feder-Verbindungen 18, 22 bereitgestellten Formschlusses radial am Leitschaufelträger 2 befestigt.Before mounting the
Nach dem Montieren der Leitschaufel 3 wird das Sicherungselement 14 am Leitschaufelträger 2 montiert. Vorzugsweise sind das Sicherungselement 14 und der Leitschaufelträger 2 mit zwei Nut-Feder-Verbindungen 45 ausgestattet, die den Nut-Feder-Verbindungen 18, 22 zwischen der Leitschaufel 3 und dem Leitschaufelträger 2 ähneln. Das Sicherungselement 14 ist am Leitschaufelträger 2 mittels wenigstens einem Riegelbolzen 46 in Verbindung mit wenigstens einem Einlasssegment 47 befestigt. Besagtes Einlasssegment 47 ist mit einer Außenstufe 48 ausgestattet. Die Plattform 6 ist mit einer Innenstufe 49 versehen, die bezüglich der Montagerichtung 44 am hinteren Ende der Plattform 6 angeordnet ist. Besagte Montagerichtung 44 ist parallel zur Strömungsrichtung orientiert. Im montierten Zustand entsprechend
Der Riegelbolzen 46 durchdringt das Sicherungselement 14 innerhalb einer Durchgangsöffnung 50 und ragt in Sackloch 51 hinein, das am Leitschaufelträger 2 ausgebildet ist. Im montierten Zustand ist besagter Riegelbolzen 46 radial innen durch das Einlasssegment 47 getragen. Radial außen ist der Riegelbolzen 46 mittels einer Druckfeder 52 durch den Leitschaufelträger 2 getragen. Der Riegelbolzen 46 sichert die axiale Position des Sicherungselements 14 und die Abstützung zwischen den beiden Stufen 48 und 49.The locking
- 11
- Leitschaufel-AnordnungVane arrangement
- 22
- Leitschaufelträgerguide vane
- 33
- Leitschaufelvane
- 44
- Strömungsmaschineflow machine
- 55
- Gehäusecasing
- 66
- Plattformplatform
- 77
- Strömungsprofilflow profile
- 88th
- erster Riegelabschnittfirst latch section
- 99
- zweiter Riegelabschnittsecond latch section
- 1010
- Abströmseite von 7Downstream side of 7
- 1111
- Anströmseite von 7Upstream side of 7
- 1212
- erster Tragabschnittfirst support section
- 1313
- zweiter Tragabschnittsecond support section
- 1414
- Sicherungselementfuse element
- 1515
- Innenkrageninner collar
- 1616
- Innenzungeinterior tongue
- 1717
- Innennutinner groove
- 1818
- erste Nut-Feder-Verbindungfirst tongue and groove connection
- 1919
- Außenkragenouter collar
- 2020
- Außenzungeouter tongue
- 2121
- Außennutouter groove
- 2222
- zweite Nut-Feder-Verbindungsecond tongue and groove connection
- 2323
- Riegelstift/AbzugsstiftLatch pin / trigger pin
- 2424
- Vertiefungdeepening
- 2525
- Stiftaufnahmepin receptacle
- 2626
- Prallplatteflapper
- 2727
- Hohlraumcavity
- 2828
- BasisBase
- 2929
- Wandwall
- 3030
- KühlgaspfadCooling gas path
- 3131
- gemeinsamer Sammelkanalcommon collection channel
- 3232
- KühlgasversorgungskanalCooling gas supply channel
- 3333
- KühlgasströmungCooling gas flow
- 3434
- Verbindungsöffnungconnecting opening
- 3535
- Abzugseinrichtungoff device
- 3636
- AbzugsdurchgangsöffnungEscape passage opening
- 3737
- Innengewindeinner thread
- 3838
- WiderlagerzoneAbutment zone
- 3939
- Abzugswerkzeugdeduction tool
- 4040
- Außengewindeexternal thread
- 4141
- Antriebsabschnittdriving section
- 4242
- vorausgehendes Endeprevious end
- 4343
- Stützkontursupport contour
- 4444
- Montagerichtungmounting direction
- 4545
- Nut-Feder-VerbindungTongue and groove
- 4646
- Riegelbolzenlocking bolt
- 4747
- Einlasssegmentinlet section
- 4848
- Außenstufeoutdoor stage
- 4949
- Innenstufeindoor stage
- 5050
- DurchgangsöffnungThrough opening
- 5151
- Sacklochblind
- 5252
- Druckfedercompression spring
- 5353
- Außenfläche von 23Outer surface of 23
- 5454
- Stufe von 23Level of 23
Claims (10)
- Guide vane arrangement of a turbomachine (4), in particular of a gas turbine, comprising:- at least one guide vane carrier (2) which can be fastened to a casing (5) of a turbomachine (4),- a plurality of guide vanes (3) which are fastened to the guide vane carrier (2) and are arranged next to one another in the circumferential direction,- the fastening between the guide vane carrier (2) and the respective guide vane (3) being configured for plugging axially, characterized in that- at least one of the guide vanes (3) is provided with a pull-off device (35) which has at least one axially extending pull-off through orifice (36),- the respective pull-off through orifice (36) being provided with an internal thread (37),- the guide vane carrier (2) being provided with an abutment zone (38) which lies axially opposite the pull-off through orifice (36),- the pull-off device (35) for introducing axially oriented pull-off forces into the respective guide vane (3) being formed by means of a pull-off tool (39) which is provided with an external thread (40) and which can be inserted into the pull-off through orifice (36) and can be pressed axially against the abutment zone (38) in order to pull off the respective guide vane (3) from the guide vane carrier (2).
- Guide vane arrangement according to Claim 1,- the pull-off device (35) for introducing the pull-off force being arranged and/or formed in the region of the fastening and/or parallel to and/or coaxially to the plugging direction of the fastening.
- Guide vane arrangement according to Claim 1 or 2,- the pull-off through orifice (36) and the internal thread (37) being formed on the respective guide vane (3), or- the pull-off through orifice (36) and the internal thread (37) being formed on a pull-off pin (23) which is a separate component in relation to the respective guide vane (3) and to the guide vane carrier (2).
- Guide vane arrangement according to Claim 3, the pull-off through orifice (36) and the internal thread (37) being formed on a pull-off pin (23) which is a separate component in relation to the respective guide vane (3) and to the guide vane carrier (2), comprising at least one of the following features:- the pull-off pin (23) is attached fixedly in terms of rotation to the respective guide vane (3);- the guide vane (3) is provided with an axially extending depression (24) into which the pull-off pin (23) is inserted;- the pull-off pin (23) is provided with two outer faces (23) which extend parallel to one another;- the pull-off pin (23) bears on the respective guide vane (3) against a supporting zone (43), lying opposite the abutment zone (38), of the guide vane (3);- the pull-off pin (23) is provided with at least one step (53) which bears against the supporting contour (43);- the pull-off pin (23) is inserted into a pin receptacle (25) which is formed on the guide vane carrier (2);- the abutment zone (38) is formed at one axial end of the pin receptacle (25).
- Guide vane arrangement according to Claim 1 or any one of the preceding claims, comprising the following features:- each guide vane (3) has a platform (6), comprising a first locking portion (8), and, spaced apart axially from this, a second locking portion (9);- the guide vane carrier (2) has a first carrying portion (12), and, spaced apart axially from this, a second carrying portion (13);- each locking portion (8, 9) and the respective carrying portion (12, 13) are designed such that they provide an axially pluggable and a radially positive fastening between the guide vane carrier (2) and the respective guide vane (3);- at least one securing element (14) is fastened to the guide vane carrier (2) and is designed such that it provides an axial fixing of at least one of the guide vanes (3);- the carrying portions (12, 13) and the locking portions (8, 9) extend in the circumferential direction;- the first locking portion (8) and the second locking portion (9) are arranged at a mutual radial spacing;- the first carrying portion (12) and the second carrying portion (13) are arranged at a mutual radial spacing.
- Guide vane arrangement according to Claim 5, comprising the following features:- the first carrying portion (12) has an inner collar (15) which projects radially inward and which extends in the circumferential direction;- the inner collar (15) is provided with an inner tongue (16) which extends axially and circumferentially;- the first locking portion (8) has an inner groove (17) which is axially open and which extends circumferentially;- the inner tongue (16) and inner groove (17) are configured such that they provide a first tongue-and-groove connection (18) between the guide vane carrier (2) and the respective guide vane (3);- the second locking portion (9) has an outer collar (19) which projects radially outward and which extends in the circumferential direction;- the outer collar (19) is provided with an outer tongue (20) which extends axially and circumferentially;- the second carrying portion (13) has an outer groove (21) which is axially open and which extends circumferentially;- the outer tongue (20) and outer groove (21) are configured such that they provide a second tongue-and-groove connection (22) between the guide vane carrier (2) and the respective guide vane (3).
- Guide vane arrangement according to Claim 6, the pull-off through orifice (36) or the pull-off pin (23) being arranged in or on the second locking portion (9) or in or on the outer collar (19).
- Guide vane arrangement according to any one of Claims 5 to 7, comprising the following features:- each platform (6) or at least one of the platforms (6) has a cavity (27) which is delimited radially inward by a base (28) and which is delimited axially and circumferentially by walls (29) which project radially outward from the base (28);- the guide vane carrier (2) has a common collecting duct (31) which extends circumferentially;- the casing (5) has at least one cooling-gas supply duct (32) which is connected fluidically to the common collecting duct (31);- the guide vane carrier (2) has a plurality of connecting orifices (34) which in each case connect the common collecting duct (31) fluidically to one of the cavities (27).
- Guide vane arrangement according to Claim 8,- one of the walls (29), which axially delimits the cavity (27), being equipped with the first locking portion (8), and- the other wall (29), which axially delimits the cavity (27), being equipped with the second locking portion (9), and/or- each guide vane (3) having a flow profile (7) which projects radially inward from the base (28), and- each flow profile (7) containing a cooling-gas path (30) which is connected fluidically to the cavity (27) by means of the base (28).
- Turbomachine, in particular a gas turbine, comprising at least one row of guide vanes (3), which is equipped with the guide vane arrangement (1) according to any one of Claims 1 to 9.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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SI200631516T SI1931859T1 (en) | 2005-10-06 | 2006-09-07 | Guide blade arrangement of a non-positive-displacement machine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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CH16142005 | 2005-10-06 | ||
PCT/EP2006/066140 WO2007039396A1 (en) | 2005-10-06 | 2006-09-07 | Guide blade arrangement of a non-positive-displacement machine |
Publications (2)
Publication Number | Publication Date |
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EP1931859A1 EP1931859A1 (en) | 2008-06-18 |
EP1931859B1 true EP1931859B1 (en) | 2012-11-07 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP06793334A Not-in-force EP1931859B1 (en) | 2005-10-06 | 2006-09-07 | Guide blade arrangement of a non-positive-displacement machine |
Country Status (6)
Country | Link |
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US (1) | US7674088B2 (en) |
EP (1) | EP1931859B1 (en) |
CA (1) | CA2624517C (en) |
SI (1) | SI1931859T1 (en) |
TW (1) | TWI371523B (en) |
WO (1) | WO2007039396A1 (en) |
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US8070429B2 (en) * | 2009-03-11 | 2011-12-06 | General Electric Company | Turbine singlet nozzle assembly with mechanical and weld fabrication |
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US9879565B2 (en) * | 2015-01-20 | 2018-01-30 | United Technologies Corporation | Enclosed jacking insert |
EP3312385A1 (en) * | 2016-10-24 | 2018-04-25 | Siemens Aktiengesellschaft | Thermal turbomachine |
US11208896B1 (en) * | 2020-10-20 | 2021-12-28 | Rolls-Royce Corporation | Turbine shroud having ceramic matrix composite component mounted with cooled pin |
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DE928746C (en) * | 1952-12-04 | 1955-06-10 | Maschf Augsburg Nuernberg Ag | Diffuser for exhaust gas fan |
GB804010A (en) * | 1956-02-13 | 1958-11-05 | Rolls Royce | Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines |
DE1036581B (en) | 1956-09-22 | 1958-08-14 | Maschf Augsburg Nuernberg Ag | Attachment of the nozzle ring of exhaust gas turbines |
DE1124969B (en) | 1959-07-03 | 1962-03-08 | Licentia Gmbh | Attachment of a nozzle ring in the housing of a steam or gas turbine |
US5131813A (en) | 1990-04-03 | 1992-07-21 | General Electric Company | Turbine blade outer end attachment structure |
EP0943785A1 (en) * | 1998-03-18 | 1999-09-22 | Asea Brown Boveri AG | Fixing a vane to a stator |
JP2002537070A (en) | 1999-02-26 | 2002-11-05 | ワーナー−ランバート・カンパニー | Bioadhesive antimicrobial wound healing composition |
DE10020229A1 (en) * | 2000-04-25 | 2001-10-31 | Alstom Power Nv | Method and device for dismantling a turbine blade |
DE10344098A1 (en) * | 2003-09-24 | 2005-04-21 | Alstom Technology Ltd Baden | Turbine blade mounting and puller has a keyway mounting for the blade foot and with a lipped grip on one side of the foot for a puller mounted on the hub |
DE502004011310D1 (en) * | 2004-07-09 | 2010-08-05 | Siemens Ag | Device for removing blades of a turbine or a compressor |
EP1931859B1 (en) | 2005-10-06 | 2012-11-07 | Alstom Technology Ltd | Guide blade arrangement of a non-positive-displacement machine |
-
2006
- 2006-09-07 EP EP06793334A patent/EP1931859B1/en not_active Not-in-force
- 2006-09-07 SI SI200631516T patent/SI1931859T1/en unknown
- 2006-09-07 WO PCT/EP2006/066140 patent/WO2007039396A1/en active Application Filing
- 2006-09-07 CA CA2624517A patent/CA2624517C/en not_active Expired - Fee Related
- 2006-10-04 TW TW095136885A patent/TWI371523B/en not_active IP Right Cessation
-
2008
- 2008-03-31 US US12/058,934 patent/US7674088B2/en active Active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3584413A1 (en) * | 2018-06-20 | 2019-12-25 | Safran Aircraft Engines | Cast and shrink-fit annular part of an aircraft turbine engine |
FR3082874A1 (en) * | 2018-06-20 | 2019-12-27 | Safran Aircraft Engines | ANNUAL FOUNDRY AND FREIGHT PARTY OF AN AIRCRAFT TURBOMACHINE |
US10920619B2 (en) | 2018-06-20 | 2021-02-16 | Safran Aircraft Engines | Annular casting and shrink-fitted part of an aircraft turbine engine |
Also Published As
Publication number | Publication date |
---|---|
TWI371523B (en) | 2012-09-01 |
CA2624517C (en) | 2014-05-13 |
TW200720527A (en) | 2007-06-01 |
US7674088B2 (en) | 2010-03-09 |
SI1931859T1 (en) | 2013-03-29 |
CA2624517A1 (en) | 2007-04-12 |
US20080193289A1 (en) | 2008-08-14 |
WO2007039396A1 (en) | 2007-04-12 |
EP1931859A1 (en) | 2008-06-18 |
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