EP2045444A1 - Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade - Google Patents

Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade Download PDF

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Publication number
EP2045444A1
EP2045444A1 EP08165091A EP08165091A EP2045444A1 EP 2045444 A1 EP2045444 A1 EP 2045444A1 EP 08165091 A EP08165091 A EP 08165091A EP 08165091 A EP08165091 A EP 08165091A EP 2045444 A1 EP2045444 A1 EP 2045444A1
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EP
European Patent Office
Prior art keywords
blade
undercut
blade root
root
intermediate pieces
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.)
Granted
Application number
EP08165091A
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German (de)
French (fr)
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EP2045444B1 (en
Inventor
Thomas Müller
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP2045444A1 publication Critical patent/EP2045444A1/en
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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
    • F01D5/30—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • Y10T409/00—Gear cutting, milling, or planing
    • Y10T409/30—Milling
    • Y10T409/303752—Process

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a blade for attachment to the rotor of a turbomachine, a method for manufacturing a blade, and a compressor with such a blade.
  • the buckets of a compressor are part of an axial compressor system that moves and compresses large quantities of air needed for the proper and safe operation of a gas turbine system.
  • the blades are on the outer circumference of the rotor of the Compressor mounted and are exposed to a variety of mechanical loads, which are particularly based on the type of blade attachment.
  • a rotor blade 13 or 27 is respectively arranged, which comprises an airfoil 14 and with a downwardly adjoining the airfoil 14 T-shaped blade root 15 and 25 (see Fig. 6 ) abuts the side surfaces of the adjacent intermediate pieces 12, 18 and engages with circumferentially protruding projections 16, 16 'and 26, 26' under the adjacent intermediate pieces 12, 18.
  • the intermediate pieces 12, 18 and the blades 13 and 27 are arranged obliquely to the rotor axis A2 standing, so that the blade axis (A1 in Fig. 5 ) with the rotor axis A2 an angle of for example 25 ° includes (see Fig. 5 ).
  • the T-shaped blade roots 25 of the compressor blades 27 have been forged (forged) by upset forging so as to obtain a strength-determining grain structure as shown in FIG Fig. 6 is indicated by the dashed lines.
  • the idea was not to forge the blade roots, but to make them by milling (grain structure in Fig. 4 ).
  • the forging radius 29 is approximately in the range between 0.5 and 1.0 mm (FIG. Fig. 6 ). Due to the notch factor, milled blade feet at the transitions require a radius that is about 1.5 to 2 times greater than the forging radius 29.
  • bulging 31 causes bulges 31 on the shaft above the projections 26, 26 '(in FIG Fig. 6 this is indicated by the dotted lines), which are in the range of 0.3 to 0.5 mm.
  • bulging 31 causes bulges 31 on the shaft above the projections 26, 26 '(in FIG Fig. 6 this is indicated by the dotted lines), which are in the range of 0.3 to 0.5 mm.
  • the object is solved by the entirety of the features of claims 1 and 8.
  • Essential for the invention is that the T-shaped blade root is milled, and that in order to reduce the mechanical stresses at the transitions of the blade root to the projections in each case an axially extending undercut is provided.
  • the compressor according to the invention has a rotor which is equipped with blades according to the invention.
  • the undercut can be a standard undercut to ISO standard.
  • the undercut is then an undercut type E or F according to DIN standard 506.
  • the spacers each have a chamfer at their adjoining the blade root side surfaces
  • the undercut has a deviating from a standard undercut to ISO standard, increased height, which the bevel exploits.
  • the height of the undercut can correspond approximately to the height of the bevel.
  • the undercut has a radius that is 1.5-2 times the radius of a comparable upset formed blade root.
  • the radius is 1.5 mm with a compression radius of 0.8, or 1.75 mm with a compression radius of 1.0.
  • the undercut follows an elliptical curve in the direction of the blade axis.
  • a preferred embodiment of the method according to the invention is characterized in that the undercuts are milled in the direction of the blade axis along an elliptical processing path.
  • Machining becomes particularly easy if a milling tool deviating from the spherical shape is used to mill the undercuts.
  • undercut which is preferably realized taking into account the lateral bevels formed on the intermediate pieces.
  • undercuts are first undercuts according to ISO standard in question, which are listed under the DIN standard 509 as undercuts form E and F.
  • the undercut of type E only cuts into one of the two adjoining surfaces that are perpendicular to each other, while the undercut of type F cuts into both surfaces.
  • Both undercut types have special outlet areas (32, 33 in Fig. 3 ), which serve the additional stress relief in the radius.
  • the blades with forged blade root can be replaced by the cheaper blades with milled blade root without losses in the Lifetime must be accepted.
  • the adjacent intermediate pieces 12, 18 need not be changed or additionally processed.
  • the contact surface between the blade root (15 in Fig. 3 ) and the adjacent intermediate pieces 12 and 18 is limited by the chamfers 17 and 19 on the side surfaces of the intermediate pieces 12, 18, but also determined, so that the type of undercut 21 within the region of the chamfers 17, 19 has no influence on the contact surface ( Fig. 3 ). Accordingly, the blades are always held in the same way between the intermediate pieces 12, 18, regardless of whether the blade root is forged ( Fig. 6 ) or milled ( Fig. 4 ). It also follows that the natural frequencies (resonances) of the blades do not change, so that there is complete interchangeability between the differently manufactured blades.
  • a standard undercut type F cuts - as already mentioned above - in both adjacent vertical surfaces in the corners of the projections 16, 16 'of the blade root 15 ( Fig. 4a ). This is the only way to achieve the increased radius for the desired equal or longer life over forged blade roots.
  • a standard F-cut can only be produced by means of a milling process if the undercut is simultaneously moved in the direction of the blade axis A1 along an elliptical processing path (23 in FIG Fig. 5 ).
  • the undercut can only be milled with a great deal of effort, since this is what the in Fig. 4a shown small milling tool 28 with a spherical milling head (head diameter (2 x radius R2): 2-3 mm, shank diameter: 1.5-2 mm) must be used.
  • modified undercut 21 used, which is characterized by an increased height h in the direction of the longitudinal axis of the blade.
  • the height h of the undercut 21 may correspond to the entire length of the chamfer 17, 19 on the side surfaces of the intermediate pieces 12, 18.
  • the increase in the height h compared to the standard undercut 30 makes it possible, according to Fig. 4 to use a larger milling tool 22 with a radius R1> R2 (R1 is eg 1.75 mm), which significantly reduces costs and processing times (dashed hatch in Fig. 4 indicates that the blade root 15 is milled and not forged).

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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)

Abstract

A blade root (15,25) adjoins the lower end of the blade airfoil (14), extends along a blade axis and is retained between two spacers (12). The blade root has a T-shaped cross-section and circumferentially extending shoulders (16,26). The shoulders fit under adjacent spacers. The T-shaped blade root is formed by milling. A relief groove at transitions of the blade root to the shoulders extends in the direction of the blade axis to reduce mechanical stresses.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Turbomaschinen. Sie betrifft eine Laufschaufel zur Befestigung am Rotor einer Turbomaschine, ein Verfahren zur Herstellung einer Laufschaufel, sowie einen Verdichter mit einer solchen Laufschaufel.The present invention relates to the field of turbomachinery. It relates to a blade for attachment to the rotor of a turbomachine, a method for manufacturing a blade, and a compressor with such a blade.

STAND DER TECHNIKSTATE OF THE ART

Die Laufschaufeln eines Verdichters sind Teil eines axialen Verdichtersystems, das grosse Mengen von Luft bewegt und komprimiert, die zum ordnungsgemässen und sicheren Betrieb eines Gasturbinensystems benötigt werden. Die Laufschaufeln sind auf dem Aussenumfang des Rotors des Verdichters montiert und sind einer Vielzahl von mechanischen Belastungen ausgesetzt, die sich insbesondere auch nach der Art der Schaufelbefestigung richten.The buckets of a compressor are part of an axial compressor system that moves and compresses large quantities of air needed for the proper and safe operation of a gas turbine system. The blades are on the outer circumference of the rotor of the Compressor mounted and are exposed to a variety of mechanical loads, which are particularly based on the type of blade attachment.

Um die für das System katastrophale Ablösung einer Laufschaufel vom Rotor sicher zu vermeiden, sind in der Vergangenheit unterschiedliche Systeme zur Befestigung der Laufschaufeln am Rotor entwickelt und vorgeschlagen worden. Eines dieser Systeme, auf welches sich die vorliegende Erfindung bezieht, ist das Befestigungssystem mit einem T-förmigen Schaufelfuss und Zwischenstücken, wie es in den Fig. 1 und 2 bzw. in Fig. 6 im Ausschnitt vereinfacht wiedergegeben ist, und dass seit langem beispielsweise aus der Druckschrift DE-PS-318 662 bekannt ist.In order to safely avoid the systematically disassembling a blade from the rotor, various systems for mounting the blades to the rotor have been developed and proposed in the past. One of these systems to which the present invention relates is the fastening system with a T-shaped blade root and spacers as shown in FIGS Fig. 1 and 2 or in Fig. 6 simplified in the cutout is reproduced, and that for a long time, for example, from the document DE-PS-318 662 is known.

Bei diesem System sind in einer um die Rotorachse (A2 in Fig. 5) des Rotors 10 umlaufenden Nut 11 in Umfangsrichtung hintereinander Zwischenstücke 12, 18 eingesetzt und mittels an Hinterschneidungen 24 anliegenden Halteflächen 20 in der Nut 11 gehalten. Zwischen zwei benachbarten Zwischenstücken 12, 18 ist jeweils eine Laufschaufel 13 bzw. 27 angeordnet, die ein Schaufelblatt 14 umfasst und mit einem nach unten an das Schaufelblatt 14 anschliessenden T-förmigen Schaufelfuss 15 bzw. 25 (siehe Fig. 6) an die Seitenflächen der angrenzenden Zwischenstücke 12, 18 anstösst und mit in Umfangsrichtung herausstehenden Vorsprüngen 16, 16' bzw. 26, 26' unter die benachbarten Zwischenstücke 12, 18 greift. Die Zwischenstücke 12, 18 und die Laufschaufeln 13 bzw. 27 sind dabei schräg zur Rotorachse A2 stehend angeordnet, so dass die Schaufelachse (A1 in Fig. 5) mit der Rotorachse A2 einen Winkel von beispielsweise 25° einschliesst (siehe Fig. 5).In this system, in one around the rotor axis (A2 in Fig. 5 ) of the rotor 10 circumferential groove 11 in the circumferential direction one behind the other intermediate pieces 12, 18 and held by means resting against undercuts 24 holding surfaces 20 in the groove 11. Between two adjacent intermediate pieces 12, 18, a rotor blade 13 or 27 is respectively arranged, which comprises an airfoil 14 and with a downwardly adjoining the airfoil 14 T-shaped blade root 15 and 25 (see Fig. 6 ) abuts the side surfaces of the adjacent intermediate pieces 12, 18 and engages with circumferentially protruding projections 16, 16 'and 26, 26' under the adjacent intermediate pieces 12, 18. The intermediate pieces 12, 18 and the blades 13 and 27 are arranged obliquely to the rotor axis A2 standing, so that the blade axis (A1 in Fig. 5 ) with the rotor axis A2 an angle of for example 25 ° includes (see Fig. 5 ).

Bisher sind die T-förmigen Schaufelfüsse 25 der Verdichter-Laufschaufeln 27 durch Stauchschmieden geformt (geschmiedet) worden und haben so eine die Festigkeit bestimmende Kornstruktur erhalten, wie sie in Fig. 6 durch die gestrichelten Linien angedeutet ist. Neuerdings wird - bedingt durch neue Anforderungen hinsichtlich Kosten, Werkzeug und Logistik - zunehmend dazu übergegangen, die Schaufelfüsse nicht mehr zu schmieden, sondern durch Fräsen herzustellen (Kornstruktur in Fig. 4). Um bei den gefrästen Schaufelfüssen an den kritischen Übergängen zu den Vorsprüngen 16, 16' bzw. 26, 26' dieselbe oder eine bessere Festigkeit zu erreichen, wie bei den geschmiedeten Schaufelfüssen, muss an den Übergängen ein grösserer Radius vorgesehen werden. Bei den geschmiedeten Schaufelfüssen 25 liegt der Schmiederadius 29 etwa im Bereich zwischen 0,5 und 1,0 mm (Fig. 6). Aufgrund des Kerbfaktors benötigen gefräste Schaufelfüsse an den Übergängen einen Radius, der etwa 1,5-bis 2-mal grösser ist, als der Schmiederadius 29.Heretofore, the T-shaped blade roots 25 of the compressor blades 27 have been forged (forged) by upset forging so as to obtain a strength-determining grain structure as shown in FIG Fig. 6 is indicated by the dashed lines. Recently, due to new requirements in terms of costs, tools and logistics increasingly The idea was not to forge the blade roots, but to make them by milling (grain structure in Fig. 4 ). In order to achieve the same or better strength in the milled blade feet at the critical transitions to the projections 16, 16 'and 26, 26', as in the forged blade roots, a larger radius must be provided at the transitions. In the case of the forged blade roots 25, the forging radius 29 is approximately in the range between 0.5 and 1.0 mm (FIG. Fig. 6 ). Due to the notch factor, milled blade feet at the transitions require a radius that is about 1.5 to 2 times greater than the forging radius 29.

Das bisherige Schmiedeverfahren für die Schaufelfüsse 25 hatte weitere Konsequenzen: Durch das Stauchschmieden kommt es zu Ausbauchungen 31 am Schaft oberhalb der Vorsprünge 26, 26' (in Fig. 6 ist dies durch die punktierten Linien angedeutet), die im Bereich von 0,3 bis 0,5 mm liegen. Damit bei den montierten Laufschaufeln die geschmiedeten Schaufelfüsse 25 trotz der seitlichen Ausbauchungen 31 dennoch sicher und unverrückbar an den benachbarten Zwischenstücken 12, 18 anliegen, sind diese an den Seitenflächen im unteren Teil mit einer langen Abschrägung 17, 19 versehen, die Platz für die Ausbauchungen 31 schafft (siehe auch Fig. 3).The previous forging method for the blade roots 25 had further consequences: bulging 31 causes bulges 31 on the shaft above the projections 26, 26 '(in FIG Fig. 6 this is indicated by the dotted lines), which are in the range of 0.3 to 0.5 mm. To ensure that the forged blade feet 25 still rest securely and immovably on the adjacent intermediate pieces 12, 18 despite the lateral bulges 31, they are provided on the side faces in the lower part with a long bevel 17, 19, the space for the bulges 31 creates (see also Fig. 3 ).

Obgleich bereits ein von der Schaufelgrösse abhängender, 0,3 bis 0,5 mm breiter Spalt zwischen den angrenzenden Zwischenstücken 12, 18 und dem T-förmigen Schaufelfuss 25 besteht, würde eine Vergrösserung des Radius in den Ecken der Vorsprünge 26, 26' um den Faktor 1,5 bis 2 - wie sie für gefräste Schaufelfüsse notwendig ist - eine unerwünschte und gefährliche Kollision genau an der Stelle hervorrufen, wo eigentlich der Abbau mechanischer Spannungen das Ziel sein sollte.Although there is already a depending on the blade size, 0.3 to 0.5 mm wide gap between the adjacent intermediate pieces 12, 18 and the T-shaped blade root 25, would increase the radius in the corners of the projections 26, 26 'to the Factor 1.5 to 2 - which is necessary for milled blade feet - cause an unwanted and dangerous collision at the exact point where the reduction of mechanical stresses should actually be the goal.

Es ist andererseits möglich, mechanische Spannungen in Bereichen von Maschinenteilen, in denen einerseits das Risiko von Rissen gross ist, andererseits der Raum für das Anbringen grösserer Radien jedoch beschränkt ist, dadurch abzubauen, dass dort geeignet dimensionierte und platzierte Freistiche nach ISO-Standard vorgesehen werden.On the other hand, it is possible for mechanical stresses in areas of machine parts in which, on the one hand, the risk of cracks is great, on the other hand, however, the space for attaching larger radii is limited to reduce the fact that suitably dimensioned and placed undercuts are provided in accordance with the ISO standard.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist Aufgabe der Erfindung, eine Laufschaufel mit T-förmigem Schaufelfuss der eingangs genannten Art in der Form so auszubilden, dass sie günstiger herstellbar ist und gleichwohl die für geschmiedete Schaufelfüsse übliche Lebensdauer erreicht, sowie ein Verfahren zu deren Herstellung anzugeben.It is an object of the invention to form a blade with T-shaped blade root of the type mentioned in the form so that it is cheaper to produce and nevertheless reaches the usual forged blade roots life, and to provide a method for their preparation.

Die Aufgabe wird durch die Gesamtheit der Merkmale der Ansprüche 1 und 8 gelöst. Wesentlich für die Erfindung ist, dass der T-förmige Schaufelfuss gefräst ist, und dass zur Verringerung der mechanischen Spannungen an den Übergängen des Schaufelfusses zu den Vorsprüngen jeweils ein in axialer Richtung verlaufender Freistich vorgesehen ist. Der erfindungsgemäss Verdichter weist einen Rotor auf, welcher mit Laufschaufeln gemäss der Erfindung bestückt ist.The object is solved by the entirety of the features of claims 1 and 8. Essential for the invention is that the T-shaped blade root is milled, and that in order to reduce the mechanical stresses at the transitions of the blade root to the projections in each case an axially extending undercut is provided. The compressor according to the invention has a rotor which is equipped with blades according to the invention.

Grundsätzlich kann der Freistich ein Standard-Freistich nach ISO-Norm sein. Insbesondere ist der Freistich dann ein Freistich vom Typ E oder F gemäss DIN-Norm 506.Basically, the undercut can be a standard undercut to ISO standard. In particular, the undercut is then an undercut type E or F according to DIN standard 506.

Besonders vorteilhaft im Hinblick auf die Reduzierung der mechanischen Spannungen ist es, wenn die Zwischenstücke an ihren an den Schaufelfuss angrenzenden Seitenflächen jeweils eine Abschrägung aufweisen, und der Freistich ein von einem Standard-Freistich nach ISO-Norm abweichende, vergrösserte Höhe aufweist, welche die Abschrägung ausnutzt. Insbesondere kann dabei die Höhe des Freistichs in etwa der Höhe der Abschrägung entsprechen.Particularly advantageous with regard to the reduction of the mechanical stresses is when the spacers each have a chamfer at their adjoining the blade root side surfaces, and the undercut has a deviating from a standard undercut to ISO standard, increased height, which the bevel exploits. In particular, the height of the undercut can correspond approximately to the height of the bevel.

Vorzugsweise weist der Freistich einen Radius auf, der dem 1,5-2-fachen des Radius eines vergleichbaren durch Stauchschmieden geformten Schaufelfusses entspricht. Insbesondere ist der Radius 1,5 mm bei einem Stauchradius von 0,8, bzw. 1,75 mm bei einem Stauchradius von 1,0.Preferably, the undercut has a radius that is 1.5-2 times the radius of a comparable upset formed blade root. In particular, the radius is 1.5 mm with a compression radius of 0.8, or 1.75 mm with a compression radius of 1.0.

Weiterhin ist es vorteilhaft, wenn der Freistich in Richtung der Schaufelachse einem elliptischen Kurvenverlauf folgt.Furthermore, it is advantageous if the undercut follows an elliptical curve in the direction of the blade axis.

Eine bevorzugte Ausgestaltung des Verfahrens nach der Erfindung ist dadurch gekennzeichnet, dass die Freistiche in Richtung der Schaufelachse entlang eines elliptischen Bearbeitungspfades gefräst werden.A preferred embodiment of the method according to the invention is characterized in that the undercuts are milled in the direction of the blade axis along an elliptical processing path.

Besonders einfach wird die Bearbeitung, wenn zum Fräsen der Freistiche ein von der Kugelform abweichendes Fräswerkzeug verwendet wird.Machining becomes particularly easy if a milling tool deviating from the spherical shape is used to mill the undercuts.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen

Fig. 1
in Umfangsrichtung gesehen die der Erfindung zugrunde liegende Befestigungsart der Laufschaufeln mit T-förmigem Schaufelfuss zwischen zwei Zwischenstücken;
Fig. 2
die Befestigungsart der Fig. 1 in perspektivischer Darstellung;
Fig. 3
die Ausgestaltung des Schaufelfusses gemäss einem Ausführungsbeispiel der Erfindung;
Fig. 4
die Bearbeitung des Freistichs am Schaufelfuss mit einem grösseren Fräswerkzeug gemäss einem Ausführungsbeispiel der Erfindung;
Fig. 4a
die Bearbeitung des Freistichs am Schaufelfuss mit einem kleineren Fräswerkzeug mit Kugelkopf;
Fig. 5
einen Schaufelfuss gemäss einem Ausführungsbeispiel der Erfindung in perspektivischer Darstellung mit einem eingezeichneten elliptischen Bearbeitungspfad; und
Fig. 6
den in herkömmlicher Weise durch Stauchschmieden hergestellten T-förmigen Schaufelfuss.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
Seen in the circumferential direction, the invention underlying the mounting of the blades with T-shaped blade root between two intermediate pieces;
Fig. 2
the attachment of the Fig. 1 in perspective view;
Fig. 3
the embodiment of the blade root according to an embodiment of the invention;
Fig. 4
the machining of the undercut on the blade root with a larger milling tool according to an embodiment of the invention;
Fig. 4a
the machining of the undercut on the blade root with a smaller milling tool with ball head;
Fig. 5
a blade root according to an embodiment of the invention in perspective view with an indicated elliptical processing path; and
Fig. 6
the T-shaped blade root produced in a conventional manner by upset forging.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

Wesentlich für die vorliegende Erfindung ist, dass der für den gefrästen Schaufelfuss benötigte vergrösserte Radius durch einen Freistich erzeugt wird, der vorzugsweise unter Berücksichtigung der an den Zwischenstücken ausgebildeten seitlichen Abschrägungen verwirklicht wird. Als Freistiche kommen zunächst Freistiche nach ISO-Standard in Frage, die unter der DIN-Norm 509 als Freistiche der Form E und F aufgeführt sind. Der Freistich vom Typ E schneidet dabei nur in eine der beiden angrenzenden, zueinander senkrechten Flächen, während der Freistich vom Typ F in beide Flächen schneidet. Beide Freistich-Typen haben spezielle Auslaufbereiche (32, 33 in Fig. 3), die dem zusätzlichen Spannungsabbau im Radius dienen.It is essential for the present invention that the increased radius required for the milled blade root is produced by an undercut, which is preferably realized taking into account the lateral bevels formed on the intermediate pieces. As undercuts are first undercuts according to ISO standard in question, which are listed under the DIN standard 509 as undercuts form E and F. The undercut of type E only cuts into one of the two adjoining surfaces that are perpendicular to each other, while the undercut of type F cuts into both surfaces. Both undercut types have special outlet areas (32, 33 in Fig. 3 ), which serve the additional stress relief in the radius.

Mit derartigen Freistichen wird erreicht, dass bei unveränderter Gesamtanordnung und Befestigungsart der Laufschaufeln ohne Probleme die Laufschaufeln mit geschmiedetem Schaufelfuss durch die kostengünstigeren Laufschaufeln mit gefrästem Schaufelfuss ersetzt werden können, ohne dass Einbussen in der Lebensdauer hingenommen werden müssen. Insbesondere müssen die angrenzenden Zwischenstücke 12, 18 nicht geändert oder zusätzlich bearbeitet werden. Die Kontaktfläche zwischen dem Schaufelfuss (15 in Fig. 3) und den benachbarten Zwischenstücken 12 und 18 wird durch die Abschrägungen 17 und 19 an den Seitenflächen der Zwischenstücke 12, 18 begrenzt, aber auch bestimmt, so dass die Art des Freistichs 21 innerhalb des Bereichs der Abschrägungen 17, 19 keinen Einfluss auf die Kontaktfläche hat (Fig. 3). Entsprechend sind die Laufschaufeln immer in derselben Weise zwischen den Zwischenstücken 12, 18 gehalten, egal, ob der Schaufelfuss geschmiedet (Fig. 6) oder gefräst (Fig. 4) ist. Daraus folgt auch, dass sich die natürlichen Frequenzen (Resonanzen) der Schaufeln nicht ändern, so dass eine vollständige Austauschbarkeit zwischen den unterschiedlich hergestellten Schaufeln besteht.With such undercuts is achieved that with unchanged overall arrangement and mounting of the blades without problems, the blades with forged blade root can be replaced by the cheaper blades with milled blade root without losses in the Lifetime must be accepted. In particular, the adjacent intermediate pieces 12, 18 need not be changed or additionally processed. The contact surface between the blade root (15 in Fig. 3 ) and the adjacent intermediate pieces 12 and 18 is limited by the chamfers 17 and 19 on the side surfaces of the intermediate pieces 12, 18, but also determined, so that the type of undercut 21 within the region of the chamfers 17, 19 has no influence on the contact surface ( Fig. 3 ). Accordingly, the blades are always held in the same way between the intermediate pieces 12, 18, regardless of whether the blade root is forged ( Fig. 6 ) or milled ( Fig. 4 ). It also follows that the natural frequencies (resonances) of the blades do not change, so that there is complete interchangeability between the differently manufactured blades.

Ein Standard-Freistich vom Typ F schneidet - wie bereits oben erwähnt - in beide angrenzenden senkrechten Flächen in den Ecken der Vorsprünge 16, 16' des Schaufelfusses 15 ein (Fig. 4a). Dies ist der einzige Weg, um den vergrösserten Radius für die gewünschte gleiche oder längere Lebensdauer gegenüber geschmiedeten Schaufelfüssen zu erzielen. Ein solcher Standard-F-Freistich kann jedoch nur mittels eines Fräsprozesses erzeugt werden, wenn der Freistich gleichzeitig in Richtung der Schaufelachse A1 entlang einem elliptischen Bearbeitungspfad (23 in Fig. 5) erfolgen soll. Der Freistich ist jedoch nur mit sehr viel Aufwand zu fräsen, da hierfür das in Fig. 4a dargestellte kleine Fräswerkzeug 28 mit einem kugelförmigen Fräskopf (Kopfdurchmesser (2 x Radius R2): 2-3 mm; Schaft-Durchmesser: 1,5-2 mm) benutzt werden muss.A standard undercut type F cuts - as already mentioned above - in both adjacent vertical surfaces in the corners of the projections 16, 16 'of the blade root 15 ( Fig. 4a ). This is the only way to achieve the increased radius for the desired equal or longer life over forged blade roots. However, such a standard F-cut can only be produced by means of a milling process if the undercut is simultaneously moved in the direction of the blade axis A1 along an elliptical processing path (23 in FIG Fig. 5 ). The undercut, however, can only be milled with a great deal of effort, since this is what the in Fig. 4a shown small milling tool 28 with a spherical milling head (head diameter (2 x radius R2): 2-3 mm, shank diameter: 1.5-2 mm) must be used.

Es wird daher beim Schaufelfuss 15 vorzugsweise der in Fig. 3, 4 und 5 gezeigte modifizierte Freistich 21 eingesetzt, der sich durch eine vergrösserte Höhe h in Richtung der Längsachse der Schaufel auszeichnet. Insbesondere kann die Höhe h des Freistichs 21 der gesamten Länge der Abschrägung 17, 19 an den Seitenflächen der Zwischenstücke 12, 18 entsprechen. Die Vergrösserung der Höhe h gegenüber dem Standard-Freistich 30 ermöglicht es, gemäss Fig. 4 ein grösseres Fräswerkzeug 22 mit einem Radius R1 > R2 einzusetzen (R1 ist z.B. 1,75 mm), wodurch die Kosten und die Bearbeitungszeiten deutlich reduziert werden (die gestrichelte Schraffur in Fig. 4 deutet an, dass der Schaufelfuss 15 gefräst und nicht geschmiedet ist).It is therefore at the blade root 15 preferably in Fig. 3 . 4 and 5 shown modified undercut 21 used, which is characterized by an increased height h in the direction of the longitudinal axis of the blade. In particular, the height h of the undercut 21 may correspond to the entire length of the chamfer 17, 19 on the side surfaces of the intermediate pieces 12, 18. The increase in the height h compared to the standard undercut 30 makes it possible, according to Fig. 4 to use a larger milling tool 22 with a radius R1> R2 (R1 is eg 1.75 mm), which significantly reduces costs and processing times (dashed hatch in Fig. 4 indicates that the blade root 15 is milled and not forged).

Die beschriebene Vergrösserung der Höhe h des Freistichs ist nicht nur erlaubt (weil durch die lange Abschrägung 17, 19 ohnehin kein Kontakt zwischen Schaufelfuss 15 und den Zwischenstücken 12, 18 besteht), sondern auch erwünscht, weil die Spannungen in der Kerbe dadurch automatisch verringert werden.The described increase in the height h of the undercut is not only allowed (because there is no contact between the blade root 15 and the intermediate pieces 12, 18 anyway due to the long bevel 17, 19), but also desirable because the stresses in the notch are thereby automatically reduced ,

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1010
Rotorrotor
1111
Nutgroove
12,1812.18
Zwischenstückconnecting piece
13,2713.27
Laufschaufelblade
1414
Schaufelblattairfoil
15,2515.25
Schaufelfussblade root
16,16'16.16 '
Vorsprunghead Start
17,1917.19
Abschrägungbevel
2020
Halteflächeholding surface
21,3021.30
FreistichFreeway
22,2822.28
Fräswerkzeugmilling tool
2323
elliptischer Bearbeitungspfadelliptical machining path
2424
Hinterschneidungundercut
26,26'26.26 '
Vorsprunghead Start
2929
Schmiederadiuswrought radius
3131
Ausbauchungbulge
32,3332.33
Auslaufbereichdischarge area
A1A1
Schaufelachseblade axis
A2A2
Rotorachserotor axis
hH
Höhe (Freistich)Height (undercut)
R1,R2R1, R2
Radius (Freistich)Radius (undercut)

Claims (11)

Laufschaufel (13) zur Befestigung am Rotor (10) einer Turbomaschine, insbesondere eines Verdichters einer Gasturbine, welche Laufschaufel (13) ein Schaufelblatt (14) und einen am unteren Ende des Schaufelblatts (14) anschliessenden, sich entlang einer Schaufelachse (A1) erstreckenden Schaufelfuss (15) umfasst, mit welchem die Laufschaufel (13) in einer auf dem Aussenumfang des Rotors (10) angeordneten umlaufenden Nut (11) zwischen zwei in Umfangsrichtung aufeinander folgenden Zwischenstücken (12, 18) gehalten wird, die ihrerseits in der Nut (11) gehalten werden, wobei der Schaufelfuss (15) im Querschnitt T-förmig ausgebildet ist und mit sich in Umfangsrichtung erstreckenden Vorsprüngen (16, 16') unter die angrenzenden Zwischenstücke (12, 18) greift, und die Zwischenstücke (12, 18) in Richtung der Schaufelachse (A1) mit Halteflächen (20) in Hinterschneidungen (24) in der Nut (11) eingreifen, dadurch gekennzeichnet, dass der T-förmige Schaufelfuss (15) gefräst ist, und dass zur Verringerung der mechanischen Spannungen an den Übergängen des Schaufelfusses (15) zu den Vorsprüngen (16, 16') jeweils ein in Richtung der Schaufelachse (A1) verlaufender Freistich (21, 30) vorgesehen ist.Blade (13) for attachment to the rotor (10) of a turbomachine, in particular a compressor of a gas turbine, which blade (13) an airfoil (14) and at the lower end of the airfoil (14), extending along a blade axis (A1) extending Blade root (15), with which the blade (13) in a on the outer circumference of the rotor (10) arranged circumferential groove (11) between two circumferentially successive intermediate pieces (12, 18) is held, which in turn in the groove ( 11), wherein the blade root (15) is T-shaped in cross-section and engages with circumferentially extending projections (16, 16 ') below the adjacent intermediate pieces (12, 18), and the intermediate pieces (12, 18). engage in the direction of the blade axis (A1) with retaining surfaces (20) in undercuts (24) in the groove (11), characterized in that the T-shaped blade root (15) is milled, and that to V reducing the mechanical stresses at the transitions of the blade root (15) to the projections (16, 16 ') in each case one in the direction of the blade axis (A1) extending undercut (21, 30) is provided. Laufschaufel nach Anspruch 1, dadurch gekennzeichnet, dass der Freistich (30) ein Standard-Freistich nach ISO-Norm ist.Blade according to claim 1, characterized in that the undercut (30) is a standard undercut to ISO standard. Laufschaufel nach Anspruch 2, dadurch gekennzeichnet, dass der Freistich (30) ein Freistich vom Typ E oder F gemäss DIN-Norm 506 ist.Blade according to claim 2, characterized in that the undercut (30) is an undercut type E or F according to DIN standard 506. Laufschaufel nach Anspruch 1, dadurch gekennzeichnet, dass die Zwischenstücke (12, 18) an ihren an den Schaufelfuss (15) angrenzenden Seitenflächen jeweils eine Abschrägung (17, 19) aufweisen, und dass der Freistich (21) ein von einem Standard-Freistich nach ISO-Norm abweichende, vergrösserte Höhe (h) aufweist.Blade according to Claim 1, characterized in that the intermediate pieces (12, 18) each have a chamfer (17, 19) on their side surfaces adjoining the blade root (15), and in that the undercut (21) extends from a standard undercut ISO standard deviating, increased height (h) has. Laufschaufel nach Anspruch 4, dadurch gekennzeichnet, dass die Höhe (h) des Freistichs (21) in etwa der Höhe der Abschrägung (17, 19) entspricht.Blade according to Claim 4, characterized in that the height (h) of the undercut (21) corresponds approximately to the height of the chamfer (17, 19). Laufschaufel nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass der Freistich (21) einen Radius (R1) aufweist, der dem 1,5-2-fachen des Radius eines vergleichbaren durch Stauchschmieden geformten Schaufelfusses entspricht.Blade according to claim 4 or 5, characterized in that the undercut (21) has a radius (R1) which corresponds to 1.5-2 times the radius of a comparable formed by upsetting blade root. Laufschaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Freistich (21, 30) in Richtung der Schaufelachse (A1) einem elliptischen Kurvenverlauf (23) folgt.Blade according to one of claims 1 to 6, characterized in that the undercut (21, 30) in the direction of the blade axis (A1) follows an elliptical curve (23). Verfahren zur Herstellung einer Laufschaufel nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass in einem ersten Schritt die T-Form des Schaufelfusses (15) durch einen Fräsprozess erzeugt wird, und dass in einem zweiten Schritt die Freistiche (21, 30) in den Schaufelfuss (15) gefräst werden.Method for producing a moving blade according to one of claims 1 to 7, characterized in that in a first step, the T-shape of the blade root (15) is produced by a milling process, and that in a second step, the undercuts (21, 30) in the blade root (15) are milled. Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass die Freistiche (21, 30) in Richtung der Schaufelachse (A1) entlang eines elliptischen Bearbeitungspfades (23) gefräst werden.A method according to claim 8, characterized in that the undercuts (21, 30) in the direction of the blade axis (A1) along an elliptical processing path (23) are milled. Verfahren nach Anspruch 8 oder 9, dadurch gekennzeichnet, dass zum Fräsen der Freistiche (21) ein von der Kugelform abweichendes Fräswerkzeug (22) verwendet wird.A method according to claim 8 or 9, characterized in that for milling the undercuts (21) a deviating from the spherical shape milling tool (22) is used. Verdichter, insbesondere für eine Gasturbine, dadurch gekennzeichnet, dass er einen Rotor (10) aufweist, welcher mit Laufschaufeln (13) gemäss einem der Ansprüche 1 bis 7 bestückt ist.Compressor, in particular for a gas turbine, characterized in that it comprises a rotor (10) which is equipped with blades (13) according to one of claims 1 to 7.
EP08165091.3A 2007-10-01 2008-09-25 Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade Active EP2045444B1 (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702203A1 (en) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor for axial flow turbomachine i.e. gas turbine, in combined cycle power plant, has rotating blades inserted into groove, and blade root comprising inverted-T root with hammer head and adapted to base area of groove in radial direction
DE102011082850A1 (en) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Compressor blade and method for its production
US8770938B2 (en) 2009-11-10 2014-07-08 Alstom Technology Ltd Rotor for an axial-throughflow turbomachine and moving blade for such a rotor
CN111571153A (en) * 2020-05-29 2020-08-25 重庆水轮机厂有限责任公司 Method for machining blade profile of Kaplan turbine blade

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010004854A1 (en) 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Blade for a turbomachine and turbomachine
CH704617A1 (en) * 2011-03-07 2012-09-14 Alstom Technology Ltd Blade assembly of a turbomachine.
FR2972380A1 (en) * 2011-03-11 2012-09-14 Alstom Technology Ltd METHOD FOR MANUFACTURING STEAM TURBINE DIAPHRAGM
CH704825A1 (en) 2011-03-31 2012-10-15 Alstom Technology Ltd Turbomachinery rotor.
CH705377A1 (en) * 2011-08-09 2013-02-15 Alstom Technology Ltd A process for reconditioning a rotor of a turbomachine.
US9359905B2 (en) 2012-02-27 2016-06-07 Solar Turbines Incorporated Turbine engine rotor blade groove
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US9739159B2 (en) 2013-10-09 2017-08-22 General Electric Company Method and system for relieving turbine rotor blade dovetail stress
EP3015652A1 (en) * 2014-10-28 2016-05-04 Siemens Aktiengesellschaft Rotor blade for a turbine
CN113914999B (en) * 2021-12-14 2022-03-18 成都中科翼能科技有限公司 Gas turbine compressor assembling method

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE318662C (en) 1918-02-18
FR451147A (en) * 1912-11-28 1913-04-11 Westinghouse Machine Co Improvements to pressurized fluid turbines
DE437049C (en) 1923-01-19 1926-11-12 Aeg Process for the manufacture of turbine blades
DE1005530B (en) * 1955-06-23 1957-04-04 Paul Miesbeck Fastening of the rotor blades of centrifugal machines, in particular steam and gas turbines
JPS59226202A (en) * 1983-06-06 1984-12-19 Toshiba Corp Moving blade of turbine
EP0551229A1 (en) * 1992-01-08 1993-07-14 Gec Alsthom Sa Drum rotor for impulse steam turbine with blades mounted in axial grooves
DE4435268A1 (en) * 1994-10-01 1996-04-04 Abb Management Ag Bladed rotor of a turbo machine
JP2005220825A (en) 2004-02-06 2005-08-18 Mitsubishi Heavy Ind Ltd Turbine moving blade
EP1698758A2 (en) 2005-02-23 2006-09-06 ALSTOM Technology Ltd Axially split rotor end piece
DE102005048883A1 (en) 2005-10-12 2007-04-19 Alstom Technology Ltd. Turbine assembly for axial steam turbine, has turbine bucket placed radially at external covering section and foot section containing perimeter counter bearings which are installed radially, over one another, in final configuration position

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2857132A (en) * 1952-02-19 1958-10-21 Gen Motors Corp Turbine wheel
US4272953A (en) * 1978-10-26 1981-06-16 Rice Ivan G Reheat gas turbine combined with steam turbine
JP3462695B2 (en) * 1997-03-12 2003-11-05 三菱重工業株式会社 Gas turbine blade seal plate
EP1130217B1 (en) * 2000-03-01 2005-05-18 ALSTOM Technology Ltd Fixing of blades in a turbomachine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR451147A (en) * 1912-11-28 1913-04-11 Westinghouse Machine Co Improvements to pressurized fluid turbines
DE318662C (en) 1918-02-18
DE437049C (en) 1923-01-19 1926-11-12 Aeg Process for the manufacture of turbine blades
DE1005530B (en) * 1955-06-23 1957-04-04 Paul Miesbeck Fastening of the rotor blades of centrifugal machines, in particular steam and gas turbines
JPS59226202A (en) * 1983-06-06 1984-12-19 Toshiba Corp Moving blade of turbine
EP0551229A1 (en) * 1992-01-08 1993-07-14 Gec Alsthom Sa Drum rotor for impulse steam turbine with blades mounted in axial grooves
DE4435268A1 (en) * 1994-10-01 1996-04-04 Abb Management Ag Bladed rotor of a turbo machine
JP2005220825A (en) 2004-02-06 2005-08-18 Mitsubishi Heavy Ind Ltd Turbine moving blade
EP1698758A2 (en) 2005-02-23 2006-09-06 ALSTOM Technology Ltd Axially split rotor end piece
DE102005048883A1 (en) 2005-10-12 2007-04-19 Alstom Technology Ltd. Turbine assembly for axial steam turbine, has turbine bucket placed radially at external covering section and foot section containing perimeter counter bearings which are installed radially, over one another, in final configuration position

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702203A1 (en) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor for axial flow turbomachine i.e. gas turbine, in combined cycle power plant, has rotating blades inserted into groove, and blade root comprising inverted-T root with hammer head and adapted to base area of groove in radial direction
US8770938B2 (en) 2009-11-10 2014-07-08 Alstom Technology Ltd Rotor for an axial-throughflow turbomachine and moving blade for such a rotor
DE102011082850A1 (en) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Compressor blade and method for its production
CN111571153A (en) * 2020-05-29 2020-08-25 重庆水轮机厂有限责任公司 Method for machining blade profile of Kaplan turbine blade

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US20090087316A1 (en) 2009-04-02

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