EP1698759B1 - Rotor end piece - Google Patents
Rotor end piece Download PDFInfo
- Publication number
- EP1698759B1 EP1698759B1 EP06110072.3A EP06110072A EP1698759B1 EP 1698759 B1 EP1698759 B1 EP 1698759B1 EP 06110072 A EP06110072 A EP 06110072A EP 1698759 B1 EP1698759 B1 EP 1698759B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- end piece
- halves
- blade
- tabs
- 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
- F01D5/32—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
- 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
Definitions
- the invention relates to the field of thermal turbomachinery, in particular it relates to a rotor end for rotors according to the preamble of claim 1. Furthermore, an assembly method for a rotor according to the invention is given.
- Thermal turbomachinery with axial turbines and axial compressors have a rotor equipped with blades and a stator, are mounted in the guide vanes for flow guidance.
- the stationary guide vanes have the task of directing the flow of the gas medium to be compressed or to be relaxed in such a way onto the rotating running blading of the respective compressor stage or the respective turbine stage that the energy conversion takes place with the best possible efficiency.
- Both blades and vanes essentially comprise a profiled airfoil and a blade root.
- grooved in the stator and on the rotor shaft are the Feet of the blades inserted and locked there.
- compressor blade rows of gas turbine rotors are arranged in circumferential grooves, which often have a T-shaped cross-section.
- blades and spacers alternate here.
- a special solution must be found for the last blades to be mounted, since then the remaining filling opening for a complete intermediate piece is too small. This residual opening is therefore filled with a so-called rotor-end.
- the known rotor closure consists of a halved intermediate piece, that is to say of two halves divided in the circumferential direction with respect to the rotor, and a wedge with the aid of which the end halves are caulked axially in the rotor.
- the two end halves in the known prior art according to the DE 812 337 each have a straight side surface formed.
- the side surfaces mentioned are opposite in the installed state, in which case the wedge is located between them.
- the invention is based on the technical problem of providing a rotor end which is as simple and inexpensive as possible during assembly and production.
- a rotor end for a rotor of a thermal turbomachine with at least one circumferential groove are provided in the blades, in particular with a hammer base, and intermediate pieces, wherein between an end blade and an end piece a residual gap is formed, in which two end halves are arranged each integrally with these associated locking tabs, which are in engagement with the end blade or with the tail, and the end halves below the lobes relief slots, wherein the tabs are arranged on the parting plane of the end halves.
- no wedge is present, i. no forces are applied to the rotor in the axial direction. This is possible due to the design-related low residual gap.
- the proposed rotor-end is safe and does not cause rotor vibrations.
- the relief slots contribute to the easy manual flexibility of the lobes and thus to the easy installation of the rotor closure. In addition, this prevents that the closing halves twist when bending the cloth.
- An advantageous development of the invention provides that the end blade and the end piece in the foot region on the side facing the remaining gap each having a recess into which the lobes of the end halves are inserted. Through the recess, the end blade and the end piece differ from the other runners and intermediate pieces.
- the recess may for example be designed in the shape of a cylinder segment and removed by means of a grinding tool.
- end halves have a material thickness of 3 mm to 5 mm. Hierduch manually bending the cloth is possible with a simple assembly tool.
- the end halves are made of a chromium-molybdenum-vanadium alloy. This ensures the desired strength of the rotor end.
- a method for mounting a rotor closure in a circumferential groove, which has two end halves has the following steps: inserting the two end halves in the remaining gap, together with supports, so that the end halves are offset from one another; Inserting a tool in the parting plane between the two end halves; Bending the flaps into the recesses of the end blade and the tail; Remove the supports.
- An advantageous development of the method according to the invention for mounting a rotor closure further comprises the following steps: Turning the tool through 90 °, so that the tabs protrude far enough into the recess.
- FIG. 1 shows a section in the rotor longitudinal direction through a rotor-1 according to the invention after installation in a compressor rotor 6.
- FIG. 2 shows a partial section along the line II - II FIG. 1 ,
- the remaining gap 15 present between an end blade 2 and an end piece 11 is filled by two end halves 4, 4.
- the flat end halves 4, 4 essentially have a cross-section which corresponds to a so-called hammer foot or two-pointed foot, with a rectangular area being excluded above the parting plane 5.
- bendable tabs 8, 8 are arranged. Below the tabs 8, 8, the closing halves 4, 4 have relief slots 10, 10.
- the end blade 2 and the end piece 11 have in the foot region on the side facing the remaining gap 15 each have a recess 9, 12, in which the tabs 8, 8 of the end halves 4, 4 are introduced by bending. Through the recessed into the recesses 9, 12 tabs 8, 8 of the rotor 1 is locked and secured against falling out.
- FIG. 3 shows an enlarged detail view of the two end halves 4, 4.
- the end halves 4, 4 with their parting plane 5 across the dividing plane 5 above a rectangular surface is cut out, the access to the two arranged on the upper edge of the parting plane 5 with a flap Tool allows.
- Below the tabs 8, 8 horizontal relief slots 10 are provided, each beginning in the parting plane 5 and terminate in a bore.
- the outer contour of the end halves 4, 4 is designed so that they can be inserted into a T-shaped circumferential groove 3 of a rotor 6 and find support therein.
- FIG. 4 which shows a plan view of the end halves 4, 4 FIG. 3 shows, the end halves only a small thickness of 3 mm to 5 mm. This makes it possible that the tabs 8,8 can still be bent manually.
- FIG. 5 shows a partial section similar to that Fig. 2 corresponds, but with introduced during assembly supports.
- a residual gap 15 remains.
- This residual gap 15 can only be taken from two divided in the circumferential direction of the groove 3 end halves 4, 4 existing rotor end 1 with supports 14, 14.
- the supports 14, 14 serve only as an assembly aid of the two 3mm to 5mm thick end halves 4, 4, which are made of a chromium-molybdenum-vanadium alloy.
- the supports 14, 14 are just as thick as the end halves 4, 4 or slightly thinner.
- a corresponding mounting tool 13 such as a screwdriver or a flat chisel, which is about 10 mm - 15 mm inserted into the parting plane 5 between the two end halves 4,4, the two tabs 8, 8 are bent out of the final plane.
- the tool 13 is preferably rotated by 90 ° so that the tabs 8, 8 protrude far enough into the recess on the blade root 9 or into the recess on the tail base 12.
- the respective recesses 9, 12 are incorporated as a cylinder-segment-like depressions in the end blade foot 7 and the End Culturefuss, whereby the components differ from the other blades and spacers. Subsequently, the only required for the installation supports 14, 14 are removed and the minimum gap evenly distributed over the circumference.
- the final configuration reached is in Figures 1 and 2 shown and described.
- the disassembly is carried out by drilling away or grinding away the lobes 8, 8 and removal of the end halves 4,4.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die Erfindung betrifft das Gebiet der thermischen Turbomaschinen, insbesondere betrifft sie einen Rotor-Schluss für Rotoren gemäss dem Oberbegriff des Patentanspruches 1. Ferner wird ein Montageverfahren für einen erfindungsgemässen Rotor-Schluss angegeben.The invention relates to the field of thermal turbomachinery, in particular it relates to a rotor end for rotors according to the preamble of
Thermische Turbomaschinen mit Axialturbinen und Axialverdichtern, weisen einen mit Laufschaufeln bestückten Rotor und einen Stator auf, in den Leitschaufeln zur Strömungsführung eingehängt sind.Thermal turbomachinery with axial turbines and axial compressors, have a rotor equipped with blades and a stator, are mounted in the guide vanes for flow guidance.
Die stationären Leitschaufeln haben die Aufgabe, den Strom des zu verdichtenden bzw. des zu entspannenden gasförmigen Mediums so auf die rotierende Laufbeschaufelung der jeweiligen Verdichterstufe bzw. der jeweiligen Turbinenstufe zu lenken, dass die Energieumwandlung mit bestmöglichem Wirkungsgrad erfolgt.The stationary guide vanes have the task of directing the flow of the gas medium to be compressed or to be relaxed in such a way onto the rotating running blading of the respective compressor stage or the respective turbine stage that the energy conversion takes place with the best possible efficiency.
Sowohl Laufschaufeln als auch Leitschaufeln weisen im wesentlichen ein profiliertes Schaufelblatt und einen Schaufelfuss auf. Um die Laufschaufeln auf dem Rotor bzw. die Leitschaufeln im Stator befestigen zu können, sind im Stator und auf der Rotorwelle Nuten eingestochen. In diese Nuten werden die Füsse der Schaufeln eingeschoben und dort arretiert.Both blades and vanes essentially comprise a profiled airfoil and a blade root. In order to secure the blades on the rotor or the stator vanes in the stator, grooved in the stator and on the rotor shaft. In these grooves are the Feet of the blades inserted and locked there.
Es ist bekannt, dass Verdichterschaufelreihen von Gasturbinenrotoren in Umfangsnuten angeordnet sind, die häufig einen T-förmigen Querschnitt aufweisen. In der Regel wechseln sich hier Schaufeln und Zwischenstücke ab. Bei der Montage solcher Schaufelreihen muss für die letzten zu montierenden Schaufeln eine spezielle Lösung gefunden werden, da dann die verbleibende Einfüllöffnung für ein vollständiges Zwischenstück zu klein ist. Diese Restöffnung wird daher mit einem sogenannten Rotor-Schluss aufgefüllt.It is known that compressor blade rows of gas turbine rotors are arranged in circumferential grooves, which often have a T-shaped cross-section. As a rule, blades and spacers alternate here. When assembling such rows of blades, a special solution must be found for the last blades to be mounted, since then the remaining filling opening for a complete intermediate piece is too small. This residual opening is therefore filled with a so-called rotor-end.
Aus der
Die beiden Schlusshälften weisen bei dem bekannten Stand der Technik gemäss der
Nachteilig an diesem Stand der Technik ist, dass bei hohen Rotordrehzahlen Festigkeitsprobleme auf Grund des Kippmomentes der beiden Schlusshälften auftreten können, welches durch die Fliehkraft während des Betriebes bewirkt wird.A disadvantage of this prior art that at high rotor speeds strength problems due to the tilting moment of the two end halves can occur, which is caused by the centrifugal force during operation.
Ein weiterer Nachteil dieser technischen Lösungen besteht darin, dass die Schlussstücke einerseits durch die Fliehkraft während des Betriebes und anderseits durch das Verstemmen des Keiles Axialkräfte auf den Rotor ausüben. Bei der Suche nach den Ursachen für die häufig auftretenden Rotorvibrationen hat man festgestellt, dass diese Axialkräfte den Rotor verbiegen und dadurch nachteilig störende Schwingungen erzeugen können.Another disadvantage of these technical solutions is that the closing pieces on the one hand by the centrifugal force during operation and on the other hand exert axial forces on the rotor by caulking the wedge. In the search for the causes of the frequently occurring rotor vibrations, it has been found that these axial forces can bend the rotor and thereby disadvantageously generate disturbing vibrations.
Zwar beschreiben die
Aus den Dokumenten
Aufgabe der vorliegenden Erfindung ist es daher, die vorgenannten Nachteile des Standes der Technik zu vermeiden. Der Erfindung liegt das technische Problem zu Grunde, einen Rotor-Schluss zur Verfügung zu stellen, welcher möglichst einfach und kostengünstig bei Montage und Herstellung ist.Object of the present invention is therefore to avoid the aforementioned disadvantages of the prior art. The invention is based on the technical problem of providing a rotor end which is as simple and inexpensive as possible during assembly and production.
Erfindungsgemäss wird diese Aufgabe durch einen Rotor-Schluss für Rotoren thermischer Turbomaschinen mit den Merkmalen des Patentanspruchs 1 gelöst. Ein erfindungsgemässes Montageverfahren wird in Anspruch 6 beschrieben. Vorteilhafte Ausführungsformen und Weiterbildungen der Erfindung sind in den Unteransprüchen beschrieben.According to the invention, this object is achieved by a rotor end for rotors of thermal turbomachines having the features of
Hierdurch werden die Nachteile des Standes der Technik vermieden und ein Rotor-Schluss zur Verfügung gestellt, welcher einfach und kostengünstig bei Montage und Herstellung ist.As a result, the disadvantages of the prior art are avoided and provided a rotor end, which is simple and inexpensive to install and manufacture.
Erfindungsgemäss ist ein Rotor-Schluss für einen Rotor einer thermischen Turbomaschine mit zumindest einer Umfangsnut, in der Laufschaufeln, insbesondere mit Hammerfuss, und Zwischenstücke vorgesehen sind, wobei zwischen einer Endschaufel und einem Endstück ein Restspalt gebildet ist, in dem zwei Schlusshälften angeordnet sind, die jeweils einstückig mit diesen verbundene Sicherungslappen aufweisen, welche mit der Endschaufel bzw. mit dem Endstück im Eingriff stehen, und die Schlusshälften unterhalb der Lappen Entlastungsschlitze aufweisen, wobei die Lappen an der Trennebene der Schlusshälften angeordnet sind. Bei der erfindungsgemässen Lösung ist kein Keil vorhanden, d.h. es werden keine Kräfte in axialer Richtung auf den Rotor aufgebracht. Dies ist aufgrund des bauartbedingten geringen Restspalts möglich. Durch die lediglich zwei Bauteile ist die Montage sehr einfach und kostengünstig. Dabei ist der vorgeschlagene Rotor-Schluss sicher und verursacht keine Rotorschwingungen. Die Entlastungsschlitze tragen zu der einfachen manuellen Biegbarkeit der Lappen und damit zur leichten Montage des Rotorschlusses bei. Außerdem wird hierdurch verhindert, dass sich die Schlusshälften beim Biegen der Lappen verwinden.According to the invention, a rotor end for a rotor of a thermal turbomachine with at least one circumferential groove are provided in the blades, in particular with a hammer base, and intermediate pieces, wherein between an end blade and an end piece a residual gap is formed, in which two end halves are arranged each integrally with these associated locking tabs, which are in engagement with the end blade or with the tail, and the end halves below the lobes relief slots, wherein the tabs are arranged on the parting plane of the end halves. In the solution according to the invention no wedge is present, i. no forces are applied to the rotor in the axial direction. This is possible due to the design-related low residual gap. Due to the only two components, the assembly is very simple and inexpensive. The proposed rotor-end is safe and does not cause rotor vibrations. The relief slots contribute to the easy manual flexibility of the lobes and thus to the easy installation of the rotor closure. In addition, this prevents that the closing halves twist when bending the cloth.
Dies erleichtert die Montage und Demontage der Schlusshälften.This facilitates the assembly and disassembly of the end halves.
Eine vorteilhafte Weiterbildung der Erfindung sieht vor, dass die Endschaufel und das Endstück im Fussbereich an der dem Restspalt zugewandten Seite jeweils eine Aussparung aufweisen, in die die Lappen der Schlusshälften einführbar sind. Durch die Aussparung unterscheiden sich die Endschaufel und das Endstück von den übrigen Laufschaufen und Zwischenstücken. Die Aussparung kann beispielsweise zylindersegmentförmig gestaltet sein und mittels Schleifwerkzeug abgetragen sein.An advantageous development of the invention provides that the end blade and the end piece in the foot region on the side facing the remaining gap each having a recess into which the lobes of the end halves are inserted. Through the recess, the end blade and the end piece differ from the other runners and intermediate pieces. The recess may for example be designed in the shape of a cylinder segment and removed by means of a grinding tool.
Noch eine vorteilhafte Weiterbildung der Erfindung sieht vor, dass die Schlusshälften eine Materialstärke von 3 mm bis 5 mm aufweisen. Hierduch ist das manuell Verbiegen der Lappen mit einfachem Montagewerkzeug möglich.Yet another advantageous development of the invention provides that the end halves have a material thickness of 3 mm to 5 mm. Hierduch manually bending the cloth is possible with a simple assembly tool.
Außerdem hat es sich als vorteilhaft erwiesen, dass die Schlusshälften aus einer Chrom-Molybdän-Vanadium Legierung hergestellt sind. Hierdurch wird die gewünschte Festigkeit des Rotor-Schlusses gewährleistet.In addition, it has proven to be advantageous that the end halves are made of a chromium-molybdenum-vanadium alloy. This ensures the desired strength of the rotor end.
Ein erfindungsgemässes Verfahren zur Montage eines Rotorschlusses in einer Umfangsnut, der zwei Schlusshälften aufweist, weist folgende Schritte auf: Einsetzen der beiden Schlusshälften in den Restspalt, zusammen mit Abstützungen, so dass die Schlusshälften gegeneinander versetzt sind; Einführen eines Werkzeugs in die Trennebene zwischen den beiden Schlusshälften; Hineinbiegen der Lappen in die Aussparungen der Endschaufel und des Endstücks; Entfernen der Abstützungen.A method according to the invention for mounting a rotor closure in a circumferential groove, which has two end halves, has the following steps: inserting the two end halves in the remaining gap, together with supports, so that the end halves are offset from one another; Inserting a tool in the parting plane between the two end halves; Bending the flaps into the recesses of the end blade and the tail; Remove the supports.
Eine vorteilhafte Weiterbildung des erfindungsgemässen Verfahrens zur Montage eines Rotorschlusses weist ferner folgende Schritte auf: Verdrehen des Werkzeugs um 90°, damit die Lappen weit genug in die Aussparung hineinstehen.An advantageous development of the method according to the invention for mounting a rotor closure further comprises the following steps: Turning the tool through 90 °, so that the tabs protrude far enough into the recess.
Weitere Vorteile der Erfindung werden nachstehend gemeinsam mit der Beschreibung eines bevorzugten Ausführungsbeispiels der Erfindung anhand der Figuren näher dargestellt. Es zeigen:
-
Fig. 1 einen Schnitt in Rotorlängsrichtung durch einen erfindungsgemässen Rotor-Schluss nach Einbau in einen Verdichterrotor; -
Fig. 2 einen teilweisen Schnitt entlang der Linie II - II aus ;Figur 1 -
Fig. 3 eine vergrößerte Detailansicht der beiden Schlusshälften; -
Fig. 4 eine Draufsicht auf die Schlusshälften aus ;Figur 3 -
Fig. 5 einen teilweisen Schnitt, der demjenigen ausFig. 2 entspricht, jedoch mit bei der Montage eingebrachten Abstützungen.
-
Fig. 1 a section in the rotor longitudinal direction by a rotor according to the invention after installation in a compressor rotor; -
Fig. 2 a partial section along the line II - IIFIG. 1 ; -
Fig. 3 an enlarged detail view of the two end halves; -
Fig. 4 a plan view of the final halvesFIG. 3 ; -
Fig. 5 a partial cut, the one fromFig. 2 corresponds, but with introduced during assembly supports.
Die Darstellung in den beigefügten Figuren erfolgt beispielhaft schematisch. In den Figuren sind jeweils gleiche Bauteile mit gleichen Bezugszeichen versehen. Ferner sind nur die für das Verständnis der Erfindung wesentlichen Elemente dargestellt.The illustration in the accompanying figures is exemplary schematically. In the figures, the same components are provided with the same reference numerals. Furthermore, only the essential elements for understanding the invention are shown.
Der zwischen einer Endschaufel 2 und einem Endstück 11 vorhandene Restspalt 15 wird durch zwei Schlusshälften 4, 4 ausgefüllt. Die flachen Schlusshälften 4, 4 weisen dabei im wesentlichen einen Querschnitt auf, der einem so genannten Hammerfuss oder Zwei-Zack-Fuss entspricht, wobei oberhalb der Trennebene 5 eine rechteckförmige Fläche ausgenommen ist. An den oberen, an die rechteckförmige Ausnehmung angrenzenden Ecken der Schlusshälften 4, 4 sind biegbare Lappen 8, 8 angeordnet. Unterhalb der Lappen 8,8 weisen die Schlusshälften 4, 4 Entlastungsschlitze 10, 10 auf.The remaining
Die Endschaufel 2 und das Endstück 11 weisen im Fussbereich an der dem Restspalt 15 zugewandten Seite jeweils eine Aussparung 9, 12 auf, in die die Lappen 8, 8 der Schlusshälften 4, 4 durch Biegen einführbar sind. Durch die in die Aussparungen 9, 12 eingebogenen Lappen 8, 8 ist der Rotorschluss 1 arretiert und gegen Herausfallen gesichert.The
Wie aus
Nachdem sämtliche Laufschaufeln und Zwischenstücke und die Endschaufel 2 und das Endstück 11 in der Umfangsnut 3 montiert sind, bleibt ein Restspalt 15 bestehen. In diesen Restspalt 15 kann nur noch der aus zwei in Umfangsrichtung der Nut 3 geteilten Schlusshälften 4, 4 bestehende Rotor-Schluss 1 mit Abstützungen 14, 14 aufgenommen werden. Die Abstützungen 14, 14 dienen dabei lediglich als Montagehilfe der beiden 3mm bis 5mm dicken Schlusshälften 4, 4, die aus einer Chrom-Molybdän-Vanadium Legierung hergestellt sind. Die Abstützungen 14, 14 sind dabei genauso dick wie die Schlusshälften 4, 4 bzw. geringfügig dünner.After all blades and spacers and the
Mit einem entsprechendem Montagewerkzeug 13 , beispielsweise einem Schraubendreher oder einem flachen Meissel, das etwa 10 mm - 15 mm in die Trennebene 5 zwischen den die beiden Schlusshälften 4,4 eingeschoben wird, werden die beiden Lappen 8, 8 aus der Schluss-Ebene herausgebogen.With a corresponding mounting
Dabei wird das Werkzeug 13 vorzugsweise um 90° gedreht, damit die Lappen 8, 8 weit genug in die Aussparung am Schaufelfuss 9 bzw. in die Aussparung am Endstückfuss 12 hineinragen. Die jeweiligen Aussparungen 9, 12 sind dabei als zylindersegmentartige Vertiefungen in den Endschaufelfuss 7 und den Endstückfuss eingearbeitet, wodurch sich die Bauteile von den übrigen Laufschaufeln und Zwischenstücken unterscheiden. Anschliessend werden die lediglich für die Montage erforderlichen Abstützungen 14, 14 entfernt und der minimale Spalt gleichmässig über den Umfang verteilt. Die nun erreichte Endkonfiguration ist in
Die Demontage erfolgt durch Wegbohren oder Wegschleifen der Lappen 8, 8 und Entnahme der Schlusshälften 4,4.The disassembly is carried out by drilling away or grinding away the
- 11
- Rotor-SchlussRotor end
- 22
- Endschaufelend blade
- 33
- Umfangsnutcircumferential groove
- 44
- Schlusshälftefinal half
- 55
- Trennebeneparting plane
- 66
- Rotorrotor
- 77
- Schaufelfussblade root
- 88th
- Lappencloth
- 99
- Aussparung am SchaufelfussRecess on the blade root
- 1010
- Entlastungsschlitzrelief slot
- 1111
- Endstücktail
- 1212
- Aussparung am EndstückfussRecess at the end piece foot
- 1313
- WerkzeugTool
- 1414
- Abstützungsupport
- 1515
- Restspaltremaining gap
Claims (6)
- Rotor end piece (1) for a rotor (6) of a thermal turbomachine having at least one circumferential slot (3) in which moving blades and intermediate pieces are provided, wherein the rotor end piece (1) has an end blade (2) and an end part (11) and a residual gap (15) is formed between the end blade (2) and the end part (11), in which residual gap (15) two end piece halves (4, 4) with securing tabs (8, 8) in each case arranged thereon in one piece are fitted, said securing tabs (8, 8) being in engagement with the end blade (2) and with the end part (11), respectively, characterized in that the end piece halves (4, 4) have relief slots (10, 10) below the tabs (8, 8), and in that the tabs (8, 8) are arranged at a parting plane (5) of the end piece halves (4, 4).
- Rotor end piece (1) according to Claim 1, characterized in that the end blade (2) and the end part (11) each have a recess (9, 12) in the root region, on the side facing the residual gap (15), into which recess (9, 12) the tabs (8, 8) of the end piece halves (4, 4) can be directed.
- Rotor end piece (1) according to one of Claims 1 to 2, characterized in that the end piece halves (4, 4) have a material thickness of 3 mm to 5 mm.
- Rotor end piece (1) according to one of the preceding claims, characterized in that the end piece halves (4, 4) are made of a chrome-molybdenum-vanadium alloy.
- Method of fitting a rotor end piece in a circumferential slot between an end blade and an end part, said rotor end piece having two end piece halves with securing tabs in each case arranged thereon in one piece, the method comprising the following steps:- inserting the two end piece halves into the residual gap together with supports, so that the end piece halves are offset from one another;- inserting a tool into a parting plane between the two end piece halves;- bending the securing tabs into recesses of the end blade and of the end part;- removing the supports.
- Method of fitting a rotor end piece according to Claim 5, the method also comprising the following steps:- turning the tool by 90° so that the securing tabs project far enough into the recess.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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CH3232005 | 2005-02-23 |
Publications (3)
Publication Number | Publication Date |
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EP1698759A2 EP1698759A2 (en) | 2006-09-06 |
EP1698759A3 EP1698759A3 (en) | 2012-04-04 |
EP1698759B1 true EP1698759B1 (en) | 2015-06-03 |
Family
ID=34974751
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP06110072.3A Not-in-force EP1698759B1 (en) | 2005-02-23 | 2006-02-17 | Rotor end piece |
Country Status (2)
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US (1) | US7367778B2 (en) |
EP (1) | EP1698759B1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US9828865B2 (en) | 2012-09-26 | 2017-11-28 | United Technologies Corporation | Turbomachine rotor groove |
US10677247B2 (en) * | 2016-01-07 | 2020-06-09 | Stein Seal Company | Slurry seal assembly |
US10465699B2 (en) * | 2017-01-26 | 2019-11-05 | DOOSAN Heavy Industries Construction Co., LTD | Compressor blade locking mechanism in disk with tangential groove |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE724549C (en) * | 1939-12-09 | 1942-08-29 | Aeg | Blade lock for a turbine blade made using intermediate pieces |
US2410588A (en) | 1942-06-23 | 1946-11-05 | Northrop Aircraft Inc | Turbine blade and assembly thereof |
FR974989A (en) * | 1948-09-17 | 1951-02-28 | Lock for blading drum-shaped rotors of axial compressors and steam or gas turbines | |
CH273791A (en) | 1949-05-25 | 1951-02-28 | Tech Studien Ag | Blade lock on blades of axial flow machines without filling pieces. |
DE1040047B (en) * | 1954-12-23 | 1958-10-02 | Maschf Augsburg Nuernberg Ag | Attachment of the end vane of an impeller for axial centrifugal machines |
GB980337A (en) * | 1962-05-08 | 1965-01-13 | Power Jets Res & Dev Ltd | Improvements in or relating to a rotor for a compressor turbine or like bladed fluidflow machine |
US3383094A (en) * | 1967-01-19 | 1968-05-14 | Gen Electric | Rotor blade locking means |
DE2002469C3 (en) * | 1970-01-21 | 1978-03-30 | Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Blade fastening in a dovetail-shaped circumferential groove of a rotor of flow machines with axial flow, in particular gas turbine jet engines |
US4633554A (en) * | 1985-08-08 | 1987-01-06 | Westinghouse Electric Corp. | Method for repairing a steam turbine or generator rotor |
DD271243A3 (en) * | 1987-10-01 | 1989-08-30 | Goerlitzer Maschinenbau Veb | SHOVEL LOCK ASSEMBLY WITH MINIMIZED SHOVEL LOCK |
US4915587A (en) * | 1988-10-24 | 1990-04-10 | Westinghouse Electric Corp. | Apparatus for locking side entry blades into a rotor |
DE10134611A1 (en) | 2000-12-16 | 2002-06-27 | Alstom Switzerland Ltd | Fixing device for a blade mounting of a compressor or turbine stage of a gas turbine system comprises a blade having a counter-contour corresponding to a connecting element of a wedge element to produce a form-locking connection |
DE10310432A1 (en) | 2003-03-11 | 2004-09-23 | Alstom Technology Ltd | Rotor end |
-
2006
- 2006-02-17 EP EP06110072.3A patent/EP1698759B1/en not_active Not-in-force
- 2006-02-23 US US11/276,296 patent/US7367778B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP1698759A3 (en) | 2012-04-04 |
EP1698759A2 (en) | 2006-09-06 |
US20060257248A1 (en) | 2006-11-16 |
US7367778B2 (en) | 2008-05-06 |
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