EP1215367B1 - Locking device for turbomachine blades - Google Patents
Locking device for turbomachine blades Download PDFInfo
- Publication number
- EP1215367B1 EP1215367B1 EP01128574A EP01128574A EP1215367B1 EP 1215367 B1 EP1215367 B1 EP 1215367B1 EP 01128574 A EP01128574 A EP 01128574A EP 01128574 A EP01128574 A EP 01128574A EP 1215367 B1 EP1215367 B1 EP 1215367B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- fixing device
- wedge element
- rotor
- positive
- 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.)
- Expired - Lifetime
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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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/37—Impeller making apparatus
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
Definitions
- the invention relates to a fixing device for a blading of a turbomachine, in which along a fastening groove introduced a number of blades and between at least two adjacent within the mounting groove inserted blades an intermediate mounting gap is provided with two formed as a closing half insert elements, which can be inserted into the intermediate mounting gap are each and have a width adapted to the width of the intermediate mounting gap width and include a gap between them, in which a wedge member is inserted, which is wedged such that both end halves are fixed by the wedge member frictionally within the mounting groove.
- Blades of the above type relate to guide but especially blades within turbomachinery, such as the compressor or turbine stage of a gas turbine plant.
- the following embodiments are preferably related to blades mounted along a mounting groove provided inside the rotor of a turbomachine and circulating along its circumference and suitably positioned depending on the flow conditions and possible maladjustments during operation the turbo machinery but especially against complete detachment from the mounting groove are reliable to secure.
- the measures to be taken with respect to the blades, as described below, may as well also apply to the integrated in the stationary housing components of turbomachines guide vanes application.
- Known security measures against an independent release of individual blades from the mounting groove generally refer to the reduction of the game between two adjacent blade roots within the mounting groove in the circumferential direction.
- FIGS. 2a-2c A rotor closure known per se, for example, from DE 812337 will be described below with reference to FIGS. 2a-2c.
- Figure 2a shows a cross section through a mounting groove 1, which is incorporated within a rotor 2.
- Rotor End 4 is radially between the two blades 31, 32 in the fastening groove 1 inserted.
- the rotor end 4 consists of two so-called end halves 41, 42 and a wedge element 43.
- both closing halves 41, 42 enclose an intermediate gap 5 into which the wedge element 43 can be inserted radially.
- the end halves 41, 42 have a corresponding recess 6 (see FIG. 2b), each resembling half a heart shape, are permanently spread in the retaining tabs 44 of the wedge element 43 as shown in Figure 2a to both closing halves 41, 42nd to press permanently against the inner contour of the mounting groove 1.
- a fixing device according to the preamble of claim 1, see, for example, a generic fixing device with reference to Figures 2a - 2c, formed such that the wedge element at least one connecting element to the side of a blade and at least one of the two adjacent to the wedge element blades to the connecting element corresponding counter contour provides, so that the wedge element and the blade enter into an intimate positive connection with each other.
- the idea underlying the invention is the creation of an intimate form-fitting connection between the wedge element and at least one immediately adjacent blade, so that no relative displacements between the blade and the wedge element and associated therewith the entire rotor end can occur, whereby the danger potential described above with respect to the detachment of the wedge element can be decisively limited.
- the wedge element is connected to both immediately adjacent blades via respective positive connection elements.
- Figure 1a shows a plan view of a composite consisting of two within a mounting groove (not shown) inserted blades 31, 32 and located between the blades 31, 32 rotor-end 4.
- the rotor-end 4 has a wedge member 43 which on its the blades 31, 32 facing sides each having a trained as a dovetail connection element 45 which engages in each case in a, within the blades 31, 32 incorporated counter contour 46 positively and non-positively.
- the mating contours 46 within the rotor blades 31, 32 are clearly visible.
- the inventively embodied rotor-end 4 first the end halves 41, 42 are inserted into the intermediate gap between the blades 31, 32 radially in the mounting groove.
- the wedge element 43 embodied according to the invention is also radially introduced radially into the intermediate gap between the two end halves 41, 42 as well as within the opposing counter contours 46 of the rotor blades 31, 32.
- the two adjacent blades 31, 32 through the Wedge element 43 mechanically connected to each other. If the wedge element 43 is completely sunk between the end halves 41, 42, the retaining tabs 44 of the wedge element 43 are pressed into the heart-shaped recesses 6 with the aid of a suitable tool.
- connection profiles are also conceivable in principle, such as, for example, hammer profiles of all kinds, as well as Christmas tree profiles.
- the mating contour 46 is incorporated within the blade root of the individual blades 31, 32. Not necessarily, the mating contour 46 extends over the entire depth of the blade root.
- FIG. 1c shows a side view of the rotor end 4 designed according to the invention.
- the wedge element 43 has the connecting element 45 designed according to the invention as a dovetail, which, according to the embodiment in FIG. 1 c, extends over the entire length of the blade root.
- the wedge member 43 has two retaining tabs 44 which engage in the corresponding recess 6 within the blades 41, 42.
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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 Erfindung bezieht sich auf eine Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine, bei der längs einer Befestigungsnut eine Anzahl von Schaufeln eingebracht und zwischen wenigstens zwei innerhalb der Befestigungsnut benachbart eingebrachter Schaufeln ein Montagezwischenspalt vorgesehen ist, mit zwei als Schlusshälften ausgebildeten Einsatzelementen, die in den Montagezwischenspalt einsetzbar sind und jeweils eine an die Breite des Montagezwischenspaltes angepaßte Breite aufweisen sowie zwischen sich einen Spaltraum einschließen, in den ein Keilelement einsetzbar ist, das derart verkeilbar ist, dass beide Schlusshälften kraftschlüssig durch das Keilelement innerhalb der Befestigungsnut fixiert sind.The invention relates to a fixing device for a blading of a turbomachine, in which along a fastening groove introduced a number of blades and between at least two adjacent within the mounting groove inserted blades an intermediate mounting gap is provided with two formed as a closing half insert elements, which can be inserted into the intermediate mounting gap are each and have a width adapted to the width of the intermediate mounting gap width and include a gap between them, in which a wedge member is inserted, which is wedged such that both end halves are fixed by the wedge member frictionally within the mounting groove.
Beschaufelungen der vorstehenden Art betreffen Leit- aber insbesondere Laufschaufeln innerhalb von Strömungsmaschine, wie beispielsweise die Verdichteroder Turbinenstufe einer Gasturbinenanlage. Die nachstehenden Ausführungen beziehen sich vorzugsweise auf Laufschaufeln, die längs einer Befestigungsnut, die innerhalb des Rotors einer Turbomaschine vorgesehen ist und diesen entlang seines Umfanges umläuft, befestigt sind und in Abhängigkeit der jeweiligen Strömungsverhältnisse in geeigneter Weise zu positionieren und gegenüber möglicherweise auftretenden Dejustierungen während des Betriebes der Turbomaschinen aber insbesondere gegen vollständiges Herauslösen aus der Befestigungsnut zuverlässig zu sichern sind. Die in Bezug auf die Laufschaufeln zu treffenden Maßnahmen, wie sie im folgenden beschrieben werden, können ebenso auch auf die in den feststehenden Gehäusebauteilen von Strömungsmaschinen integrierten Leitschaufeln Anwendung finden.Blades of the above type relate to guide but especially blades within turbomachinery, such as the compressor or turbine stage of a gas turbine plant. The following embodiments are preferably related to blades mounted along a mounting groove provided inside the rotor of a turbomachine and circulating along its circumference and suitably positioned depending on the flow conditions and possible maladjustments during operation the turbo machinery but especially against complete detachment from the mounting groove are reliable to secure. The measures to be taken with respect to the blades, as described below, may as well also apply to the integrated in the stationary housing components of turbomachines guide vanes application.
Die Gefahr des vollständigen Herauslösens einzelner Laufschaufeln aus den jeweiligen Befestigungsvorkehrungen ist gegeben, wenn sich die innerhalb der Befestigungsnuten eingesetzten und in an sich bekannter Weise befestigten Laufschaufeln innerhalb des jeweiligen Montagespiels in Umfangsrichtung längs der Befestigungsnut auf dem Rotor ungleichmäßig verschieben können. Durch derartige periphere Dejustierungen bei einer Vielzahl längs der Befestigungsnut eingesetzten Laufschaufeln kann sich ein zwischen zwei benachbarten Laufschaufeln beachtlicher Spalt einstellen, der groß genug ist, dass sich eine Laufschaufel durch radiale Verdrehung aus der Befestigungsnut lösen kann, wodurch sich ein erheblicher Schaden an der gesamten Turbomaschinenanlage ergibt.The risk of complete detachment of individual blades from the respective Befestigungsvorkehrungen is given if the inserted within the mounting grooves and fixed in a conventional manner blades within the respective mounting game in the circumferential direction along the mounting groove on the rotor can move unevenly. By such peripheral misadjustments with a plurality of blades inserted along the mounting groove, a gap considerable enough between two adjacent blades can be set which is large enough for a blade to dislodge from the mounting groove by radial rotation, thereby causing considerable damage to the entire turbomachinery results.
An sich bekannte Sicherungsmaßnahmen gegen ein sich selbständiges Lösen einzelner Laufschaufeln aus der Befestigungsnut beziehen sich im allgemeinen auf die Reduzierung des Spiels zwischen zwei benachbarten Schaufelfüßen innerhalb der Befestigungsnut in Umfangsrichtung. Nach der Montage aller in die Befestigungsnut eingesetzten Laufschaufeln sowie ganzen und halbierten Zwischenstücke ergibt sich bspw. zwischen zwei benachbart sich innerhalb der Befestigungsnut gegenüberstehenden Laufschaufeln eine Lücke, der sogenannte Montagezwischenspalt, in die zum Schließen der Lücke ein sogenannter Rotor-Schluss eingesetzt wird, der dafür sorgt, dass das zwischen den, in die Befestigungsnut eingesetzten Laufschaufeln sowie Zwischenstücken vorhandene Spiel auf einen Minimum begrenzt wird.Known security measures against an independent release of individual blades from the mounting groove generally refer to the reduction of the game between two adjacent blade roots within the mounting groove in the circumferential direction. After mounting all the blades used in the mounting groove and complete and halved intermediate pieces results, for example, between two adjacent within the mounting groove opposing blades a gap, the so-called mounting gap, in the closing of the gap, a so-called rotor-end is used for this purpose ensures that existing between the, used in the mounting groove blades and spacers existing game is limited to a minimum.
Ein an sich beispielsweise aus DE 812337 bekannter Rotor-Schluss wird nachstehend unter Bezugnahme auf die Figuren 2a - 2c beschrieben. Figur 2a zeigt einen Querschnitt durch eine Befestigungsnut 1, die innerhalb eines Rotors 2 eingearbeitet ist. Zur gegenseitigen Befestigung zweier innerhalb der Befestigungsnut 1 unmittelbar benachbart angeordneter Laufschaufeln 31, 32, siehe hierzu eine Draufsicht-Abbildung gemäß Figur 2c, ist der sog. Rotor-Schluss 4 radial zwischen den beiden Schaufeln 31, 32 in der Befestigungsnut 1 eingefügt. Der Rotor-Schluss 4 besteht, wie aus Figur 2b im Einzelnen hervorgeht, aus zwei sog. Schlusshälften 41, 42 sowie einem Keilelement 43. Die jeweils der Befestigungsnut 1 zugewandten Seiten der Schlusshälften 41, 42 sind für einen kraft- und formschlüssigen Eingriff mit der Innenkontur der Befestigungsnut 1 entsprechend ausgebildet. Im eingefügten Zustand innerhalb der Befestigungsnut 1 schließen beide Schlusshälften 41, 42 einen Zwischenspalt 5 ein, in den das Keilelement 43 radialwärts einsetzbar ist. Im oberen Bereich weisen die Schlusshälften 41, 42 eine entsprechende Ausnehmung 6 auf (siehe Fig. 2b), die jeweils einer halben Herzform ähnelt, in die Haltelappen 44 des Keilelementes 43 gemäß Darstellung in Figur 2a dauerhaft gespreizt werden, um beide Schlusshälften 41, 42 gegen die Innenkontur der Befestigungsnut 1 dauerhaft zu pressen.A rotor closure known per se, for example, from DE 812337 will be described below with reference to FIGS. 2a-2c. Figure 2a shows a cross section through a
Jedoch entstehen aufgrund der unterschiedlichen thermischen Ausdehnungsverhalten zwischen den Schaufeln, dem Rotor-Schluss sowie dem Rotor während des Betriebes ein Spiel zwischen den Schaufeln und den innerhalb der Befestigungsnut befindlichen Zwischenstücken einschließlich des Rotor-Schlusses. Aufgrund des sich dabei einstellenden Umfangsspieles kann es vorkommen, dass sich die Schlusshälften derart in Umfangsrichtung längs der Befestigungsnut gegeneinander verschieben, dass sich das gespreizte Keilelement aus den herzförmig ausgeformten Ausnehmungen lösen kann. Ein derartiger Fall führt wiederum zu dem eingangs bereits beschriebenen Schadensszenario.However, due to the different thermal expansion behavior between the blades, the rotor-end and the rotor during operation, a clearance between the blades and located within the mounting groove spacers including the rotor-end. Due to the thereby adjusting circumferential clearance, it may happen that the end halves so move in the circumferential direction along the mounting groove against each other, that the splayed wedge element can release from the heart-shaped recesses formed. Such a case in turn leads to the damage scenario already described above.
Es besteht daher die Aufgabe, eine gattungsgemäße Fixiervorrichtung, wie sie bspw. aus den Figuren 2a - 2c hervorgeht, derart weiterzubilden, dass das vorstehend beschriebene Schadensszenario ausgeschlossen werden kann. Die betreffenden Maßnahmen sollen konstruktiv möglichst einfach und in der Realisierung kostengünstig sein.It is therefore the object of developing a generic fixing device, such as, for example, from FIGS. 2a-2c, in such a way that the damage scenario described above can be ruled out. The measures in question should be structurally as simple as possible and inexpensive to implement.
Die Lösung der der Erfindung zugrundeliegenden Aufgabe ist im Anspruch 1 angegeben. Den Erfindungsgedanken vorteilhaft weiterbildenden Merkmale sind Gegenstand der Unteransprüche und insbesondere der Beschreibung unter Bezugnahme auf die Figuren zu entnehmen.The solution of the problem underlying the invention is specified in
Erfindungsgemäß ist eine Fixiervorrichtung gemäß des Oberbegriffes des Anspruches 1, siehe bspw. eine gattungsgemäße Fixiervorrichtung unter Bezugnahme auf die Figuren 2a - 2c, derart ausgebildet, dass das Keilelement zumindest ein Verbindungselement zur Seite einer Schaufel und zumindest eine der beiden an das Keilelement angrenzenden Schaufeln eine zu dem Verbindungselement korrespondierende Gegenkontur vorsieht, so dass das Keilelement und die Schaufel eine innige Formschlussverbindung miteinander eingehen.According to the invention, a fixing device according to the preamble of
Die der Erfindung zugrundeliegende Idee ist die Schaffung einer innigen Formschlussverbindung zwischen dem Keilelement und wenigstens einer unmittelbar angrenzenden Laufschaufel, so dass keine Relativverschiebungen zwischen der Laufschaufel und dem Keilelement und damit verbunden dem gesamten Rotor-Schluss auftreten können, wodurch das eingangs beschriebene Gefahrenpotential bezüglich des Herauslösens des Keilelementes entscheidend eingeschränkt werden kann.The idea underlying the invention is the creation of an intimate form-fitting connection between the wedge element and at least one immediately adjacent blade, so that no relative displacements between the blade and the wedge element and associated therewith the entire rotor end can occur, whereby the danger potential described above with respect to the detachment of the wedge element can be decisively limited.
In besonders vorteilhafter Weise ist das Keilelement mit beiden unmittelbar benachbarten Schaufeln über jeweilige formschlüssige Verbindungselemente verbunden. Eine derartig erfindungsgemäße Ausbildung einer Fixiervorrichtung ist nachstehend unter Bezugnahme auf die Figuren näher erläutert.In a particularly advantageous manner, the wedge element is connected to both immediately adjacent blades via respective positive connection elements. An inventive design of a fixing device is explained below with reference to the figures.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnungen exemplarisch beschrieben. Es zeigen:
- Fig. 1a
- Draufsicht eines erfindungsgemäß ausgebildeten Rotor-Schlusses in Verbindung mit zwei benachbarten Schaufeln,
- Fig. 1b
- Einzelkomponentendarstellung in Draufsicht der gemäß in Figur 1a dargestellten Komponenten,
- Fig. 1c
- Seitenansicht des erfindungsgemäß ausgebildeten Rotor-Schlusses,
- Fig. 2a - c
- Darstellungen eines an sich bekannten Rotor-Schlusses (Stand der Technik).
- Fig. 1a
- Top view of a rotor end according to the invention in conjunction with two adjacent blades,
- Fig. 1b
- Single component representation in plan view of the components shown in FIG. 1a,
- Fig. 1c
- Side view of the inventively designed rotor-end,
- Fig. 2a - c
- Representations of a known rotor-end (prior art).
Figur 1a zeigt eine Draufsicht auf einen Verbund bestehend aus zwei innerhalb einer Befestigungsnut (nicht dargestellt) eingefügter Laufschaufeln 31, 32 und einem zwischen den Laufschaufeln 31, 32 befindlichen Rotor-Schluss 4. Der Rotor-Schluss 4 weist ein Keilelement 43 auf, das an seinen den Laufschaufeln 31, 32 zugewandten Seiten jeweils ein als Schwalbenschwanz ausgebildetes Verbindungselement 45 aufweist, das in jeweils in eine, innerhalb der Laufschaufeln 31, 32 eingearbeitete Gegenkontur 46 form- und kraftschlüssig eingreift.Figure 1a shows a plan view of a composite consisting of two within a mounting groove (not shown) inserted
Durch die erfindungsgemäß zwischen dem Rotor-Schluss 4 und beiden Laufschaufeln 31, 32 eingefügte mechanische Verbindung können Relativbewegungen bedingt durch unterschiedliche thermische Ausdehnungserscheinungen ausgeschlossen werden, so dass sich kein unzulässiger Zwischenspalt längs der Befestigungsnut ausbilden kann, durch den sich die Gefahr eines Herauslösens von innerhalb der Befestigungsnut befindlichen Teilen ergeben würde.By virtue of the mechanical connection inserted between the
In der Einzelkomponentendarstellung gemäß Figur 1b sind die Gegenkonturen 46 innerhalb der Laufschaufeln 31, 32 klar ersichtlich. Zur Montage des erfindungsgemäß ausgebildeten Rotor-Schlusses 4, werden zunächst die Schlusshälften 41, 42 in den Zwischenspalt zwischen den Laufschaufeln 31, 32 radialwärts in die Befestigungsnut eingefügt. Anschließend wird das erfindungsgemäß ausgebildete Keilelement 43 ebenfalls radialwärts sowohl in den Zwischenspalt zwischen beiden Schlusshälften 41, 42 als auch innerhalb der sich gegenüberliegenden Gegenkonturen 46 der Laufschaufeln 31, 32 radial eingeführt. Hierdurch werden die beiden benachbart liegenden Laufschaufeln 31, 32 durch das Keilelement 43 mechanisch miteinander verbunden. Ist das Keilelement 43 vollständig zwischen den Schlusshälften 41, 42 versenkt, so werden die Haltelappen 44 des Keilelementes 43 in die herzförmig ausgebildeten Ausnehmungen 6 mit Hilfe eines geeigneten Werkzeuges verpresst.In the single-component representation according to FIG. 1b, the
Neben der Ausbildung des Verbindungselementes 45 als Schwalbenschwanz sind grundsätzlich auch alternative Verbindungsprofile denkbar, wie beispielsweise Hammerprofile aller Art sowie auch Tannenbaumprofile. Vorzugsweise ist die Gegenkontur 46 innerhalb des Schaufelfußes der einzelnen Laufschaufeln 31, 32 eingebracht. Nicht notwendigerweise erstreckt sich die Gegenkontur 46 über die gesamte Tiefe des Schaufelfußes.In addition to the formation of the connecting
In Figur 1c ist eine Seitenansicht auf den erfindungsgemäß ausgebildeten Rotor-Schluss 4 dargestellt. Im Unterschied zur Darstellung gemäß Figur 2b weist das Keilelement 43 das erfindungsgemäß als Schwalbenschwanz ausgebildete Verbindungselement 45 auf, das sich gemäß der Ausführungsform in Figur 1c über die gesamte Länge des Schaufelfusses erstreckt. Ebenso wie im Fall der Figur 2b weist das Keilelement 43 zwei Haltelappen 44 auf, die in die entsprechende Ausnehmung 6 innerhalb der Laufschaufeln 41, 42 eingreifen.FIG. 1c shows a side view of the
Ebenso ist es denkbar, dass weitere Verbindungselemente zwischen den einzelnen Schlusshälften 41, 42 und den diesen unmittelbar angrenzenden Laufschaufeln 31, 32 vorgesehen sind. Auf diese Weise kann eine weiter verbesserte mechanisch innige Verbindung zwischen den erfindungsgemäß ausgebildeten Rotor-Schluss und den benachbarten Laufschaufeln erreicht werden.
Erfindungsgemässe Verbindungselemente können auch an anderer Stelle in der selben Schaufelreihe eingebaut werden.Likewise, it is conceivable that further connecting elements between the individual end halves 41, 42 and the
Connecting elements according to the invention can also be installed elsewhere in the same blade row.
- 11
- Befestigungsnutmounting groove
- 22
- Rotorrotor
- 31,3231.32
- Schaufelnshovel
- 44
- Rotor-SchlussRotor end
- 41, 4241, 42
- Schlusshälftenfinal halves
- 4343
- Keilelementkey member
- 4444
- Haltelappenretaining tabs
- 4545
- Verbindungselementconnecting element
- 4646
- Gegenkonturmating contour
- 55
- Zwischenspaltintermediate gap
- 66
- Ausnehmungenrecesses
Claims (9)
- Fixing device for a blading system of a turbomachine in which a plurality of blades (31,32) is fastened along a fastening slot (1) and an installation intermediate gap is provided between at least two blades (31,32) adjacently installed inside the fastening slot (1), with two insert elements constructed as lock halves (41,42) which are insertable in the installation intermediate gap and each have a width conforming to the width of the installation intermediate gap and between each other enclose a space (5) into which is insertable a wedge element (43) which is wedgable in such a way that both lock halves (41,42) are fixed by the wedge element (43) inside the fastening slot (1) in a positive-locking manner,
characterized in that the wedge element (43) provides at least one connecting element (45) on the side of one blade (31,32) and at least one of the two blades (31,32) adjacent to the wedge element (43) provides a mating contour (46) corresponding to the connecting element (45) so that the wedge element (43) and the blades (31,32) make a positive-locking connection with one another. - Fixing device according to Claim 1,
characterized in that the connecting element (45) and the corresponding mating contour (46) are formed as a dovetail connection. - Fixing device according to Claim 1 or 2,
characterized in that the wedge element (43) provides connecting elements (45) on both sides for both adjacent blades (31,32) for the creation in each case of a positive-locking connection. - Fixing device according to one of Claims 1 to 3,
characterized in that the wedge element (43) is insertable radially between both blades (31,32) and both lock halves (41,42) and provides retaining tabs (44) which are durably spreadable apart in recesses (6) provided correspondingly in the lock halves (41,42). - Fixing device according to one of Claims 1 to 4,
characterized in that the at least one connecting element (45) as well as the corresponding mating contour (46) is constructed as a T-profile or in fir-tree form. - Fixing device according to one of Claims 1 to 5,
characterized in that the blades (31,32) are rotor blades inside a rotor assembly or stator blades inside a stator assembly. - Fixing device according to one of Claims 1 to 6,
characterized in that the turbomachine is a compressor unit or a turbine stage inside a gas turbine installation. - Fixing device according to one of Claims 1 to 7,
characterized in that the blades (31,32) are arranged in a blade row and at least one positive-locking connection is provided in the blade row between the wedge element (43) and a blade (31,32). - Fixing device according to one of Claims 1 to 8,
characterized in that the blades (31,32) of a blade row are fastened in a fastening slot (1).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10062908 | 2000-12-16 | ||
| DE10062908 | 2000-12-16 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1215367A2 EP1215367A2 (en) | 2002-06-19 |
| EP1215367A3 EP1215367A3 (en) | 2004-01-21 |
| EP1215367B1 true EP1215367B1 (en) | 2006-12-27 |
Family
ID=7667528
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01128574A Expired - Lifetime EP1215367B1 (en) | 2000-12-16 | 2001-11-30 | Locking device for turbomachine blades |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6647602B2 (en) |
| EP (1) | EP1215367B1 (en) |
| DE (2) | DE10134611A1 (en) |
Families Citing this family (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10310432A1 (en) * | 2003-03-11 | 2004-09-23 | Alstom Technology Ltd | Rotor end |
| DE10346239A1 (en) | 2003-10-06 | 2005-04-21 | Alstom Technology Ltd Baden | Method for fixing the blading of a turbomachine and fixing device |
| EP1698758B1 (en) | 2005-02-23 | 2015-11-11 | Alstom Technology Ltd | Axially split rotor end piece |
| EP1698759B1 (en) | 2005-02-23 | 2015-06-03 | Alstom Technology Ltd | Rotor end piece |
| US7435055B2 (en) * | 2005-03-29 | 2008-10-14 | Siemens Power Generation, Inc. | Locking spacer assembly for a turbine engine |
| EP1803899A1 (en) * | 2006-01-02 | 2007-07-04 | Siemens Aktiengesellschaft | Blade locking assembly for a turbomachine |
| EP1803900A1 (en) | 2006-01-02 | 2007-07-04 | Siemens Aktiengesellschaft | Closure unit for the remaining space between the first and the last blades of a bladed ring inserted in a circumferencial slot of a turbomachine, and corresponding turbomachine |
| US8523529B2 (en) * | 2009-11-11 | 2013-09-03 | General Electric Company | Locking spacer assembly for a circumferential entry airfoil attachment system |
| US20110255978A1 (en) * | 2010-04-16 | 2011-10-20 | Brian Denver Potter | Locking Assembly For Circumferential Attachments |
| US9175572B2 (en) * | 2012-04-16 | 2015-11-03 | General Electric Company | Turbomachine blade mounting system |
| US9341071B2 (en) * | 2013-10-16 | 2016-05-17 | General Electric Company | Locking spacer assembly |
| WO2016195657A1 (en) * | 2015-06-02 | 2016-12-08 | Siemens Aktiengesellschaft | Locking spacer assembly between compressor blade structures in a turbine engine |
| EP3115554A1 (en) * | 2015-07-09 | 2017-01-11 | Siemens Aktiengesellschaft | Rotor blade assembly with elastic support members for a thermal turbomachine |
| US10465699B2 (en) | 2017-01-26 | 2019-11-05 | DOOSAN Heavy Industries Construction Co., LTD | Compressor blade locking mechanism in disk with tangential groove |
| US10519970B2 (en) | 2017-02-09 | 2019-12-31 | DOOSAN Heavy Industries Construction Co., LTD | Compressor blade locking mechanism in disk with tangential groove |
| EP3752716B1 (en) | 2018-03-28 | 2021-10-13 | Siemens Energy Global GmbH & Co. KG | Locking spacer assembly, corresponding blade assembly and method for installing a locking spacer |
| EP3765715B1 (en) | 2018-04-18 | 2021-12-29 | Siemens Energy Global GmbH & Co. KG | Locking spacer assembly, blade assembly and method for installing a locking spacer |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR974989A (en) * | 1948-09-17 | 1951-02-28 | Lock for blading drum-shaped rotors of axial compressors and steam or gas turbines | |
| US3721506A (en) * | 1971-05-25 | 1973-03-20 | Gen Electric | Split-nut blade locking assembly |
| DE19654471B4 (en) * | 1996-12-27 | 2006-05-24 | Alstom | Rotor of a turbomachine |
| DE19728345A1 (en) * | 1997-07-03 | 1999-01-07 | Asea Brown Boveri | Non-positive and positive connection of rotating components |
| EP1124038A1 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blading |
| US6439841B1 (en) * | 2000-04-29 | 2002-08-27 | General Electric Company | Turbine frame assembly |
| US6517313B2 (en) * | 2001-06-25 | 2003-02-11 | Pratt & Whitney Canada Corp. | Segmented turbine vane support structure |
| US6582195B2 (en) * | 2001-06-27 | 2003-06-24 | General Electric Company | Compressor rotor blade spacer apparatus |
-
2001
- 2001-07-17 DE DE10134611A patent/DE10134611A1/en not_active Withdrawn
- 2001-11-30 EP EP01128574A patent/EP1215367B1/en not_active Expired - Lifetime
- 2001-11-30 DE DE50111726T patent/DE50111726D1/en not_active Expired - Lifetime
- 2001-11-30 US US09/996,683 patent/US6647602B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| EP1215367A2 (en) | 2002-06-19 |
| EP1215367A3 (en) | 2004-01-21 |
| US20020127105A1 (en) | 2002-09-12 |
| DE50111726D1 (en) | 2007-02-08 |
| US6647602B2 (en) | 2003-11-18 |
| DE10134611A1 (en) | 2002-06-27 |
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