EP2295724B1 - Stator vane for an axial-flow turbomachine and corresponding stator vane assembly - Google Patents
Stator vane for an axial-flow turbomachine and corresponding stator vane assembly Download PDFInfo
- Publication number
- EP2295724B1 EP2295724B1 EP09011070A EP09011070A EP2295724B1 EP 2295724 B1 EP2295724 B1 EP 2295724B1 EP 09011070 A EP09011070 A EP 09011070A EP 09011070 A EP09011070 A EP 09011070A EP 2295724 B1 EP2295724 B1 EP 2295724B1
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- EP
- European Patent Office
- Prior art keywords
- blade
- stator blade
- circumferential groove
- vane
- stator
- 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
- 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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
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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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
Definitions
- the invention relates to a guide vane for an axially flow-through turbomachine, comprising a two opposing sides having blade root with a platform and at least one arranged thereon blade. Furthermore, the invention relates to a stator blade assembly having a support structure, on the inner circumferential surface of which a circumferential groove is provided in which guide vanes held in a form-locking manner are arranged in a row.
- Such a guide vane and guide vane assembly for a compressor are, for example, from US 2005/0191177 A1 known.
- a circumferential groove is provided for each vane ring of a compressor stage.
- the sidewalls of the circumferential groove have undercuts to hold guide vanes inserted therein with correspondingly shaped, hammer-shaped blade roots in this form-fitting manner.
- Two adjacent vanes in the circumferential groove each have a bore in their opposite side surfaces.
- a clamping sleeve for mechanical coupling of the two immediately adjacent blade feet is used.
- a strained seat of blades known in a hammer-shaped circumferential groove For applying a force acting on the blades in the radial direction clamping force a circumferential groove is formed in the groove bottom of the circumferential groove, in which a force acting on the blade spring ring is used.
- the spring ring is formed in the form of a curved clamping sleeve, which in addition to the usual longitudinal slot also has a plurality of slots extending in its circumferential direction, whereby interposed freely ending spring arms are formed, by means of which the blades inserted in the circumferential groove are fixed braced in the radial direction.
- the object of the invention is the specification of an alternative vane arrangement and the provision of a suitable vane.
- a vane for an axially flow-through turbomachine comprising a two opposing sides blade root with a platform and at least one arranged thereon blade, the blade root having on one of the two sides at least one protruding molding, in which at least one threaded hole is provided for radially clamping the guide vane in a circumferential groove of a supporting structure of a turbomachine by means of a clamping screw screwed into the threaded hole, supported on the groove base of the circumferential groove and wherein the blade root on the other of the two sides has at least one recess for receiving at least one Having molded piece of an adjacent vane including a screwed therein screw.
- the guide vane arrangement according to the invention makes it possible to achieve a radially fixed clamping of the guide vane in the support structure of an axial-flow turbomachine. Since the clamping force is generated only when screwing and tightening the clamping screw, the guide vane and in particular the blade root can be manufactured with comparatively large tolerances and with comparatively low accuracy of fit with respect to the contour of the circumferential groove. On the one hand this facilitates the positioning, i. Insertion and displacement of the vane in the circumferential groove. On the other hand, the gaps required for thermal expansion can thereby be kept at a sufficient size, which renders the vane arrangement less susceptible to thermal influences.
- the tensioning of the guide blade on the support structure blocks relative movements of the guide vanes and thereby reduces possible wear.
- the guide vanes due to their play-free attachment to a defined radial position, whereby the radial gaps between the free-standing blade tips of the vanes and the rotor opposite these blades tips can be set and manufactured closer than before. This reduces the radial gap losses occurring in the flow medium at the blade tips of freestanding vanes during operation of the turbomachine, which increases the efficiency of the turbomachine.
- the clamping screw required for clamping In order for the clamping screw required for clamping the guide vane does not protrude into the flow channel of the turbomachine is at one of the two opposite Side of the blade root arranged therefrom a shaped piece.
- the fitting is arranged substantially closer to the underside of the blade root than at the surface of the platform.
- a threaded hole is provided in which the clamping screw can be screwed. Since the fitting protrudes laterally, the threaded hole and the clamping screw for assembly work are particularly accessible.
- the platform of that guide vane which is arranged directly adjacent to a respective vane, covers the shaped piece including the clamping screw of the relevant vane.
- at least one recess in a size is provided on the other of the two opposite sides of the blade root, which corresponds at least to the installation space of the shaped piece including the clamping screw screwed therein.
- the Leitschaufelfuß is hammer-shaped.
- the guide vane on one side comprises two fittings, each with a threaded hole.
- a tension of the guide blade take place, in which the clamping force is generated in each case close to the side walls of the circumferential groove and not like a vane with only one fitting, centered in between. This increases the security of the tension.
- two threaded holes are provided with a comparable distance in a correspondingly large fitting.
- the vane may also be formed as a vane segment, which has two or more blades.
- the turbomachine is an axially flow-through compressor, so that the guide vane is formed as a compressor vane or as a compressor vane segment.
- At least one of the guide vanes has a fuse for receiving blade root reaction forces in the circumferential direction.
- each vane has been secured in this way so far. Due to the now reliable and strained with relatively large force vane, the number of previously used fuses can be reduced to accommodate blade root reaction forces, so that, for example, only every fourth or every third vane to accommodate such forces must be secured.
- the support structure is designed as a guide blade carrier or as a turbomachine housing, which is split in half along its axial extension. This facilitates the insertion of vanes in the circumferential groove. Also, the provision of a vane lock is avoided, which would otherwise be required for a one-piece support structure with a then endless circumferential groove.
- FIG. 2 show in perspective from different directions a guide vane 10 according to the invention for a turbomachine.
- the vane 10 includes a blade root 12 having two opposite sides 14, 16. Between the two opposite sides 14, 16, a platform 18 is arranged, protruding from the surface 20 of a transversely extending aerodynamically curved blade 22 freestanding.
- a protruding molding 24 is integrally formed in the manner of a tab.
- the molding 24 is arranged centrally near a blade root bottom 25.
- a threaded hole 26 is present, whose threaded axis is oriented perpendicular to the plane of the surface 20 of the platform 18.
- a recess 29 is provided at the other (14) of the two sides 14, 16 .
- the recess 29 of the relevant vane 10 is chosen in its position and size so that when adjacent in a ring vanes 10, the or each fitting 24 - including one disposed therein, in 1 and FIG. 2 Clamping screw not shown - one to the respective vane 10 immediately adjacent vane 10 can be fully absorbed.
- the vane 10 also has two hooks 27 which protrude at a web 23 connecting the two sides 14, 16. Between hook 27 and platform 18 is thereby a respective groove 28 for receiving projections of the circumferential groove is present, in which the guide vane 10 is to be used.
- the web 23 and the hooks 27 have a hammer-like appearance, after which the blade root 12 is also referred to as hammer-shaped.
- the juxtaposed in the circumferential groove vanes 10 are always in such a way that the one side 16 of a first vane 10 of the other side 14 of a second vane 10 is as far as possible opposite each other.
- FIG. 3 shows the longitudinal section through an annular support structure 30, which is part of a stator carrier or a housing of the axially flow-through turbomachine.
- a circumferential groove 34 extending in the circumferential direction is provided.
- the circumferential groove 34 has two mutually opposite side walls 36, 38, on which projections 40, 42 are provided for the positive retention of the guide vane 10.
- guide vane 10 differs from that in the 1 and FIG.
- each have a clamping screw 44 is screwed.
- the clamping screw 44 may be formed for example as a grub screw or as an ordinary screw with a screw head.
- the screw end of the clamping screw 44 is supported on the groove base 35 of the circumferential groove 34 and presses the arranged on the blade root 12 hook 27 to the projections 40, 42 of the circumferential groove 34, whereby the guide vane 10 in the radial direction of the axial flow-through turbomachine firmly biased.
- FIG. 4 shows the cross section through FIG. 3 according to the section line IV-IV, wherein also in FIG. 4 identical features are provided with identical reference numerals.
- the fitting 24 protrudes on the side 16 and is part of the blade root bottom 25.
- recess 29 for receiving a fitting 24 of an adjacent vane 10 of a screwed therein clamping screw 44 can be seen.
- the recess 29 is arranged according to the shaped piece 24 also on the blade root lower side 25.
- FIG. 5 In the following description of the figures and in this figure, the reference numerals of the features associated with a first guide vane 10a are extended by the suffix a, the reference symbols of the features associated with a second guide vane 10b by the suffix b and the reference numerals of the features associated with a third vane 10c by the suffix c.
- the first vane 10a is already positioned at its destination and with the help of two madenartiger clamping screws 44a in the circumferential groove 34 firmly clamped.
- two second and third vanes 10b, 10c are already threaded in the circumferential groove 34.
- the second vane 10b immediately adjacent thereto is displaced in the circumferential direction, ie in the direction of the arrow 52, until its platforms 18a, 18b abut one another.
- the fitting 24a of the first vane 10a is disposed in the recess 29b of the second vane 10b, so that from the flow channel view, the platform 18b of the second vane 10b completely covers the molding 24a of the first vane 10a.
- the surface 20b of the platform 18b covers the recess 29b when projected radially.
- the second vane 10b is fastened with the aid of further clamping screws at the corresponding position.
- the third vane 10c can be slid over the molding 24b of the second vane 10b, so that its clamping screws are also covered by the platform 18c of the third vane 10c.
- a complete vane ring for an axial flow turbomachine can be mounted, in which case all vanes 10 are pressed with a defined bias to the projections 40, 42 of the holding 34.
- the vanes 10 are also for receiving blade root reaction forces according to FIG. 6 further secured.
- a through hole is provided, into which from the rear side of the support structure 30 of a further screw 54 can be screwed with a pin which engages in a corresponding recess on the underside of the blade root 12 of the guide vane 10.
- the invention is not limited to those in 1, 2 and 3 Of course, it is possible, on one side 16 and then two eccentric fittings 24, each with a threaded hole 26 to provide.
- the other side 14 of such a vane 10 then has one or two recesses 29 for receiving the corresponding fittings 24.
- the invention provides a guide vane 10 and a guide vane assembly 50 for an axially flow-through turbomachine, in particular compressors, in which each vane 10 is held in a circumferential groove 34 via a fixed restraint.
- a protruding molding 24 is provided with a threaded hole 26 on one side 16 of the blade root 12, in which a on the groove base 35 of the circumferential groove 34 supporting clamping screw 44 can be screwed.
- a particular advantage of the invention is that in the vane ring both the fitting 24 and the clamping screw 44 screwed therein is completely covered by the platform 18 of a neighboring vane 10, so that the intermeshing thread of threaded hole 26 and clamping screw 44 in front of the flow channel the turbo-machine working medium flowing through the surface 20 of the platform 18 is shielded.
- the shield prevents corrosion and the setting of the clamping screw 44, which ensures the disassembly of the guide vanes 10 from the circumferential groove 34 even after a long period of operation safely.
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Abstract
Description
Die Erfindung betrifft eine Leitschaufel für eine axial durchströmbare Turbomaschine, umfassend einen zwei einander gegenüberliegende Seiten aufweisenden Schaufelfuß mit einer Plattform und zumindest ein daran angeordnetes Schaufelblatt. Ferner betrifft die Erfindung eine Leitschaufelanordnung mit einer Tragstruktur, an dessen Innenmantelfläche eine Umfangsnut vorgesehen ist, in welcher durch Formschluss gehaltene Leitschaufeln aneinandergereiht sitzen.The invention relates to a guide vane for an axially flow-through turbomachine, comprising a two opposing sides having blade root with a platform and at least one arranged thereon blade. Furthermore, the invention relates to a stator blade assembly having a support structure, on the inner circumferential surface of which a circumferential groove is provided in which guide vanes held in a form-locking manner are arranged in a row.
Eine derartige Leitschaufel und Leitschaufelanordnung für einen Verdichter sind beispielsweise aus der
Daneben ist aus der
Aufgabe der Erfindung ist die Angabe einer alternativen Leitschaufelanordnung und die Bereitstellung einer dafür geeigneten Leitschaufel.The object of the invention is the specification of an alternative vane arrangement and the provision of a suitable vane.
Die auf die Leitschaufel gerichtete Aufgabe wird mit einer Leitschaufel für eine axial durchströmbare Turbomaschine gelöst, welche einen zwei einander gegenüberliegende Seiten aufweisenden Schaufelfuß mit einer Plattform und zumindest ein daran angeordnetes Schaufelblatt umfasst, wobei der Schaufelfuß an einer der beiden Seiten zumindest ein hervorstehendes Formstück aufweist, in dem zumindest ein Gewindeloch zum radialen Verspannen der Leitschaufel in einer Umfangsnut einer Tragstruktur einer Turbomaschine mittels einer im Gewindeloch eingeschraubten, sich am Nutgrund der Umfangsnut abstützenden Spannschraube vorgesehen ist und bei der der Schaufelfuß an der anderen der beiden Seiten zumindest eine Ausnehmung zur Aufnahme mindestens eines Formstücks einer benachbarten Leitschaufel einschließlich einer darin eingeschraubten Spannschraube aufweist.The task directed to the vane is achieved with a vane for an axially flow-through turbomachine comprising a two opposing sides blade root with a platform and at least one arranged thereon blade, the blade root having on one of the two sides at least one protruding molding, in which at least one threaded hole is provided for radially clamping the guide vane in a circumferential groove of a supporting structure of a turbomachine by means of a clamping screw screwed into the threaded hole, supported on the groove base of the circumferential groove and wherein the blade root on the other of the two sides has at least one recess for receiving at least one Having molded piece of an adjacent vane including a screwed therein screw.
Die auf die Leitschaufelanordnung gerichtete Aufgabe wird mit einer ringförmigen Tragstruktur gelöst, an dessen Innenmantelfläche eine Umfangsnut vorgesehen ist, in welcher durch Formschluss gehaltene Leitschaufeln gemäß vorgenannter Ausgestaltung aneinandergereiht sitzen, wobei jede derartige Leitschaufel mittels einer im Gewindeloch ihres Formstücks eingeschraubten, sich am Nutgrund der Umfangsnut abstützenden Spannschraube in der Umfangsnut verspannt ist und das Formstück einschließlich der Spannschraube vollständig von der Plattform derjenigen Leitschaufel überdeckt ist, welche zur betreffenden Leitschaufel unmittelbar benachbart ist.The directed to the vane assembly task is solved with an annular support structure, on whose inner circumferential surface a circumferential groove is provided, in which held by positive locking vanes sit according to the aforementioned embodiment, each such vane screwed by means of a screwed in the threaded hole of its mold, at the groove bottom of the circumferential groove supporting clamping screw is clamped in the circumferential groove and the fitting including the clamping screw is completely covered by the platform of that vane, which is immediately adjacent to the relevant vane.
Durch die erfindungsgemäße Leitschaufelanordnung kann eine in Radialrichtung feste Einspannung der Leitschaufel in der Tragstruktur einer axial durchströmbaren Turbomaschine erreicht werden. Da die Spannkraft erst beim Einschrauben und Anziehen der Spannschraube erzeugt wird, kann die Leitschaufel und insbesondere deren Schaufelfuß mit vergleichsweise großen Toleranzen und mit vergleichsweise geringer Passgenauigkeit gegenüber der Kontur der Umfangsnut gefertigt werden. Dies erleichtert einerseits die Positionierung, d.h. Einsetzen und Verschieben der Leitschaufel in der Umfangsnut. Andererseits können dadurch die für eine thermische Dehnung benötigten Spalte in einer ausreichenden Größe vorgehalten werden, was die Leitschaufelanordnung unempfindlicher gegen thermische Einflüsse macht.The guide vane arrangement according to the invention makes it possible to achieve a radially fixed clamping of the guide vane in the support structure of an axial-flow turbomachine. Since the clamping force is generated only when screwing and tightening the clamping screw, the guide vane and in particular the blade root can be manufactured with comparatively large tolerances and with comparatively low accuracy of fit with respect to the contour of the circumferential groove. On the one hand this facilitates the positioning, i. Insertion and displacement of the vane in the circumferential groove. On the other hand, the gaps required for thermal expansion can thereby be kept at a sufficient size, which renders the vane arrangement less susceptible to thermal influences.
Da die Montagespiele und damit die Fertigungstoleranzen aufgrund des Ausgleichs der größeren Spiele durch die Spannschraube vergrößert werden können, entsteht auch ein Kostenvorteil in der Fertigung der entsprechenden Bauteile.Since the assembly games and thus the manufacturing tolerances due to the compensation of the larger games can be increased by the clamping screw, there is also a cost advantage in the production of the corresponding components.
Ferner werden durch die Verspannung der Leitschaufel an der Tragstruktur Relativbewegungen der Leitschaufeln blockiert und dadurch möglicher Verschleiß reduziert.Furthermore, the tensioning of the guide blade on the support structure blocks relative movements of the guide vanes and thereby reduces possible wear.
Zudem weisen die Leitschaufeln aufgrund ihrer spielfreien Befestigung eine definierte radiale Lage auf, wodurch die Radialspalte zwischen den freistehenden Blattspitzen der Leitschaufeln und dem diesen Blattspitzen gegenüberliegenden Rotor enger eingestellt und gefertigt werden können als bisher. Dies reduziert die im Strömungsmedium auftretenden Radialspaltverluste an den Blattspitzen von freistehenden Leitschaufeln während des Betriebs der Turbomaschine, was den Wirkungsgrad der Turbomaschine steigert.In addition, the guide vanes due to their play-free attachment to a defined radial position, whereby the radial gaps between the free-standing blade tips of the vanes and the rotor opposite these blades tips can be set and manufactured closer than before. This reduces the radial gap losses occurring in the flow medium at the blade tips of freestanding vanes during operation of the turbomachine, which increases the efficiency of the turbomachine.
Damit die zur Verspannung der Leitschaufel benötigte Spannschraube nicht in den Strömungskanal der Turbomaschine hineinragt, ist an einer der beiden einander gegenüberliegenden Seiten des Schaufelfußes ein davon hervorstehendes Formstück angeordnet. Das Formstück ist dabei wesentlich näher an der Unterseite des Schaufelfußes angeordnet als an der Oberfläche der Plattform. In dem Formstück ist ein Gewindeloch vorgesehen, in dem die Spannschraube eingeschraubt werden kann. Da das Formstück seitlich hervorsteht, sind das Gewindeloch und die Spannschraube für die Montagearbeiten besonders gut zugänglich.In order for the clamping screw required for clamping the guide vane does not protrude into the flow channel of the turbomachine is at one of the two opposite Side of the blade root arranged therefrom a shaped piece. The fitting is arranged substantially closer to the underside of the blade root than at the surface of the platform. In the fitting a threaded hole is provided in which the clamping screw can be screwed. Since the fitting protrudes laterally, the threaded hole and the clamping screw for assembly work are particularly accessible.
Um eine Strömungskanalbegrenzung der Turbomaschine mit möglichst wenig Bauteilkanten bereitzustellen, ist vorgesehen, dass die Plattform derjenigen Leitschaufel, welche zu einer betreffenden Leitschaufel unmittelbar benachbart angeordnet ist, das Formstück einschließlich der Spannschraube der betreffenden Leitschaufel überdeckt. Hierzu ist an der anderen der zwei einander gegenüberliegenden Seiten des Schaufelfußes zumindest eine Ausnehmung in einer Größe vorgesehen, welche mindestens dem Bauraum des Formstücks einschließlich der darin eingeschraubten Spannschraube entspricht. Durch diese Maßnahme kann lokal eine Strömungskanalbegrenzung allein durch die Oberflächen der Plattformen des Schaufelfußes erreicht werden, ohne dass weitere Bauteile in der Umfangsnut zur Abdeckung des Formstücks einschließlich Spannschraube erforderlich sind. Zudem sind die Spannschrauben mittels der Plattform der benachbarten Leitschaufel vom Strömungsmedium abgeschirmt und somit vor dessen Einflüssen geschützt. Dies verhindert Korrosion und das Festsetzen der Spannschrauben im Gewinde des Lochs.In order to provide a flow channel boundary of the turbomachine with as few component edges as possible, it is provided that the platform of that guide vane, which is arranged directly adjacent to a respective vane, covers the shaped piece including the clamping screw of the relevant vane. For this purpose, at least one recess in a size is provided on the other of the two opposite sides of the blade root, which corresponds at least to the installation space of the shaped piece including the clamping screw screwed therein. By this measure, locally a flow channel limitation can be achieved only by the surfaces of the platforms of the blade root, without further components in the circumferential groove to cover the fitting including clamping screw are required. In addition, the clamping screws are shielded by the platform of the adjacent vane from the flow medium and thus protected from its influence. This prevents corrosion and the setting of the clamping screws in the thread of the hole.
Weitere vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Further advantageous embodiments are specified in the subclaims.
Zweckmäßiger Weise ist der Leitschaufelfuß hammerförmig ausgebildet. Gemäß einer weiteren vorteilhaften Ausgestaltung umfasst die Leitschaufel an der einen Seite zwei Formstücke mit jeweils einem Gewindeloch. Hierdurch kann eine Verspannung der Leitschaufel erfolgen, bei der die Spannkraft jeweils nahe an den Seitenwänden der Umfangsnut erzeugt wird und nicht wie bei einer Leitschaufel mit nur einem Formstück, mittig dazwischen. Dies steigert die Sicherheit der Verspannung. Selbstverständlich ist auch denkbar, dass in einem entsprechend großen Formstück zwei Gewindelöcher mit vergleichbarem Abstand vorgesehen sind.Appropriately, the Leitschaufelfuß is hammer-shaped. According to a further advantageous embodiment, the guide vane on one side comprises two fittings, each with a threaded hole. As a result, a tension of the guide blade take place, in which the clamping force is generated in each case close to the side walls of the circumferential groove and not like a vane with only one fitting, centered in between. This increases the security of the tension. Of course, it is also conceivable that two threaded holes are provided with a comparable distance in a correspondingly large fitting.
Selbstverständlich kann die Leitschaufel auch als Leitschaufelsegment ausgebildet sein, welche zwei oder mehr Schaufelblätter aufweist.Of course, the vane may also be formed as a vane segment, which has two or more blades.
Vorzugsweise handelt es sich bei der Turbomaschine um einen axial durchströmbaren Verdichter, so dass die Leitschaufel als Verdichterleitschaufel oder als Verdichterleitschaufelsegment ausgebildet ist.Preferably, the turbomachine is an axially flow-through compressor, so that the guide vane is formed as a compressor vane or as a compressor vane segment.
Gemäß einer vorteilhaften Ausgestaltung der Leitschaufelanordnung weist zumindest eine der Leitschaufeln eine Sicherung zur Aufnahme von Schaufelfußreaktionskräften in umlaufender Richtung auf. Üblicher Weise war bisher jede Leitschaufel derartig gesichert. Aufgrund der nunmehr zuverlässigen und mit vergleichsweise großer Kraft verspannten Leitschaufel kann die Anzahl an bisher verwendeten Sicherungen zur Aufnahme an Schaufelfußreaktionskräften reduziert werden, so dass beispielsweise nur noch jede vierte oder jede dritte Leitschaufel zur Aufnahme derartiger Kräfte gesichert werden muss.According to an advantageous embodiment of the vane arrangement, at least one of the guide vanes has a fuse for receiving blade root reaction forces in the circumferential direction. Usually, each vane has been secured in this way so far. Due to the now reliable and strained with relatively large force vane, the number of previously used fuses can be reduced to accommodate blade root reaction forces, so that, for example, only every fourth or every third vane to accommodate such forces must be secured.
Gemäß einer anderen vorteilhaften Ausgestaltung ist die Tragstruktur als Leitschaufelträger oder als Turbomaschinengehäuse ausgebildet, welches entlang seiner Axialerstreckung hälftig teilbar ist. Dies erleichtert das Einsetzen von Leitschaufeln in der Umfangsnut. Auch wird das Vorsehen eines Leitschaufelschlosses vermieden, welches ansonsten bei einer einstückigen Tragstruktur mit einer dann endlosen Umfangsnut erforderlich wäre.According to another advantageous embodiment, the support structure is designed as a guide blade carrier or as a turbomachine housing, which is split in half along its axial extension. This facilitates the insertion of vanes in the circumferential groove. Also, the provision of a vane lock is avoided, which would otherwise be required for a one-piece support structure with a then endless circumferential groove.
Weitere Vorteile, Merkmale und Eigenschaften der Erfindung werden anhand von bevorzugten Ausführungsbeispielen und nachfolgenden Zeichnungen näher erläutert. Es zeigen:
- FIG 1, 2
- eine erfindungsgemäße Leitschaufel gemäß einer ers- ten Ausgestaltung in unterschiedlichen perspektivi- schen Ansichten,
- FIG 3
- den Längsschnitt durch eine Tragstruktur und Leit- schaufel gemäß einer zweiten Ausgestaltung,
- FIG 4
- den Querschnitt durch die Ausgestaltung gemäß
FIG 3 , - FIG 5
- die Abwicklung einer in einer Tragstruktur ange- ordneten Umfangsnut mit darin angeordneten Leit- schaufeln und
- FIG 6
- die Draufsicht auf eine in einer Umfangsnut ange- ordneten Leitschaufel einschließlich einer Siche- rung zur Aufnahme von Schaufelfußreaktionskräften.
- FIG. 1, 2
- FIG. 2 shows a guide vane according to the invention in different perspective views, according to a first embodiment; FIG.
- FIG. 3
- 3 a longitudinal section through a support structure and guide blade according to a second embodiment,
- FIG. 4
- the cross section through the embodiment according to
FIG. 3 . - FIG. 5
- the development of a arranged in a support structure circumferential groove with therein arranged guide vanes and
- FIG. 6
- the top view of a arranged in a circumferential groove vane including a fuse for receiving Schaufelfußreaktionskräften.
An einer (16) der beiden Seiten 14, 16 ist ein hervorstehendes Formstück 24 nach Art einer Lasche angeformt. Das Formstück 24 ist dabei nahe einer Schaufelfußunterseite 25 mittig angeordnet. Im Formstück 24 ist ein Gewindeloch 26 vorhanden, dessen Gewindeachse senkrecht zur Ebene der Oberfläche 20 der Plattform 18 ausgerichtet ist.On one (16) of the two
An der anderen (14) der beiden Seiten 14, 16 ist eine Ausnehmung 29 vorgesehen. Die Ausnehmung 29 der betreffenden Leitschaufel 10 ist dabei in ihrer Lage und ihrer Größe so gewählt, dass bei in einem Kranz aneinanderliegenden Leitschaufeln 10 das oder jedes Formstück 24 - einschließlich einer darin angeordneten, in
Die Leitschaufel 10 weist zudem zwei Haken 27 auf, die an einem die beiden Seiten 14, 16 verbindenden Steg 23 hervorstehen. Zwischen Haken 27 und Plattform 18 ist dadurch jeweils eine Nut 28 zur Aufnahme von Vorsprüngen der Umfangsnut vorhanden, in welche die Leitschaufel 10 eingesetzt werden soll. Der Steg 23 und die Haken 27 haben eine hammerförmige Anmutung, wonach der Schaufelfuß 12 auch als hammerförmig bezeichnet wird.The
Die in der Umfangsnut aneinandergereihten Leitschaufeln 10 liegen stets derartig aneinander, dass die eine Seite 16 einer ersten Leitschaufel 10 der anderen Seite 14 einer zweiten Leitschaufel 10 möglichst spaltlos einander gegenüber steht.The juxtaposed in the
In den Gewindelöchern 26 ist jeweils eine Spannschraube 44 eingeschraubt. Die Spannschraube 44 kann beispielsweise als Madenschraube oder auch als gewöhnliche Schraube mit einem Schraubenkopf ausgebildet sein. Das Schraubenende der Spannschraube 44 stützt sich am Nutgrund 35 der Umfangsnut 34 ab und drückt dabei die am Schaufelfuß 12 angeordneten Haken 27 an die Vorsprünge 40, 42 der Umfangsnut 34, wodurch die Leitschaufel 10 in Radialrichtung der axial durchströmbaren Turbomaschine fest vorgespannt anliegt.In the threaded
Die Leitschaufeln 10 sind zudem zur Aufnahme von Schaufelfußreaktionskräften gemäß
Die Erfindung beschränkt sich nicht auf die in
Insgesamt wird mit der Erfindung eine Leitschaufel 10 und eine Leitschaufelanordnung 50 für eine axial durchströmbare Turbomaschine, insbesondere Verdichter angegeben, bei der jede Leitschaufel 10 über eine feste Einspannung in einer Umfangsnut 34 gehaltert ist. Zur festen Einspannung ist an einer Seite 16 des Schaufelfußes 12 ein hervorstehendes Formstück 24 mit einem Gewindeloch 26 vorgesehen, in welches eine sich am Nutgrund 35 der Umfangsnut 34 abstützende Spannschraube 44 einschraubbar ist. Ein besonderer Vorteil der Erfindung liegt darin, dass im Leitschaufelkranz sowohl das Formstück 24 als auch die darin eingeschraubte Spannschraube 44 von der Plattform 18 einer dazu benachbarten Leitschaufel 10 vollständig überdeckt ist, so dass die ineinandergreifenden Gewinde von Gewindeloch 26 und Spannschraube 44 vor dem im Strömungskanal der Turbomaschine strömenden Arbeitsmedium durch die Oberfläche 20 der Plattform 18 abgeschirmt ist. Die Abschirmung verhindert Korrosion und das Festsetzen der Spannschraube 44, was die Demontage der Leitschaufeln 10 aus der Umfangsnut 34 selbst nach längerer Betriebsdauer sicher gewährleistet.Overall, the invention provides a
Claims (9)
- Stator blade (10) for a turbomachine which is exposable to axial throughflow,
comprising a blade root (12), having two oppositely disposed sides (14, 16), with a platform (18) and at least one blade airfoil (22) which is arranged thereupon,
characterized in that
the blade root (12) on one of the two sides (16) has at least one projecting shaped piece (24) in which provision is made for at least one threaded hole (26) for the radial tensioning of the stator blade (10) in a circumferential groove (34) of a carrier structure (30) of a turbomachine by means of a tensioning screw (44) which is screwed into the threaded hole and supported on the bottom (35) of the circumferential groove (34), and in which the blade root (12) on the other of the two sides (14) has at least one recess (29) for accommodating at least one shaped piece (24) of an adjacent stator blade (10), including a tensioning screw (44) which is screwed into it. - Stator blade (10) according to Claim 1,
the blade root (12) of which is of an inverted T-shaped design. - Stator blade (10) according to Claim 1 or 2,
with two shaped pieces (24), having one threaded hole (26) in each case, or with two threaded holes (26) in the one shaped piece (24). - Stator blade (10) according to one of Claims 1 to 3,
in which the shaped piece (24) is formed at least comparatively close to the underside (25) of the blade root. - Stator blade (10) according to one of Claims 1 to 4,
which has two or more blade airfoils (22) as a stator blade segment. - Stator blade (10) according to one of Claims 1 to 5,
formed as a compressor stator blade of a compressor which is exposable to axial throughflow. - Stator blade arrangement (50) for a turbomachine, preferably a compressor,
with an annular carrier structure (30), on the inner generated surface (32) of which provision is made for a circumferential groove (34) in which stator blades (10), which are retained by means of a form fit, according to one of Claims 1 to 5 are seated in a butt-mounted manner, wherein each such stator blade (10) is tensioned in the circumferential groove (34) by means of a tensioning screw (44) which is screwed in the threaded hole (26) of its shaped piece (24) and supported on the bottom (35) of the circumferential groove (34), and the shaped piece (24), including the tensioning screw (44), is fully covered by the platform (18) of that stator blade (10) which is directly adjacent to the stator blade (10) in question. - Stator blade arrangement (50) according to Claim 7,
in which at least one of the stator blades (10) has a locking device for absorbing blade root reaction forces in the circumferential direction. - Stator blade arrangement (50) according to Claim 7 or 8,
in which the carrier structure (30) can be split in half.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09011070A EP2295724B1 (en) | 2009-08-28 | 2009-08-28 | Stator vane for an axial-flow turbomachine and corresponding stator vane assembly |
AT09011070T ATE547591T1 (en) | 2009-08-28 | 2009-08-28 | GUIDE VANE FOR AN AXIAL FLOW TURBO MACHINE AND ASSOCIATED GUIDE VANE ARRANGEMENT |
US12/868,946 US8622708B2 (en) | 2009-08-28 | 2010-08-26 | Stator blade for a turbomachine which is exposable to axial throughflow, and also stator blade arrangement for it |
CN201010268815XA CN102003219B (en) | 2009-08-28 | 2010-08-27 | Stator vane for axial-flow turbomachine and corresponding stator vane assembly |
JP2010190834A JP5073027B2 (en) | 2009-08-28 | 2010-08-27 | Stator blades and vane structure for axially flowable turbomachines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09011070A EP2295724B1 (en) | 2009-08-28 | 2009-08-28 | Stator vane for an axial-flow turbomachine and corresponding stator vane assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2295724A1 EP2295724A1 (en) | 2011-03-16 |
EP2295724B1 true EP2295724B1 (en) | 2012-02-29 |
Family
ID=41395104
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09011070A Not-in-force EP2295724B1 (en) | 2009-08-28 | 2009-08-28 | Stator vane for an axial-flow turbomachine and corresponding stator vane assembly |
Country Status (5)
Country | Link |
---|---|
US (1) | US8622708B2 (en) |
EP (1) | EP2295724B1 (en) |
JP (1) | JP5073027B2 (en) |
CN (1) | CN102003219B (en) |
AT (1) | ATE547591T1 (en) |
Families Citing this family (19)
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PL2739861T3 (en) | 2011-08-04 | 2020-01-31 | Novenco Building & Industry A/S | Axial blower |
US8888459B2 (en) * | 2011-08-23 | 2014-11-18 | General Electric Company | Coupled blade platforms and methods of sealing |
DE102012200057A1 (en) * | 2012-01-03 | 2013-07-04 | Siemens Aktiengesellschaft | Attaching a lock blade to a rotor unit |
JP5555727B2 (en) * | 2012-01-23 | 2014-07-23 | 川崎重工業株式会社 | Axial flow compressor blade manufacturing method |
JP6012222B2 (en) | 2012-03-30 | 2016-10-25 | 三菱重工業株式会社 | Stator blade segment, axial fluid machine including the same, and stator vane coupling method thereof |
US10309235B2 (en) | 2012-08-27 | 2019-06-04 | United Technologies Corporation | Shiplap cantilevered stator |
US10125783B2 (en) | 2013-02-25 | 2018-11-13 | Greenheck Fan Corporation | Fan assembly and fan wheel assemblies |
US10184488B2 (en) | 2013-02-25 | 2019-01-22 | Greenheck Fan Corporation | Fan housing having flush mounted stator blades |
CN105392997B (en) | 2013-02-25 | 2018-07-10 | 格林瀚克通风设备有限公司 | Flow-mixing blower fan component |
US9505092B2 (en) | 2013-02-25 | 2016-11-29 | Greenheck Fan Corporation | Methods for fan assemblies and fan wheel assemblies |
BE1022361B1 (en) * | 2014-11-06 | 2016-03-17 | Techspace Aero Sa | Mixed axial turbine engine compressor stator. |
JP2019503295A (en) * | 2015-11-10 | 2019-02-07 | マターネット, インコーポレイテッドMatternet, Inc. | Method and system for transport using unmanned aerial vehicles |
JP6641654B2 (en) * | 2016-01-08 | 2020-02-05 | 三菱日立パワーシステムズ株式会社 | Method for removing a moving blade, removal device for performing the method, and rotor set including the removal device |
GB2551164B (en) * | 2016-06-08 | 2019-12-25 | Rolls Royce Plc | Metallic stator vane |
CN106988794B (en) * | 2017-06-02 | 2018-12-14 | 中国航发南方工业有限公司 | Stator sub-assembly clamping means and stator sub-assembly |
US10934863B2 (en) * | 2018-11-13 | 2021-03-02 | Rolls-Royce Corporation | Turbine wheel assembly with circumferential blade attachment |
CN114340998A (en) * | 2019-10-09 | 2022-04-12 | 小鹰公司 | Hybrid power system for different flight modes |
DE102020200447A1 (en) * | 2020-01-15 | 2021-07-15 | Ziehl-Abegg Se | Housing for a fan and fan with a corresponding housing |
CN112943685B (en) * | 2021-03-10 | 2022-09-13 | 哈电发电设备国家工程研究中心有限公司 | Pull rod type blade root connecting structure |
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US1061640A (en) * | 1910-10-10 | 1913-05-13 | Colonial Trust Co | Blading. |
US3252687A (en) * | 1965-02-01 | 1966-05-24 | Gen Motors Corp | Rotor blade locking |
CH581783A5 (en) * | 1975-01-30 | 1976-11-15 | Bbc Sulzer Turbomaschinen | |
US4645425A (en) * | 1984-12-19 | 1987-02-24 | United Technologies Corporation | Turbine or compressor blade mounting |
US5713721A (en) * | 1996-05-09 | 1998-02-03 | General Electric Co. | Retention system for the blades of a rotary machine |
DE29715180U1 (en) * | 1997-08-23 | 1997-10-16 | MTU Motoren- und Turbinen-Union München GmbH, 80995 München | Guide blade for a gas turbine |
ITMI20012783A1 (en) * | 2001-12-21 | 2003-06-21 | Nuovo Pignone Spa | CONNECTION AND LOCKING SYSTEM OF ROTORIAL BLADES OF AN AXIAL COMPRESSOR |
US6821087B2 (en) * | 2002-01-21 | 2004-11-23 | Honda Giken Kogyo Kabushiki Kaisha | Flow-rectifying member and its unit and method for producing flow-rectifying member |
US7651319B2 (en) | 2002-02-22 | 2010-01-26 | Drs Power Technology Inc. | Compressor stator vane |
US6761538B2 (en) * | 2002-10-31 | 2004-07-13 | General Electric Company | Continual radial loading device for steam turbine reaction type buckets and related method |
ATE391835T1 (en) * | 2004-07-22 | 2008-04-15 | Siemens Ag | SAFETY DEVICE FOR A ROTATING BLADE OF A FLOW MACHINE ARRANGED ON A ROTATING ROTOR DISC, FLOW MACHINE AND METHOD FOR MOUNTING AND DISASSEMBLING A ROTOR BLADE ON A ROTOR DISC OF A FLOW MACHINE |
JP4760090B2 (en) * | 2005-03-30 | 2011-08-31 | ブラザー工業株式会社 | Conveying apparatus and image forming apparatus |
EP1788198A2 (en) * | 2005-11-21 | 2007-05-23 | The General Electric Company | Turbine blades retention system and method |
US8511983B2 (en) * | 2008-02-19 | 2013-08-20 | United Technologies Corporation | LPC exit guide vane and assembly |
-
2009
- 2009-08-28 EP EP09011070A patent/EP2295724B1/en not_active Not-in-force
- 2009-08-28 AT AT09011070T patent/ATE547591T1/en active
-
2010
- 2010-08-26 US US12/868,946 patent/US8622708B2/en not_active Expired - Fee Related
- 2010-08-27 CN CN201010268815XA patent/CN102003219B/en not_active Expired - Fee Related
- 2010-08-27 JP JP2010190834A patent/JP5073027B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
JP2011047406A (en) | 2011-03-10 |
JP5073027B2 (en) | 2012-11-14 |
EP2295724A1 (en) | 2011-03-16 |
US20110052397A1 (en) | 2011-03-03 |
CN102003219A (en) | 2011-04-06 |
ATE547591T1 (en) | 2012-03-15 |
US8622708B2 (en) | 2014-01-07 |
CN102003219B (en) | 2013-12-18 |
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