EP0422433A1 - Arrangement for fastening turbine blades - Google Patents

Arrangement for fastening turbine blades Download PDF

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Publication number
EP0422433A1
EP0422433A1 EP90118255A EP90118255A EP0422433A1 EP 0422433 A1 EP0422433 A1 EP 0422433A1 EP 90118255 A EP90118255 A EP 90118255A EP 90118255 A EP90118255 A EP 90118255A EP 0422433 A1 EP0422433 A1 EP 0422433A1
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EP
European Patent Office
Prior art keywords
support
arrangement according
turbo blades
sections
arrangement
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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.)
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Application number
EP90118255A
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German (de)
French (fr)
Inventor
Uwe Schmidt-Eisenlohr
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
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MTU Motoren und Turbinen Union Muenchen GmbH
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Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0422433A1 publication Critical patent/EP0422433A1/en
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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
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference

Definitions

  • the invention relates to an arrangement for fastening turbo blades on the circumference of a rotor, in which an outwardly widening support strip is formed on the outer circumference of the rotor and is clasped on both sides by retaining flanges of the turbo blades.
  • the support strip consists of support sections of equal length, arranged alternately, with support beads formed on both sides and intermediate sections without support beads, and the holding flanges have the width of the support sections.
  • the arrangement has the advantage that with simultaneous quick assembly and hot gas shielding of the rotor, a rotationally symmetrical contour can be achieved, and thus no unfavorable stress concentrations occur at some points in the outer area of the rotor.
  • the overall construction can thus be designed to be tension-friendly and unnecessary, weight-increasing reinforcements can be avoided.
  • the holding flanges are preferably arranged radially under each turbo blade and have such a width and wall thickness that the centrifugal forces occurring during operation can be absorbed with the necessary certainty.
  • An advantageous development of the invention provides that at least at one point on the circumference a means for locking the turbo blades in the circumferential direction is attached.
  • This is preferably designed as an axially fixable locking filler fitted in at least one intermediate section.
  • Such means for locking can also be attached to several equally distributed locations on the circumference.
  • Filling pieces are advantageously used on both sides of the intermediate sections in order to achieve a favorable flow contour, and they do not have a supporting function.
  • Another advantageous embodiment of the invention provides that several, but at least two turbo blades with retaining flanges form an integral component. It is expedient to design the assignment of retaining flanges and turbo blades in the same way as for individual blades. This arrangement has the advantage that the assembly effort ver is reduced, and there is the possibility of support in the event of material failure in individual holding flanges. It is also advantageous that the holding flanges are connected to one another via connecting webs on both sides of the support strip. This enables the filler pieces, which are arranged in the intermediate sections, to be fixed. Furthermore, the locking filler piece can be axially fixed via these connecting webs.
  • FIG. 1 shows a partial axial section or cross section through a fastening arrangement, by means of which turbo blades 2 provided on the circumference of a rotor 1 are fastened.
  • the attachment takes place in that on the outer circumference of the rotor 1 a support strip 3 is formed which extends in the circumferential direction and which are clasped by retaining flanges 4a, b formed on the turbo blades 2.
  • the support strip 3 is shown in more detail in Figures 3 and 4.
  • the support strip 3 is constructed from support sections 5 of the same length, alternatingly arranged, and intermediate sections 6 arranged between them.
  • the support bar 3 is shown cut at the level of an intermediate section 6, and it can be seen that the support sections 5 consist of support beads 7 formed on both sides of the support bar 3.
  • FIG. 2 shows a top view of an integral component 8 consisting of two turbo blades 2, in which the two turbo blades 2, which are supported by holding flanges 4a, b, stand on a platform 9 which extends over two divisions of the blades.
  • the support bar 3 lying under the platform 9 is indicated by dashed lines.
  • FIG. 5 shows a cross section through the support strip 3, the outer contour of the platform 9 (FIG. 4) together with the turbo blades 2 being indicated.
  • the support bar 3 is surrounded by the holding flanges 4a, b, while in the area of the intermediate sections 6 locking filler pieces 10 are used which prevent displacement of the holding flanges 4a, b connected to the platform 9 in the circumferential direction.
  • These locking filler pieces 10 do not have to be attached in each intermediate section 6, it may be sufficient to arrange them only in a single intermediate section 6.
  • simple filler pieces 11 or molded elements 16 integrally connected to the platform are used at the outer ends of the components in order to achieve a favorable flow contour.
  • FIGS. 6a and 6b show two sections according to lines A-B from FIG.
  • These support strips 13, as shown in FIG. 6b, are integrally formed on the blade root region 14 of the turbo blades 2 pointing radially inwards and, in cooperation with the retaining tabs 12, serve to fix the locking filler pieces 10 and the simple filler pieces 11.
  • the support strip 13 is preferably radial in this case inner area with two adjacent retaining flanges 4a and 4b connected back-like.
  • FIGS. 7 and 8 show a further preferred embodiment of the invention, in which the two tangential outer ends of the platform 9 are formed diagonally opposite one another as extensions 15, 16 of the holding flanges 4a and 4b.
  • this extension is shown in section along the line VII of Figure 8, it can be seen that it has a cavity 17 for weight reduction.
  • FIG. 9 shows an alternative embodiment of the invention, which differs from the ones described above in the mushroom-shaped shape of the support strip 3a and in the formation of a merely thin wall 18 as a connection in the circumferential direction of adjacent holding flanges 4c.
  • a radially inserted pin 19 is provided in order to prevent the platform 9 from slipping in the circumferential direction with respect to the support bar 3a.
  • FIG. 10 The top view of this embodiment in FIG. 10 shows how the bolt 19 is inserted between two turbo blades 2. Furthermore, the connection of adjacent retaining flanges 4c can be seen through the relatively thin walls 18, as a result of which a smooth contour of the blade root is produced in the circumferential direction.

Abstract

An arrangement for fastening turbine blades (2) on a rotor (1), having a supporting strip (3), which expands outwards on the outer circumference, is bracketed on both sides by retaining flanges (4a, b) of the turbine blades. In this case, the supporting strip consists of supporting sections (5) which are of equal length, are arranged alternately, and have supporting beads (7), integrally formed on both sides, and intermediate sections (6), without supporting beads, and the retaining flanges having the same width as the supporting sections. The invention has the advantage that the supporting structure of the rotor is of rotationally symmetrical construction up to the maximum diameter, and the surface which is wetted by hot gas is noticeably reduced.

Description

Die Erfindung betrifft eine Anordnung zur Befestigung von Turboschau­feln am Umfang eines Rotors, bei dem am Außenumfang des Rotors eine nach außen hin sich erweiterende Tragleiste angeformt ist, die beid­seitig von Halteflanschen der Turboschaufeln umklammert ist.The invention relates to an arrangement for fastening turbo blades on the circumference of a rotor, in which an outwardly widening support strip is formed on the outer circumference of the rotor and is clasped on both sides by retaining flanges of the turbo blades.

Eine derartige Anordnung ist beispielsweise aus DE-OS 19 57 614 be­kannt geworden, bei der die der Außenumfang des Rotors bzw. der Ro­torscheibe selber als Tragleiste ausgeformt ist. Bei dieser Anordnung werden die Halteflansche mit der Tragleiste verschweißt, und bilden so ein integrales Bauteil.Such an arrangement has become known, for example, from DE-OS 19 57 614, in which the outer circumference of the rotor or the rotor disk itself is shaped as a support strip. With this arrangement, the holding flanges are welded to the support bar, thus forming an integral component.

Hiervon ausgehend ist es Aufgabe der vorliegenden Erfindung, eine Anordnung zu schaffen, welche die Vorteile der vorbekannten Anordnung, nämlich die Abschirmung des Rotors vom Heißgasstrom, aufweist und gleichzeitig einfach montierbar ist. Ferner soll auch bei Beschädigung einzelner Schaufeln ein Auswechseln schnell durchführbar sein.Proceeding from this, it is an object of the present invention to provide an arrangement which has the advantages of the known arrangement, namely the shielding of the rotor from the hot gas flow, and at the same time is simple to install. Furthermore, it should also be possible to replace it quickly if individual blades are damaged.

Erfindungsgemäß wird diese Aufgabe dadurch gelöst, daß die Tragleiste aus gleich langen alternierend angeordneten Tragabschnitten mit beid­seitig angeformtem Tragwulsten und Zwischenabschnitten ohne Tragwul­sten besteht, und die Halteflansche die Breite der Tragabschnitte aufweist.According to the invention, this object is achieved in that the support strip consists of support sections of equal length, arranged alternately, with support beads formed on both sides and intermediate sections without support beads, and the holding flanges have the width of the support sections.

Die Anordnung hat den Vorteil, daß bei gleichzeitig schneller Mon­tierbarkeit und Heißgasabschirmung des Rotors eine rotationsymetrische Kontur erzielbar ist, und somit keine ungünstigen Spannungskon­zentrationen an einigen Punkten im Rotoraußenbereich auftreten. Somit läßt sich die Gesamtkonstruktion spannungsgünstig auslegen und unnö­tige, gewichtserhöhende Verstärkungen vermeiden.The arrangement has the advantage that with simultaneous quick assembly and hot gas shielding of the rotor, a rotationally symmetrical contour can be achieved, and thus no unfavorable stress concentrations occur at some points in the outer area of the rotor. The overall construction can thus be designed to be tension-friendly and unnecessary, weight-increasing reinforcements can be avoided.

Vorzugsweise sind die Halteflansche radial unter jeder Turboschaufel angeordnet, und weisen eine derartige Breite und Wandstärke auf, daß die im Betrieb auftretenden Fliehkräfte mit der nötigen Sicherheit aufgenommen werden können.The holding flanges are preferably arranged radially under each turbo blade and have such a width and wall thickness that the centrifugal forces occurring during operation can be absorbed with the necessary certainty.

Eine vorteilhafte Weiterbildung der Erfindung sieht vor, daß minde­stens an einer Stelle des Umfangs ein Mittel zur Arretierung der Tur­boschaufeln in Umfangsrichtung angebracht ist. Dieses ist vorzugsweise als in mindestens einem Zwischenabschnitt eingepaßtes axial fi­xierbares Arretierfüllstück ausgebildet. Es können auch an mehreren gleich verteilten Stellen des Umfangs derartige Mittel zur Arretierung angebracht sein. Beidseitig der Zwischenabschnitte sind vorteil­hafterweise Füllstücke zur Erzielung einer günstigen Strömungskontur eingesetzt, die keine tragende Funktion übernehmen.An advantageous development of the invention provides that at least at one point on the circumference a means for locking the turbo blades in the circumferential direction is attached. This is preferably designed as an axially fixable locking filler fitted in at least one intermediate section. Such means for locking can also be attached to several equally distributed locations on the circumference. Filling pieces are advantageously used on both sides of the intermediate sections in order to achieve a favorable flow contour, and they do not have a supporting function.

Eine weitere vorteilhafte Ausbildung der Erfindung sieht vor, daß mehrere, mindestens jedoch zwei Turboschaufeln mit Halteflanschen ein integrales Bauteil bilden. Dabei ist es zweckmäßig, die Zuordnung von Halteflanschen und Turboschaufeln genau wie bei Einzelschaufeln auszu­bilden. Diese Anordnung hat den Vorteil, daß der Montageaufwand ver­ ringert ist, und die Möglichkeit der Abstützung bei Werkstoffversagen in einzelnen Halteflanschen besteht. Weiterhin vorteilhaft ist es, daß auf beiden Seiten der Tragleiste die Halteflansche über Verbindungs­stege miteinander verbunden sind. Das ermöglicht eine Fixierung der Füllstücke, die in den Zwischenabschnitten angeordnet sind. Ferner kann über diese Verbindungsstege die axiale Fixierung des Arre­tierfüllstückes erfolgen.Another advantageous embodiment of the invention provides that several, but at least two turbo blades with retaining flanges form an integral component. It is expedient to design the assignment of retaining flanges and turbo blades in the same way as for individual blades. This arrangement has the advantage that the assembly effort ver is reduced, and there is the possibility of support in the event of material failure in individual holding flanges. It is also advantageous that the holding flanges are connected to one another via connecting webs on both sides of the support strip. This enables the filler pieces, which are arranged in the intermediate sections, to be fixed. Furthermore, the locking filler piece can be axially fixed via these connecting webs.

Die Erfindung wird nachfolgend anhand der beigefügten Zeichnungen näher erläutert. Dabei zeigt:

  • Fig. 1 einen Axialteilschnitt durch eine Rotorschaufelbefestigung,
  • Fig. 2 die Anordnung gemäß Fig. 1 in Draufsicht,
  • Fig. 3 eine Tragleiste im Querschnitt,
  • Fig. 4 die Tragleiste in Draufsicht,
  • Fig. 5 einen Schnitt im Umfangsrichtung durch die Befestigungsan­ordnung,
  • Fig. 6a einen Teilquerschnitt durch die Befestigungsanordnung,
  • Fig. 6b einen anderen Teilquerschnitt durch die Befestigungsanordnung,
  • Fig. 7 einen weiteren Querschnitt durch die Vorrichtung zwischen zwei Halteflanschen,
  • Fig. 8 einen Schnitt analog Fig. 5 mit Außenelementen gemäß Fig. 7
  • Fig. 9 eine alternative Ausführungsform im Querschnitt,
  • Fig. 10 die Ausführungsform gemäß Fig. 9 in Draufsicht.
The invention is explained below with reference to the accompanying drawings. It shows:
  • 1 is a partial axial section through a rotor blade attachment,
  • 2 shows the arrangement according to FIG. 1 in plan view,
  • 3 is a support bar in cross section,
  • 4 the support bar in plan view,
  • 5 shows a section in the circumferential direction through the fastening arrangement,
  • 6a shows a partial cross section through the fastening arrangement,
  • 6b shows another partial cross section through the fastening arrangement,
  • 7 shows a further cross section through the device between two holding flanges,
  • 8 shows a section analogous to FIG. 5 with outer elements according to FIG. 7
  • 9 shows an alternative embodiment in cross section,
  • Fig. 10 shows the embodiment of FIG. 9 in plan view.

In Fig. 1 ist ein Axialteilschnitt bzw. Querschnitt durch eine Befe­stigungsanordnung gezeigt, mittels der am Umfang eines Rotors 1 vorge­sehene Turboschaufeln 2 befestigt werden. Die Befestigung erfolgt dadurch, daß am Außenumfang des Rotors 1 eine sich im Umfangsrichtung erstreckende Tragleiste 3 angeformt ist, die von an den Turboschaufeln 2 angeformten Halteflanschen 4a,b umklammert sind. Die Tragleiste 3 ist in den Figuren 3 und 4 näher dargestellt. In der Draufsicht gemäß Figur 4 ist zu erkennen, daß die Tragleiste 3 aus gleich langen alternierend angeordneten Tragabschnitten 5 und dazwischen ange­ordneten Zwischenabschnitten 6 aufgebaut ist. In Fig. 3 ist die Trag­leiste 3 in Höhe eines Zwischenabschnittes 6 geschnitten dargestellt, und es ist zu erkennen, daß die Tragabschnitte 5 aus beidseitig an der Tragleiste 3 angeformten Tragwulsten 7 bestehen.1 shows a partial axial section or cross section through a fastening arrangement, by means of which turbo blades 2 provided on the circumference of a rotor 1 are fastened. The attachment takes place in that on the outer circumference of the rotor 1 a support strip 3 is formed which extends in the circumferential direction and which are clasped by retaining flanges 4a, b formed on the turbo blades 2. The support strip 3 is shown in more detail in Figures 3 and 4. In the plan view according to FIG. 4 it can be seen that the support strip 3 is constructed from support sections 5 of the same length, alternatingly arranged, and intermediate sections 6 arranged between them. In Fig. 3, the support bar 3 is shown cut at the level of an intermediate section 6, and it can be seen that the support sections 5 consist of support beads 7 formed on both sides of the support bar 3.

In Fig. 2 ist in Draufsicht ein aus zwei Turboschaufeln 2 bestehendes integrales Bauteil 8 dargestellt, bei dem die beiden Turboschaufeln 2, die durch Halteflanschen 4a,b getragen werden, auf einer Plattform 9 stehen, die sich über zwei Teilungen der Beschaufelung erstreckt. Die unter der Plattform 9 liegende Tragleiste 3 ist dabei gestrichelt angedeutet.2 shows a top view of an integral component 8 consisting of two turbo blades 2, in which the two turbo blades 2, which are supported by holding flanges 4a, b, stand on a platform 9 which extends over two divisions of the blades. The support bar 3 lying under the platform 9 is indicated by dashed lines.

Fig. 5 zeigt einen Querschnitt durch die Tragleiste 3, wobei die Au­ßenkontur der Plattform 9 (Fig. 4) zusammen mit den Turboschaufeln 2 angedeutet ist. Im Bereich der Tragabschnitte 5 ist die Tragleiste 3 von den Halteflanschen 4a,b umgeben, während im Bereich der Zwischen­abschnitte 6 Arretierfüllstücke 10 eingesetzt sind, die ein Ver­schieben mit der Plattform 9 verbundenen Halteflanschen 4a,b in Um­fangsrichtung verhindern. Diese Arretierfüllstücke 10 müssen nicht in jedem Zwischenabschnitt 6 angebracht sein, es kann ausreichend sein, diese nur in einem einzeigen Zwischenabschnitt 6 anzuordnen. In den anderen Zwischenabschnitten werden einfache Füllstücke 11 oder in­tegral mit der Plattform verbundene Formelemente 16 (Fig. 7) an den Außenenden der Bauteile zur Erzielung einer günstigen Strömungskontur eingesetzt.FIG. 5 shows a cross section through the support strip 3, the outer contour of the platform 9 (FIG. 4) together with the turbo blades 2 being indicated. In the area of the support sections 5, the support bar 3 is surrounded by the holding flanges 4a, b, while in the area of the intermediate sections 6 locking filler pieces 10 are used which prevent displacement of the holding flanges 4a, b connected to the platform 9 in the circumferential direction. These locking filler pieces 10 do not have to be attached in each intermediate section 6, it may be sufficient to arrange them only in a single intermediate section 6. In the In other intermediate sections, simple filler pieces 11 or molded elements 16 (FIG. 7) integrally connected to the platform are used at the outer ends of the components in order to achieve a favorable flow contour.

Die Figuren 6a und 6b zeigen zwei Schnitte gemäß den Linien A-B aus Figur 5. In Figur 6a ist dabei die Form eines Arretierfüllstückes 10 im Querschnitt zu sehen, an dem radial innen Haltebügel 12 angeformt sind, die Stützleisten 13 umgreifen. Diese Stützleisten 13 sind, wie in Figur 6b dargestellt, am Schaufelfußbereich 14 der Turboschaufeln 2 nach radial innen weisend angeformt und dienen im Zusammenwirken mit den Haltelaschen 12 der Fixierung der Arretierfüllstücke 10 und der einfachen Füllstücke 11. Die Stützleiste 13 ist dabei vorzugsweise in ihrem radial inneren Bereich mit je zwei benachbarten Halteflanschen 4a bzw. 4b rückenartig verbunden.FIGS. 6a and 6b show two sections according to lines A-B from FIG. These support strips 13, as shown in FIG. 6b, are integrally formed on the blade root region 14 of the turbo blades 2 pointing radially inwards and, in cooperation with the retaining tabs 12, serve to fix the locking filler pieces 10 and the simple filler pieces 11. The support strip 13 is preferably radial in this case inner area with two adjacent retaining flanges 4a and 4b connected back-like.

In Figur 7 und 8 ist eine weitere bevorzugte Ausführungsform der Er­findung dargestellt, bei der die beiden tangentialen Außenenden der Plattform 9 diagonal sich gegenüberliegend als Verlängerungen 15, 16 der Halteflansche 4a bzw. 4b ausgebildet sind. In Figur 7 ist diese Verlängerung im Schnitt gemäß der Linie VII aus Figur 8 dargestellt, wobei zu erkennen ist, daß diese einen Hohlraum 17 zur Gewichtsredu­zierung aufweist.FIGS. 7 and 8 show a further preferred embodiment of the invention, in which the two tangential outer ends of the platform 9 are formed diagonally opposite one another as extensions 15, 16 of the holding flanges 4a and 4b. In Figure 7, this extension is shown in section along the line VII of Figure 8, it can be seen that it has a cavity 17 for weight reduction.

In Figur 9 ist eine alternative Ausführungsform der Erfindung darge­stellt, die sich von den oben beschriebenen durch die pilzförmige Form der Tragleiste 3a sowie die Ausbildung einer lediglich dünnen Wandung 18 als Verbindung in Umfangsrichtung benachbarter Halte­flansche 4c unterscheidet. Um ein Verrutschen der Plattform 9 in Um­fangsrichtung gegenüber der Tragleiste 3a zu verhindern, ist ein ra­dial eingesetzter Bolzen 19 vorgesehen.FIG. 9 shows an alternative embodiment of the invention, which differs from the ones described above in the mushroom-shaped shape of the support strip 3a and in the formation of a merely thin wall 18 as a connection in the circumferential direction of adjacent holding flanges 4c. In order to prevent the platform 9 from slipping in the circumferential direction with respect to the support bar 3a, a radially inserted pin 19 is provided.

In der Draufsicht dieser Ausführungsform in Figur 10 ist dargestellt, wie der Bolzen 19 zwischen zwei Turboschaufeln 2 eingesetzt ist. Fer­ner ist die Verbindung benachbarter Halteflansche 4c durch die relativ dünnen Wandungen 18 erkennbar, wodurch eine im Umfangsrichtung glatte Kontur des Schaufelfußes erzeugt wird.The top view of this embodiment in FIG. 10 shows how the bolt 19 is inserted between two turbo blades 2. Furthermore, the connection of adjacent retaining flanges 4c can be seen through the relatively thin walls 18, as a result of which a smooth contour of the blade root is produced in the circumferential direction.

Claims (8)

1. Anordnung zur Befestigung von Turboschaufeln am Umfang eines Ro­tors, bei dem am Außenumfang des Rotors eine nach außen hin sich erweiternde Tragleiste angeformt ist die beidseitig von Halte­flanschen der Turboschaufeln umklammert ist, dadurch gekennzeich­net, daß die Tragleiste (3) aus gleich langen, alternierend ange­ordneten Tragabschnitten (5) mit beidseitig angeoformten Tragwul­sten (7) und Zwischenabschnitten (6) ohne Tragwulsten besteht, und die Halteflansche (4a,b) die Breite der Tragabschnitte (5) auf­weisen.1. Arrangement for fastening turbo blades on the circumference of a rotor, in which an outwardly widening support bar is formed on the outer circumference of the rotor and is clasped on both sides by retaining flanges of the turbo blades, characterized in that the support bar (3) of the same length, alternating arranged support sections (5) with support beads (7) molded on both sides and intermediate sections (6) without support beads, and the holding flanges (4a, b) have the width of the support sections (5). 2. Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Halte­flansche (4a,b) radial unter jeder Turboschaufel (2) angeordnet sind.2. Arrangement according to claim 1, characterized in that the holding flanges (4a, b) are arranged radially under each turbo blade (2). 3. Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß an minde­stens einem Halteflanschpaar (4a,b) Mittel zur Arretierung der Turboschaufeln (2) in Umfangsrichtung angebracht sind.3. Arrangement according to claim 1, characterized in that on at least one retaining flange pair (4a, b) means for locking the turbo blades (2) are attached in the circumferential direction. 4. Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß das Mittel zur Arretierung der Turboschaufeln (2) als in einem Zwischenab­schnitt (6) eingepaßtes, axial fixierbares Arretierfüllstück (10) ausgebildet ist.4. Arrangement according to claim 1, characterized in that the means for locking the turbo blades (2) is designed as an axially fixable locking filler (10) fitted in an intermediate section (6). 5. Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß an den Außenenden unter der Plattform (9), Füllstücke (11) zur Erzielung einer, in Umfangsrichtung, glatten Strömungskontur eingesetzt sind.5. Arrangement according to claim 1, characterized in that at the outer ends under the platform (9), filler pieces (11) are used to achieve a, in the circumferential direction, smooth flow contour. 6. Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß mindestens zwei Turboschaufeln (2) mit Halteflanschen (4a,b) ein integrales Bauteil bilden.6. Arrangement according to claim 1, characterized in that at least two turbo blades (2) with retaining flanges (4a, b) form an integral component. 7. Anordnung nach Anspruch 4, dadurch gekennzeichnet, daß Stützlei­sten (13) im Bereich zwischen zwei benachbarten Halteflanschen (4a,b) an den Turboschaufeln (2) angebracht sind.7. Arrangement according to claim 4, characterized in that support strips (13) in the region between two adjacent retaining flanges (4a, b) on the turbo blades (2) are attached. 8. Anordnung nach Anspruch 4, 5 und 7, dadurch gekennzeichnet, daß an den Füllstücken (10,11) Haltelaschen (12) angebracht sind, die mit den Stützleisten (13) zu deren Fixierung dienen.8. Arrangement according to claim 4, 5 and 7, characterized in that on the filler pieces (10,11) retaining tabs (12) are attached, which serve to fix the support strips (13).
EP90118255A 1989-10-13 1990-09-22 Arrangement for fastening turbine blades Withdrawn EP0422433A1 (en)

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Application Number Priority Date Filing Date Title
DE19893934207 DE3934207A1 (en) 1989-10-13 1989-10-13 ARRANGEMENT FOR FASTENING TURBO BLADES
DE3934207 1989-10-13

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EP0422433A1 true EP0422433A1 (en) 1991-04-17

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US5638411A (en) * 1991-05-23 1997-06-10 Mitsubishi Denki Kabushiki Kaisha Stuff bit synchronization system
DE19904027A1 (en) * 1999-02-02 2000-08-03 Abb Research Ltd Compressor for compression of gaseous media has ribs provided on hub of compressor wheel and form-fit into lower section of blades, forming mechanical connection
CN103967840A (en) * 2013-02-04 2014-08-06 航空技术空间股份有限公司 Attaching the blades of an axial turbocompressor to the compressor drum
EP3862571A1 (en) * 2020-02-06 2021-08-11 ABB Schweiz AG Fan, synchronous machine and method for producing a fan

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CN103967840A (en) * 2013-02-04 2014-08-06 航空技术空间股份有限公司 Attaching the blades of an axial turbocompressor to the compressor drum
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US9739150B2 (en) 2013-02-04 2017-08-22 Safran Aero Boosters Sa Attaching the blades of an axial turbocompressor to the compressor drum
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EP3862571A1 (en) * 2020-02-06 2021-08-11 ABB Schweiz AG Fan, synchronous machine and method for producing a fan
WO2021155966A1 (en) * 2020-02-06 2021-08-12 Abb Schweiz Ag Fan, synchronous machine and method of producing a fan
CN114901952A (en) * 2020-02-06 2022-08-12 Abb瑞士股份有限公司 Fan, synchronous motor and method for producing fan

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