EP1491723B1 - Method of modifying the coupling geometry in shroud band segments of turbine blades - Google Patents

Method of modifying the coupling geometry in shroud band segments of turbine blades Download PDF

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Publication number
EP1491723B1
EP1491723B1 EP04102733A EP04102733A EP1491723B1 EP 1491723 B1 EP1491723 B1 EP 1491723B1 EP 04102733 A EP04102733 A EP 04102733A EP 04102733 A EP04102733 A EP 04102733A EP 1491723 B1 EP1491723 B1 EP 1491723B1
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EP
European Patent Office
Prior art keywords
coupling
geometry
removal
application
modified
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EP04102733A
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German (de)
French (fr)
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EP1491723A1 (en
EP1491723B2 (en
Inventor
Hartmut Hähnle
Christoph Nagler
Ingo Schwarz
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General Electric Technology GmbH
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Alstom Technology AG
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Classifications

    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/49336—Blade making
    • 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
    • Y10T29/49716—Converting

Definitions

  • the invention relates to a method for modifying the coupling geometry in shroud segments of turbine blades.
  • the type of coupling ie the coupling angle and the coupling surface
  • the type of coupling is of essential importance for the performance of the turbine blades, and in particular for the wear behavior in the area of the coupling, because of the transmission of the coupling forces. Due to the og factors that affect the shroud coupling, even small changes in the turbine design of individual turbine stages, for example, by retooling a turbine stage or changed operating conditions, can lead to undesirably high wear on existing turbine stages. If it is determined on the basis of operating experience that the wear in the coupling region of two turbine shroud segments is impermissibly high, so far only a repair of the turbine blade in the coupling region takes place.
  • the coupling region is usually coated with chromium carbide. In extreme cases, individual blades or blade groups must be replaced. In addition, reduce the maintenance intervals in unfavorable cases, which reduces the efficiency of the system.
  • US-4,291,448-A discloses a method of repairing closed shroud segments by grinding the affected zones and applying additional material to restore the original coupling geometry.
  • the invention is therefore based on the object to avoid the above-mentioned disadvantages of the prior art and to provide a method for modifying the coupling angle in shroud segments of turbine blades, which improves the wear behavior in the coupling region and the life of the shroud segments of turbine blades on effective and cost-effective Way extended.
  • the modification should be carried out either on existing turbine blades or on new parts that are interchangeable with turbine blades that have reached the end of their life.
  • the method according to the invention for modifying the coupling geometry for shroud segments of turbine blades has the following steps: calculating a modified coupling geometry.
  • simulations are used for applications in which the changed flow conditions in a modernized turbomachine and their effects on the relevant turbine stage can be analyzed.
  • an advantageous development of the method according to the invention provides that the application zones are previously processed in such a way that an improved order cross-section is provided. This is done, for example, by removing material at a point of the shroud segment, which provides a sufficiently large cross-section to order material safely and reliably connect.
  • this also angular cross-sections can be defined, which are advantageous for manufacturing reasons, since the application material is connected on several sides with the original shroud segment.
  • An advantageous embodiment of the method according to the invention further provides that the modified coupling geometry provides for a change in the coupling angle by at least ⁇ 5 °, preferably ⁇ 15 ° to ⁇ 40 °.
  • the angle data are measured from the circumferential direction. It is important that an increase in the coupling angle is aimed for when the coupling forces transmitted are too small. Conversely, if transmission forces are too great, the aim is to reduce the coupling angle.
  • a particularly advantageous embodiment of the method provides that the change in the coupling angle is ⁇ 25 °. This angle has proved to be advantageous, for example, in experiments for changing coupling angles from 15 ° to 40 °.
  • Yet another advantageous embodiment of the method according to the invention provides that the application of additional material takes place by means of build-up welding.
  • the deposition welding has proven by laser.
  • Yet another advantageous embodiment of the method according to the invention provides that the removal of excess material takes place by means of grinding. If larger segments are to be separated, a cut-off grinder, for example, can be used here.
  • a further method for modifying an existing casting mold for a turbine blade with a shroud segment, for a modified geometry of the coupling angle comprises the following steps: calculating a modified coupling geometry; Removal of mold material located within the modified coupling geometry; and / or applying additional, nonexistent Mold material outside the modified coupling geometry; Post-processing of the removal and / or order zones.
  • these modifications are the reverse steps, as in the inventive method according to claim 1, since this is a negative mold.
  • Such modification of existing molds is helpful in making replacement turbine blades that would otherwise need to be subsequently modified.
  • a cost-effective option for further use of existing molds is presented, without having to sacrifice the benefits of the modified coupling geometry.
  • an advantageous embodiment of the method according to the invention provides that the modified coupling geometry has a change in the coupling angle by at least ⁇ 5 °, preferably ⁇ 15 ° to ⁇ 40 °. It is particularly advantageous if the change in the coupling angle is ⁇ 25 °.
  • FIG. 1 shows a perspective view of a grid model of a turbine blade 1 with a shroud segment 7.
  • the turbine blade 1 has at its upper end a blade head 2 and at its lower end a blade root 3, which continues in a shaft 4 (only indicated).
  • a shaft 4 (only indicated).
  • the blade profile leading edge 5 and on the right side of the drawing the blade profile trailing edge 6 is shown.
  • the shroud segment 7 extends essentially transversely to the blade chord 2 extending between the blade profile leading edge 5 and the blade profile trailing edge 6 and parallel to the circumferential direction U.
  • the shroud segment 7 does not extend beyond the entire blade depth, but only on an area in the blade center.
  • the transition between the shroud segment 7 and the blade head 2 is determined by transition radii.
  • 7 contact surfaces 8, 9 are provided on the side surfaces of the shroud segment, which abut against contact surfaces of adjacent shroud segments during operation.
  • Figures 3a and 3b show a schematic plan view of the coupling region of shroud segments 7 from the pressure side and suction side without modification.
  • the pressure-side end of the shroud segment 7 shown in FIG. 3 a shows approximately centrally a fin 11 which serves as a sealing web between the housing inner wall of the turbine housing and the turbine shroud constructed from the shroud segments 7.
  • the contact surface 8 of the shroud segment 7, which serves the mutual support of adjacent turbine blades, has in the present embodiment, prior to the modification at an angle of 15 ° measured from the circumferential direction. Furthermore, the stepped or Z-shaped side edge of the shroud segment can be clearly seen without modification.
  • the suction-side end of the shroud segment 7 shown in FIG. 3b likewise has an approximately centrally arranged fin 11.
  • the contact surface 9, which virtually forms the long connecting line between the upper and lower horizontal Z beams, also has an angle of 15 on the suction-side shroud segment 7 °, measured from the circumferential direction, on.
  • the calculated in the present embodiment optimum angle for the modified pressure-side and suction-side contact surfaces is measured at 40 ° from the circumferential direction.
  • the desired angle change is thus 25 ° each.
  • the corresponding shroud sections are prepared so that an optimal cross-section for the application of new shroud material is provided by previous material removal.
  • These preparation surfaces are limited in Figures 3a and 3b by dashed lines and the outer contour and identified by reference numeral 10.
  • the removal of material takes place by a grinding process. In principle, however, any other suitable removal method is possible.
  • Figures 4a and 4b show a schematic plan view of the coupling region of the shroud segments 7 of the pressure and suction side with modified coupling geometry. Again, the fins 11 are shown, which are parallel to the circumferential direction shown by arrow U.
  • the contact surfaces 8, 9 extend at an angle of 40 °, measured from the circumferential direction.
  • FIG. 4b clearly shows the angle change from 15 ° to 40 ° caused by the removal of material and the application of material.
  • the removal of material by means of cut-off grinding and the material application by means of build-up welding is carried out.
  • any suitable order and removal method can be used.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)

Abstract

The method of modification of the coupling geometry of the cover segments (7) of a turbine vane involves computing a modified geometry and levelling the cover segment material which extends beyond the modified geometry. This is followed by application of additional material (13) outside the existing modified coupling geometry. The removal and deposition areas are then further worked.

Description

Technisches GebietTechnical area

Die Erfindung betrifft ein Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln.The invention relates to a method for modifying the coupling geometry in shroud segments of turbine blades.

Stand der TechnikState of the art

Bei Turbinenstufen ist es bekannt, Turbinenlaufschaufeln mit einem Deckband auszustatten. Dabei ist die Deckband-Kopplung der nebeneinander liegenden Schaufeln oder Schaufelsegmente durch einen definierten Kopplungswinkel gekennzeichnet, der allerdings durch auf die Schaufeln wirkende Fliehkräfte, die Schaufelentwindung, die Deckbandstreckung, Temperatur des Arbeitsmediums, etc. beeinflusst wird. Durch den Kopplungswinkel und die Kopplungsfläche wiederum lassen sich die Spannungskräfte, die beim Abstützen der Schaufeln untereinander im Betrieb wirken, kontrollieren. Derartige Turbinenlaufschaufeln mit Deckbandsegment werden beispielsweise in den deutschen Patentschriften DE 36 20 162 C2 und DE 35 17 283 C2 beschrieben.In turbine stages, it is known to provide turbine blades with a shroud. The shroud coupling of the adjoining blades or blade segments is characterized by a defined coupling angle, which however is influenced by centrifugal forces acting on the blades, the blade entanglement, the shroud stretch, the temperature of the working medium, etc. The coupling angle and the coupling surface, in turn, make it possible to control the tension forces acting on one another during the support of the blades during operation. Such turbine blades with shroud segment are described for example in German patents DE 36 20 162 C2 and DE 35 17 283 C2.

Die Art der Kopplung, d.h. der Kopplungswinkel und die Kopplungsfläche, ist für das Betriebsverhalten der Turbinenlaufschaufeln, und hier insbesondere für das Verschleißverhalten im Bereich der Kopplung, wegen der Übertragung der Kopplungskräfte von wesentlicher Bedeutung. Aufgrund der o.g. Faktoren, die die Deckband-Kopplung beeinflussen, können schon geringe Änderungen am Turbinendesign einzelner Turbinenstufen, beispielsweise durch Umrüsten einer Turbinenstufe oder veränderte Betriebsbedingungen, zu unerwünscht hohem Verschleiß an bestehenden Turbinenstufen führen. Wird aufgrund von Betriebserfahrungen festgestellt, dass der Verschleiss im Kopplungsbereich zweier Turbinen-Deckbandsegmente unzulässig hoch ist, so erfolgt bisher lediglich eine Reparatur der Turbinenschaufel im Kopplungsbereich. Dabei wird der Kopplungsbereich in der Regel mit Chromcarbid beschichtet. Im Extremfall müssen einzelne Schaufeln oder Schaufelgruppen ausgetauscht werden. Ausserdem verkürzen sich in ungünstigen Fällen die Wartungsintervalle, was die Wirtschaftlichkeit der Anlage verringert.The type of coupling, ie the coupling angle and the coupling surface, is of essential importance for the performance of the turbine blades, and in particular for the wear behavior in the area of the coupling, because of the transmission of the coupling forces. Due to the og factors that affect the shroud coupling, even small changes in the turbine design of individual turbine stages, for example, by retooling a turbine stage or changed operating conditions, can lead to undesirably high wear on existing turbine stages. If it is determined on the basis of operating experience that the wear in the coupling region of two turbine shroud segments is impermissibly high, so far only a repair of the turbine blade in the coupling region takes place. The coupling region is usually coated with chromium carbide. In extreme cases, individual blades or blade groups must be replaced. In addition, reduce the maintenance intervals in unfavorable cases, which reduces the efficiency of the system.

US-4,291,448-A offenbart ein Verfahren zur Reparatur von verschliessenen Deckbandsegmenten durch Schleifen der betroffenen Zonen und Auftragen von zusätzlichem Material, um die originale Kopplungsgeometrie wieder zu erhalten.US-4,291,448-A discloses a method of repairing closed shroud segments by grinding the affected zones and applying additional material to restore the original coupling geometry.

Darstellung der ErfindungPresentation of the invention

Der Erfindung liegt daher die Aufgabe zugrunde, die obengenannten Nachteile des Standes der Technik zu vermeiden und ein Verfahren zum Modifizieren des Kopplungswinkels bei Deckbandsegmenten von Turbinenlaufschaufeln zur Verfügung zu stellen, welches das Verschleißverhalten im Kopplungsbereich verbessert und die Lebensdauer der Deckbandsegmente von Turbinenlaufschaufeln auf wirkungsvolle und kostengünstige Weise verlängert. Die Modifikation soll dabei entweder an bestehenden Turbinenlaufschaufeln durchführbar sein oder aber an Neuteilen, die gegen Turbinenlaufschaufeln austauschbar sind, die das Ende ihrer Lebensdauer erreicht haben.The invention is therefore based on the object to avoid the above-mentioned disadvantages of the prior art and to provide a method for modifying the coupling angle in shroud segments of turbine blades, which improves the wear behavior in the coupling region and the life of the shroud segments of turbine blades on effective and cost-effective Way extended. The modification should be carried out either on existing turbine blades or on new parts that are interchangeable with turbine blades that have reached the end of their life.

Diese Aufgabe wird durch das Verfahren nach Anspruch 1 gelöst. Weitere vorteilhafte Ausgestaltungen und Weiterbildungen sind in den Unteransprüchen angegeben.This object is achieved by the method according to claim 1. Further advantageous embodiments and further developments are specified in the subclaims.

Das erfindungsgemäße Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln weist dabei folgende Schritte auf: Berechnen einer modifizierten Kopplungsgeometrie. Hier kommen beispielsweise Simulationen zur Anwendungen, in denen die veränderten Strömungsbedingungen in einer modernisierten Turbomaschine und deren Auswirkungen auf die betreffende Turbinenstufe analysiert werden können. Abtragen von außerhalb der modifizierten Kopplungsgeometrie gelegenen Deckbandmaterial; und/oder Auftragen von zusätzlichem, nicht innerhalb der modifizierten Kopplungsgeometrie vorhandenen Materials; Nachbearbeiten der Abtrags- und/oder Auftragszonen. Eine Nachbearbeitung kann insbesondere nach Materialauftrag notwendig sein, da hierdurch die gewünschte Oberflächengüte erzielbar ist. Auf diese Weise kann beispielsweise der Kopplungswinkel und die Kopplungsfläche oder aber nur der Kopplungswinkel oder nur die Kopplungsfläche variiert werden.The method according to the invention for modifying the coupling geometry for shroud segments of turbine blades has the following steps: calculating a modified coupling geometry. Here, for example, simulations are used for applications in which the changed flow conditions in a modernized turbomachine and their effects on the relevant turbine stage can be analyzed. Removal of shroud material outside the modified coupling geometry; and / or applying additional material not present within the modified coupling geometry; Post-processing of the removal and / or order zones. Post-processing may be necessary, in particular after the application of material, since in this way the desired surface quality can be achieved. In this way, for example, the coupling angle and the coupling surface or only the coupling angle or only the coupling surface can be varied.

Durch das erfindungsgemäße Verfahren werden die Nachteile des Standes der Technik vermieden und das Verschleißverhalten im Kopplungsbereich verbessert. Ferner wird die Lebensdauer der Turbinenschaufeln auf wirkungsvolle und kostengünstige Weise verlängert.By the method according to the invention, the disadvantages of the prior art are avoided and the wear behavior in the coupling region is improved. Furthermore, the life of the turbine blades is extended in an effective and cost effective manner.

Eine vorteilhafte Weiterbildung des erfindungsgemäßen Verfahrens sieht vor, dass die Auftragszonen vorab derart bearbeitet werden, dass ein verbesserter Auftragsquerschnitt zur Verfügung gestellt wird. Dies geschieht beispielsweise durch Materialabtrag an einer stelle des Deckbandsegments, das einen ausreichend grossen Querschnitt bietet um Auftragsmaterial damit sicher und zuverlässig zu verbinden. Ausserdem können hierdurch auch Winkelquerschnitte definiert werden, die aus herstellungstechnischen Gründen vorteilhaft sind, da das Auftragsmaterial an mehreren Seiten mit dem original Deckbandsegment verbunden ist.An advantageous development of the method according to the invention provides that the application zones are previously processed in such a way that an improved order cross-section is provided. This is done, for example, by removing material at a point of the shroud segment, which provides a sufficiently large cross-section to order material safely and reliably connect. In addition, this also angular cross-sections can be defined, which are advantageous for manufacturing reasons, since the application material is connected on several sides with the original shroud segment.

Eine vorteilhafte Ausführungsform des erfindungsgemäßen Verfahrens sieht ferner vor, dass die modifizierte Kopplungsgeometrie eine Änderung des Kopplungswinkels um zumindest ±5°, vorzugsweise ±15° bis ±40° vorsieht. Dabei sind die Winkelangaben von der Umfangsrichtung aus gemessen. Es gilt, dass bei zu kleinen übertragenen Kopplungskräften eine Vergrösserung des Kopplungswinkels angestrebt wird. Umgekehrt wird bei zu grossen Übertragungskräften eine Verkleinerung des Kopplungswinkels angestrebt.An advantageous embodiment of the method according to the invention further provides that the modified coupling geometry provides for a change in the coupling angle by at least ± 5 °, preferably ± 15 ° to ± 40 °. The angle data are measured from the circumferential direction. It is important that an increase in the coupling angle is aimed for when the coupling forces transmitted are too small. Conversely, if transmission forces are too great, the aim is to reduce the coupling angle.

Ferner sieht eine besonders vorteilhafte Weiterbildung des Verfahrens vor, dass die Änderung des Kopplungswinkels ± 25° beträgt. Dieser Winkel hat sich beispielsweise in Versuchen als vorteilhaft zur Änderung von Kopplungswinkeln von 15° auf 40° erwiesen.Furthermore, a particularly advantageous embodiment of the method provides that the change in the coupling angle is ± 25 °. This angle has proved to be advantageous, for example, in experiments for changing coupling angles from 15 ° to 40 °.

Noch eine vorteilhafte Ausführungsform des erfindungsgemäßen Verfahrens sieht vor, dass das Auftragen von zusätzlichem Material mittels Auftragsschweissen erfolgt. Hier hat sich beispielsweise das Auftragsschweissen mittels Laser bewährt.Yet another advantageous embodiment of the method according to the invention provides that the application of additional material takes place by means of build-up welding. Here, for example, the deposition welding has proven by laser.

Noch eine vorteilhafte Ausführungsform des erfindungsgemäßen Verfahrens sieht vor, dass das Abtragen von überschüssigem Material mittels Schleifen erfolgt. Sofern grössere Segmente abgetrennt werden sollen, kann hier beispielsweise ein Trennschleifer zur Anwendung kommen.Yet another advantageous embodiment of the method according to the invention provides that the removal of excess material takes place by means of grinding. If larger segments are to be separated, a cut-off grinder, for example, can be used here.

Ein weiteres erfindungsgemässes Verfahren zum Modifizieren einer bestehenden Gussform für eine Turbinenlaufschaufel mit Deckbandsegment, für eine geänderte Geometrie des Kopplungswinkels, weist folgende Schritte auf: Berechnen einer modifizierten Kopplungsgeometrie; Abtragen von innerhalb der modifizierten Kopplungsgeometrie gelegenen Gussformmaterial; und/oder Auftragen von zusätzlichem, nicht vorhandenen Gussformmaterial ausserhalb der modifizierten Kopplungsgeometrie; Nachbearbeiten der Abtrags- und/oder Auftragszonen. Im wesentlichen handelt es sich bei diesen Modifikationen um die umgekehrten Schritte, wie bei dem erfindungsgemäßen Verfahren nach Patentanspruch 1, da es sich hier um eine Negativform handelt. Eine derartige Modifikation von bereits bestehenden Gussformen ist hilfreich, wenn Ersatz-Turbinenschaufeln hergestellt werden sollen, die andernfalls nachträglich modifiziert werden müssten. Hierdurch wird eine kostengünstige Möglichkeit zur weiteren Nutzung bereits bestehender Gussformen vorgestellt, ohne auf die Vorteile der modifizierten Kopplungsgeometrie verzichten zu müssen.A further method according to the invention for modifying an existing casting mold for a turbine blade with a shroud segment, for a modified geometry of the coupling angle, comprises the following steps: calculating a modified coupling geometry; Removal of mold material located within the modified coupling geometry; and / or applying additional, nonexistent Mold material outside the modified coupling geometry; Post-processing of the removal and / or order zones. Essentially, these modifications are the reverse steps, as in the inventive method according to claim 1, since this is a negative mold. Such modification of existing molds is helpful in making replacement turbine blades that would otherwise need to be subsequently modified. As a result, a cost-effective option for further use of existing molds is presented, without having to sacrifice the benefits of the modified coupling geometry.

Eine vorteilhafte Ausführungsform des erfindungsgemäßen Verfahrens sieht vor, dass die modifizierte Kopplungsgeometrie eine Änderung des Kopplungswinkels um zumindest ±5°, vorzugsweise ±15° bis ±40° aufweist. Besonders vorteilhaft ist es, wenn die Änderung des Kopplungswinkels ±25° beträgt.An advantageous embodiment of the method according to the invention provides that the modified coupling geometry has a change in the coupling angle by at least ± 5 °, preferably ± 15 ° to ± 40 °. It is particularly advantageous if the change in the coupling angle is ± 25 °.

Dabei kann in vorteilhafter Weise auch hier das Auftragen von zusätzlichem Material mittels Auftragsschweissen und das Abtragen von überschüssigem Material mittels Schleifen erfolgen.In this case, the application of additional material by means of build-up welding and the removal of excess material by means of grinding can be carried out in an advantageous manner here as well.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Im folgenden ist eine vorteilhafte Ausführungsform der Erfindung in Verbindung mit den beigefügten Zeichnungen beschrieben. Darin zeigen:

Figur 1
eine perspektivische Ansicht einer Turbinenlaufschaufel mit Deckbandsegment;
Figur 2
eine schematische Detailansicht II des Deckbandsegments aus Figur 1;
Figur 3a, 3b
eine schematische Draufsicht auf den Kopplungsbereich des Deckbandsegments von Druck- und Saugseite ohne Modifikation;
Figur 4a, 4b
eine schematische Draufsicht auf den Kopplungsbereich des Deckbandsegments von Druck- und Saugseite mit Modifikation.
In the following an advantageous embodiment of the invention will be described in conjunction with the accompanying drawings. Show:
FIG. 1
a perspective view of a turbine blade with shroud segment;
FIG. 2
a schematic detail view II of the shroud segment of Figure 1;
Figure 3a, 3b
a schematic plan view of the coupling region of the shroud segment of pressure and suction side without modification;
Figure 4a, 4b
a schematic plan view of the coupling region of the shroud segment of the pressure and suction side with modification.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. In der nachfolgenden Beschreibung sind gleiche oder ähnliche Teile mit gleichen Bezugszeichen gekennzeichnet.Only the elements essential to the understanding of the invention are shown. In the following description, the same or similar parts are identified by the same reference numerals.

Wege zur Ausführung der ErfindungWays to carry out the invention

Figur 1 zeigt eine perspektivische Ansicht eines Gittermodells einer Turbinenlaufschaufel 1 mit einem Deckbandsegment 7. Die Turbinenlaufschaufel 1 weist an ihrem oberen Ende einen Schaufelkopf 2 und an ihrem unteren Ende einen Schaufelfuss 3 auf, der sich in einem Schaft 4 fortsetzt (nur angedeutet). In der linken Zeichnungsseite ist die Schaufelprofil-Vorderkante 5 und auf der rechten Zeichnungsseite die Schaufelprofil-Hinterkante 6 gezeigt.1 shows a perspective view of a grid model of a turbine blade 1 with a shroud segment 7. The turbine blade 1 has at its upper end a blade head 2 and at its lower end a blade root 3, which continues in a shaft 4 (only indicated). In the left side of the drawing, the blade profile leading edge 5 and on the right side of the drawing the blade profile trailing edge 6 is shown.

Wie insbesondere in Figur 2 der Darstellung des Details II aus Figur 1 entnommen werden kann, verläuft das Deckbandsegment 7 am Schaufelkopf 2 im wesentlichen quer zur zwischen der Schaufelprofil-Vorderkante 5 und der Schaufelprofil-Hinterkante 6 verlaufenden Profilsehne und parallel zur Umfangsrichtung U. Das Deckbandsegment 7 erstreckt sich dabei nicht über die gesamte Schaufeltiefe, sondern lediglich auf einen Bereich in der Schaufelmitte. Der Übergang zwischen dem Deckbandsegment 7 und dem Schaufelkopf 2 wird durch Übergangsradien bestimmt. Ferner sind an den Seitenflächen des Deckbandsegments 7 Kontaktflächen 8, 9 vorgesehen, die während des Betriebs an Kontaktflächen benachbarter Deckbandsegmente anliegen.As can be seen in particular in FIG. 2 of the illustration of detail II from FIG. 1, the shroud segment 7 extends essentially transversely to the blade chord 2 extending between the blade profile leading edge 5 and the blade profile trailing edge 6 and parallel to the circumferential direction U. The shroud segment 7 does not extend beyond the entire blade depth, but only on an area in the blade center. The transition between the shroud segment 7 and the blade head 2 is determined by transition radii. Furthermore, 7 contact surfaces 8, 9 are provided on the side surfaces of the shroud segment, which abut against contact surfaces of adjacent shroud segments during operation.

Figuren 3a und 3b zeigen eine schematische Draufsicht auf den Kopplungsbereich von Deckbandsegmenten 7 von Druckseite und Saugseite ohne Modifikation.Figures 3a and 3b show a schematic plan view of the coupling region of shroud segments 7 from the pressure side and suction side without modification.

Das in Figur 3a dargestellte druckseitige Ende des Deckbandsegments 7 zeigt etwa mittig angeordnet eine Finne 11, die als Dichtsteg zwischen der Gehäuseinnenwand des Turbinengehäuses und dem aus den Deckbandsegmenten 7 aufgebauten Turbinendeckband dient. Die Kontaktfläche 8 des Deckbandsegments 7, die der gegenseitigen Abstützung von benachbarten Turbinenlaufschaufeln dient, weist dabei im vorliegenden Ausführungsbeispiel vor der Modifikation einen Winkel von 15° gemessen von der Umfangsrichtung auf. Ferner ist deutlich der gestufte bzw. Z-förmige Seitenrand des Deckbandsegments ohne Modifikation erkennbar.The pressure-side end of the shroud segment 7 shown in FIG. 3 a shows approximately centrally a fin 11 which serves as a sealing web between the housing inner wall of the turbine housing and the turbine shroud constructed from the shroud segments 7. The contact surface 8 of the shroud segment 7, which serves the mutual support of adjacent turbine blades, has in the present embodiment, prior to the modification at an angle of 15 ° measured from the circumferential direction. Furthermore, the stepped or Z-shaped side edge of the shroud segment can be clearly seen without modification.

Das in Figur 3b dargestellte saugseitige Ende des Deckbandsegments 7 zeigt ebenfalls eine etwa mittig angeordnet Finne 11. Die Kontaktfläche 9, die quasi die lange Verbindungslinie zwischen dem oberen und dem unteren horizontalen Z-Balken bildet, weist auch am saugseitigen Deckbandsegment 7 einen Winkel von 15°, gemessen von der Umfangsrichtung, auf.The suction-side end of the shroud segment 7 shown in FIG. 3b likewise has an approximately centrally arranged fin 11. The contact surface 9, which virtually forms the long connecting line between the upper and lower horizontal Z beams, also has an angle of 15 on the suction-side shroud segment 7 °, measured from the circumferential direction, on.

Der im vorliegenden Ausführungsbeispiel errechnete optimale Winkel für die modifizierten druckseitigen und saugseitigen Kontaktflächen beträgt jeweils 40° von der Umfangsrichtung gemessen. Die gewünschte Winkeländerung beträgt somit jeweils 25°. Zur Änderung der Kopplungsgeometrie muss an einigen Stellen Material abgetragen werden und an anderen Stellen Material hinzugefügt werden.The calculated in the present embodiment optimum angle for the modified pressure-side and suction-side contact surfaces is measured at 40 ° from the circumferential direction. The desired angle change is thus 25 ° each. To change the coupling geometry, material has to be removed in some places and material has to be added elsewhere.

Zum Auftragen von zusätzlichem Material werden die entsprechenden Deckbandabschnitte so vorbereitet, dass durch vorherigen Materialabtrag ein optimaler Querschnitt zum Auftragen von neuem Deckbandmaterial zur Verfügung gestellt wird. Diese Vorbereitungsflächen sind in Figuren 3a und 3b durch gestrichelte Linien und die Aussenkontur begrenzt und mit Bezugsziffer 10 gekennzeichnet. Im vorliegenden Ausführungsbeispiel erfolgt dabei der Materialabtrag durch ein Schleifverfahren. Grundsätzlich ist aber jedes andere geeignete Abtragsverfahren möglich.For the application of additional material, the corresponding shroud sections are prepared so that an optimal cross-section for the application of new shroud material is provided by previous material removal. These preparation surfaces are limited in Figures 3a and 3b by dashed lines and the outer contour and identified by reference numeral 10. In the present embodiment, the removal of material takes place by a grinding process. In principle, however, any other suitable removal method is possible.

Figuren 4a und 4b zeigen eine schematische Draufsicht auf den Kopplungsbereich der Deckbandsegmente 7 von Druck- und Saugseite mit modifizierter Kopplungsgeometrie. Auch hier sind die Finnen 11 dargestellt, die parallel zur durch Pfeil U dargestellten Umfangsrichtung verlaufen. Die Kontaktflächen 8, 9 verlaufen dabei unter einem Winkel von 40°, gemessen von der Umfangsrichtung.Figures 4a and 4b show a schematic plan view of the coupling region of the shroud segments 7 of the pressure and suction side with modified coupling geometry. Again, the fins 11 are shown, which are parallel to the circumferential direction shown by arrow U. The contact surfaces 8, 9 extend at an angle of 40 °, measured from the circumferential direction.

In den Figuren 4a und 4b sind die Auftragsflächen 13, in denen zusätzliches Deckbandmaterial aufgetragen wurde, innerhalb der Deckbandkontur gestrichelt dargestellt. Die Abtragsflächen 12, d.h. Zonen in denen überschüssiges Deckbandmaterial entfernt wurde, sind ausserhalb der Deckbandkontur mit gestrichelten Linien begrenzt. In Figur 4b ist anschaulich die durch den Materialabtrag und das Materialauftragen hervorgerufene Winkeländerung von 15° auf 40° dargestellt.In the figures 4a and 4b, the application surfaces 13, in which additional shroud material has been applied, shown in dashed lines within the shroud contour. The removal surfaces 12, i. Zones in which excess shroud material has been removed are bounded by dashed lines outside the shroud contour. FIG. 4b clearly shows the angle change from 15 ° to 40 ° caused by the removal of material and the application of material.

Ferner ist in den Figuren 4a und 4b die Änderung der Kontur von einer ursprünglich Z-förmigen Kontur in einen im wesentlichen diagonal verlaufenden Kopplungsbereich mit abgerundetem Endbereich zu erkennen. Hierdurch werden die Verschleisseigenschaften verbessert und die Lebensdauer des Deckbandsegments erheblich verlängert.Further, in Figures 4a and 4b, the change in contour from an initial Z-shaped contour to a substantially diagonal Recognizing coupling region with rounded end. As a result, the wear properties are improved and the life of the shroud segment significantly extended.

Im vorliegenden Ausführungsbeispiel ist der Materialabtrag mittels Trennschleifen und der Materialauftrag mittels Auftragsschweissen, hier im WIG-Schweissverfahren, erfolgt. Grundsätzlich ist aber jedes geeignete Auftrags- und Abtragsverfahren verwendbar.In the present embodiment, the removal of material by means of cut-off grinding and the material application by means of build-up welding, here in the TIG welding process, is carried out. In principle, however, any suitable order and removal method can be used.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
TurbinenlaufschaufelTurbine blade
22
Schaufelkopfshovel head
33
Schaufelfussblade root
44
Schaftshaft
55
Schaufelprofil-VorderkanteAirfoil leading edge
66
Schaufelprofil-HinterkanteAirfoil trailing edge
77
DeckbandsegmentShroud segment
88th
Kontaktfläche DruckseiteContact surface pressure side
99
Kontaktfläche SaugseiteContact surface suction side
1010
Vorbereitungsflächepreparation surface
1111
Finnefin
1212
Abtragsflächecut area
1313
Auftragsflächeapplication surface
UU
Umfangsrichtungcircumferentially

Claims (11)

  1. Method of modifying the coupling geometry in shroud band segments (7) of turbine moving blades (1), the method having the following steps:
    - calculation of a modified coupling geometry;
    - removal of shroud band material (12) situated outside the modified coupling geometry; and/or
    - application of additional material (13) not present inside the modified coupling geometry;
    - reworking the removal and/or application zones.
  2. Method according to patent Claim 1, the application zones being premachined in such a way that an improved application cross section is made available.
  3. Method according to patent Claim 1 or 2, the modified coupling geometry having a change in the coupling angle of at least ±5°, preferably ±15° to ±40°.
  4. Method according to patent Claim 3, the change in the coupling angle being ±25°.
  5. Method according to one of the preceding patent claims, the application of additional material being effected by means of deposition welding.
  6. Method according to one of the preceding patent claims, the removal of excess material being effected by means of grinding.
  7. Method of modifying an existing casting mould for a turbine moving blade having a shroud band segment, for a changed geometry of the coupling angle, the method having the following steps:
    - calculation of a modified coupling geometry;
    - removal of casting mould material situated inside the modified coupling geometry; and/or
    - application of additional casting mould material, which is not present, outside the modified coupling geometry;
    - reworking the removal and/or application zones.
  8. Method according to patent Claim 7, the modified coupling geometry having a change in the coupling angle of at least ±5°, preferably ±15° to ±40°.
  9. Method according to patent Claim 8, the change in the coupling angle being ±25°.
  10. Method according to one of patent Claims 7 to 9, the application of additional material being effected by means of deposition welding.
  11. Method according to one of patent Claims 7 to 10, the removal of excess material being effected by means of grinding.
EP04102733A 2003-06-23 2004-06-15 Method of modifying the coupling geometry in shroud band segments of turbine blades Expired - Lifetime EP1491723B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10328310A DE10328310A1 (en) 2003-06-23 2003-06-23 Method of modifying the coupling geometry of shroud segments of turbine blades
DE10328310 2003-06-23

Publications (3)

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EP1491723A1 EP1491723A1 (en) 2004-12-29
EP1491723B1 true EP1491723B1 (en) 2006-08-23
EP1491723B2 EP1491723B2 (en) 2009-05-06

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US (2) US7644498B2 (en)
EP (1) EP1491723B2 (en)
AT (1) ATE337470T1 (en)
DE (2) DE10328310A1 (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699984A1 (en) * 2008-11-27 2010-05-31 Alstom Technology Ltd Method for optimizing the contact surfaces of abutting shroud segments adjacent blades of a gas turbine.
US9151166B2 (en) 2010-06-07 2015-10-06 Rolls-Royce North American Technologies, Inc. Composite gas turbine engine component
US20140147283A1 (en) * 2012-11-27 2014-05-29 General Electric Company Method for modifying a airfoil shroud and airfoil
US20140147284A1 (en) * 2012-11-27 2014-05-29 General Electric Company Method for modifying an airfoil shroud
US10465531B2 (en) * 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
JP6142008B2 (en) 2013-03-15 2017-06-07 インテル コーポレイション Mobile computing device technology and systems and methods using the same
US9091277B1 (en) 2014-04-25 2015-07-28 Computer Assisted Manufacturing Technology Corporation Systems and methods for manufacturing a shrouded impeller
EP3029267A1 (en) * 2014-12-04 2016-06-08 Siemens Aktiengesellschaft Method of manufacturing a vibration damper for a turbine blade by laser build-up welding
CN106475733B (en) * 2016-10-11 2018-11-13 吉林大学 A kind of subregion structure bionic coupling surface reconditioning Waste machine tool guide rail and its method
CA3065099C (en) 2017-04-28 2023-01-03 Fluid Handling Llc Technique to improve the performance of a pump with a trimmed impeller using additive manufacturing
DE102018201265A1 (en) 2018-01-29 2019-08-01 MTU Aero Engines AG Shroud segment for placement on a blade of a turbomachine and blade

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4291448A (en) * 1977-12-12 1981-09-29 Turbine Components Corporation Method of restoring the shrouds of turbine blades
US4400915A (en) † 1980-06-02 1983-08-30 United Technologies Corporation Fixture for restoring a face on the shroud of a rotor blade
US4589175A (en) † 1980-06-02 1986-05-20 United Technologies Corporation Method for restoring a face on the shroud of a rotor blade
DE3517283A1 (en) 1985-05-14 1986-11-20 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen BINDING BLADES OF A THERMAL TURBO MACHINE
US4657171A (en) † 1985-06-13 1987-04-14 General Electric Company Repair of a member having a projection
CH666722A5 (en) * 1985-07-05 1988-08-15 Bbc Brown Boveri & Cie Vane ring of an axially flowed turbo machine.
US4822248A (en) * 1987-04-15 1989-04-18 Metallurgical Industries, Inc. Rebuilt shrouded turbine blade and method of rebuilding the same
EP0290773B1 (en) * 1987-05-04 1991-05-22 Siemens Aktiengesellschaft Method for manufacturing sections by grinding, and turbine blades so manufactured
US4893388A (en) † 1988-12-08 1990-01-16 Westinghouse Electric Corp. Method of modifying turbine rotor discs
EP0389913B1 (en) 1989-03-28 1998-06-17 Refurbished Turbine Components Limited Turbine blade repair
JP3034417B2 (en) * 1994-02-18 2000-04-17 株式会社東芝 Rotor blade control device for axial flow turbine
AUPO879497A0 (en) * 1997-08-26 1997-09-18 Warman International Limited Pump impeller and method
US6464128B1 (en) * 1999-05-28 2002-10-15 General Electric Company Braze repair of a gas turbine engine stationary shroud
US6701616B2 (en) * 2002-06-28 2004-03-09 General Electric Company Method of repairing shroud tip overlap on turbine buckets

Also Published As

Publication number Publication date
EP1491723A1 (en) 2004-12-29
US8006381B2 (en) 2011-08-30
US20050097741A1 (en) 2005-05-12
ATE337470T1 (en) 2006-09-15
US20100077586A1 (en) 2010-04-01
US7644498B2 (en) 2010-01-12
DE10328310A1 (en) 2005-01-13
EP1491723B2 (en) 2009-05-06
DE502004001246D1 (en) 2006-10-05

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