[go: up one dir, main page]

EP1690011A1 - Rotor for a compressor - Google Patents

Rotor for a compressor

Info

Publication number
EP1690011A1
EP1690011A1 EP04804578A EP04804578A EP1690011A1 EP 1690011 A1 EP1690011 A1 EP 1690011A1 EP 04804578 A EP04804578 A EP 04804578A EP 04804578 A EP04804578 A EP 04804578A EP 1690011 A1 EP1690011 A1 EP 1690011A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
depth
blade
recess
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
EP04804578A
Other languages
German (de)
French (fr)
Other versions
EP1690011B8 (en
EP1690011B1 (en
Inventor
René Bachofner
Pietro Grigioni
Wolfgang Kappis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia IP UK Ltd
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1690011A1 publication Critical patent/EP1690011A1/en
Application granted granted Critical
Publication of EP1690011B1 publication Critical patent/EP1690011B1/en
Publication of EP1690011B8 publication Critical patent/EP1690011B8/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a rotor for a compressor according to the preamble of claim 1.
  • Rotors of high-pressure compressors such as are used in particular in gas turbines, generally have a multi-stage blading which comprises blade rings arranged one behind the other in the axial direction. Each blade ring contains a large number of rotor blades that run around the circumference of the rotor are arranged and attached. Each of the rotor blades sits with a blade root in a circumferential groove, which is designed as a recess in the rotor.
  • a rotor is known for example from the document DE-A1-196 15 549.
  • the rotor blade 15 comprises an airfoil 21 projecting radially outwards and a blade root 16, which are separated from one another by a platform 18.
  • the rotor blade 15 is fastened to the blade root 16 in the rotor 10.
  • a circumferential groove in the form of a recess 11 is provided for fastening the blades, which has a depth of insertion T.
  • Shoulders 14 with a shoulder depth A are formed on the side walls within the recess 11.
  • the blade root 16 has a widening lower part 17 with a cross-sectional contour in the form of an upside-down "T" with which it engages behind the shoulders 14 of the recess 11.
  • the centrifugal force acting on the rotor blade 15 when the rotor 10 rotates becomes thereby transferred to the shoulders 14 of the recess 11 via contact surfaces 13.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is to provide an insertion depth of the insertion that is significantly greater than the minimum insertion depth.
  • the insertion depth should preferably be more than 10% greater than the minimum insertion depth. It has proven particularly useful when the screwing depth is about 40% greater than the minimum screwing depth.
  • a preferred embodiment of the invention is characterized in that the moving blades have a blade root that is adapted to the screwing depth, and that recesses are provided in the blade root to reduce weight. As a result, the increase in weight of the moving blade due to the extended blade root can be compensated and the forces occurring during operation can be reduced.
  • a recess is provided in the blade root above the lower part in the form of a hole passing through the blade root in the circumferential direction, the hole being designed in particular as an elongated hole extending in the radial direction.
  • FIG. 1 in a fragmentary longitudinal section, the attachment of a rotor blade in the rotor of a high-pressure compressor according to the prior art
  • Fig. 2 in a representation comparable to Fig. 1 shows an embodiment for a blade attachment according to the invention.
  • the rotor blade 25 is fastened in the rotor 20 with the airfoil 22, the platform 28 and the blade root 26 by means of a recess 21.
  • lateral shoulders 24 are again formed here, behind which the blade root 26 engages with its widened lower part 27 and is supported on the contact surfaces 23 when centrifugal forces occur.
  • Screw-in depth T executed, which is significantly, in particular more than 10%, greater than the minimum screw-in depth Tmi n used in the prior art. This makes it possible to bring the shoulder depth of the shoulders 24 to a value B which is substantially greater than the shoulder depth A in the known attachment according to FIG. 1.
  • the screwing depth T is approximately 40% greater than that minimum insertion depth Tm in , which has proven itself in practice.
  • the height of the blade root 26 With the increase in the screw-in depth T and the shoulder depth B, the height of the blade root 26 also increases. By lengthening the blade root 26, the blade weight inevitably also increases, which would lead to increased centrifugal forces and thus to increased mechanical stress on the rotor 20.
  • a first preferred type of recess is an elongated hole 19 that passes through the blade root 26 in the circumferential direction and extends in the radial direction.
  • the elongated hole 19 is arranged in the slender section of the blade root 26 and is located in the middle between the two shoulders 24.
  • a second preferred type of recess is rounded-sided recesses 29 on the underside of the lower part 27 of the blade root 26. Both types of recesses 19, 29 can be combined individually or with each other in order to achieve the desired weight reduction by saving material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a rotor (20) for a compressor, in particular a gas turbine, comprising a plurality of moving blades (25), which are arranged in the form of a ring about the rotation axis of the rotor (20) and which are each maintained in a peripheral turned groove (21) on the rotor (21) by means of a blade root (26), whereby a widening lower part (27) of said blade root (26) engages behind two shoulders (24), formed on the lateral walls of said turned groove (21). The aim of said invention is to extend the lifetime of such a rotor. Said aim is achieved, whereby the depth (T) of the turned groove (21) is substantially greater than a minimal groove depth (Tmin), a strength of rotor (20), which is sufficient for start-up, being thus obtained in the area of the blade mounting, according to the predetermined material characteristics of the rotor (20) and operating conditions of the compressor.

Description

BESCHREIBUNG DESCRIPTION

ROTOR FÜR EINEN VERDICHTERROTOR FOR A COMPRESSOR

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Turbomaschinen. Sie betrifft einen Rotor für einen Verdichter gemäss dem Oberbegriff des Anspruchs 1 ,The present invention relates to the field of turbomachinery. It relates to a rotor for a compressor according to the preamble of claim 1.

STAND DER TECHNIKSTATE OF THE ART

Rotoren von Hochdruck-Verdichtem, wie sie insbesondere in Gasturbinen eingesetzt werden, weisen in der Regel eine mehrstufige Beschaufelung auf, die in axialer Richtung hintereinander angeordnete Schaufelkränze umfasst. Jeder Schaufelkranz enthält eine Vielzahl von Laufschaufeln, die am Umfang des Rotors angeordnet und befestigt sind. Jede der Laufschaufeln sitzt mit einem Schaufelfuss in einer Umfangsnut, die als Eindrehung in den Rotor ausgebildet ist. Ein solcher Rotor ist beispielsweise aus der Druckschrift DE-A1-196 15 549 bekannt.Rotors of high-pressure compressors, such as are used in particular in gas turbines, generally have a multi-stage blading which comprises blade rings arranged one behind the other in the axial direction. Each blade ring contains a large number of rotor blades that run around the circumference of the rotor are arranged and attached. Each of the rotor blades sits with a blade root in a circumferential groove, which is designed as a recess in the rotor. Such a rotor is known for example from the document DE-A1-196 15 549.

Die Befestigung einer einzelnen Laufschaufel in einem Rotor nach dem Stand der Technik ist auch in Fig. 1 wiedergegeben: Die Laufschaufel 15 umfasst ein radial nach aussen abstehendes Schaufelblatt 21 und einen Schaufelfuss16, die durch eine Plattform 18 voneinander getrennt sind. Die Laufschaufel 15 ist mit dem Schaufelfuss 16 im Rotor 10 befestigt. Zur Befestigung der Laufschaufeln ist eine Umfangsnut in Form einer Eindrehung 11 vorgesehen, die eine Eindrehtiefe T hat. Innerhalb der Eindrehung 11 sind an den Seitenwänden Schultern 14 mit einer Schultertiefe A ausgebildet. Der Schaufelfuss 16 weist ein sich verbreiterndes Unterteil 17 mit einer Querschnittskontur in Form eines auf dem Kopf stehenden „T" auf, mit dem es hinter die Schultern 14 der Eindrehung 11 greift. Die bei Drehung des Rotors 10 auf die Laufschaufel 15 wirkende Fliehkraft wird dabei über Anpressflächen 13 auf die Schultern 14 der Eindrehung 11 übertragen.The attachment of an individual rotor blade in a rotor according to the prior art is also shown in FIG. 1: The rotor blade 15 comprises an airfoil 21 projecting radially outwards and a blade root 16, which are separated from one another by a platform 18. The rotor blade 15 is fastened to the blade root 16 in the rotor 10. A circumferential groove in the form of a recess 11 is provided for fastening the blades, which has a depth of insertion T. Shoulders 14 with a shoulder depth A are formed on the side walls within the recess 11. The blade root 16 has a widening lower part 17 with a cross-sectional contour in the form of an upside-down "T" with which it engages behind the shoulders 14 of the recess 11. The centrifugal force acting on the rotor blade 15 when the rotor 10 rotates becomes thereby transferred to the shoulders 14 of the recess 11 via contact surfaces 13.

Um die mechanische Festigkeit des Rotors durch die Eindrehungen 11 für die Laufschaufeln möglichst wenig zu schwächen, werden die Eindrehungen 11 im Stand der Technik mit einer minimalen Eindrehtiefe T=Tmin ausgeführt. Diese minimale Eindrehtiefe Tmin ermöglicht eine Schultertiefe A der Schulter 14, die gerade ausreicht, um unter den vorherrschenden extremen Betriebsbedingungen (hohe Drehzahlen, Temperaturen bis zu 500°C) und den Eigenschaften des gewählten Rotormaterials eine ausreichende anfängliche Festigkeit des Rotors 10 im Bereich der Schultern 14 zu ermöglichen.The mechanical strength of the rotor to weaken by the turned grooves 11 for the rotor blades as little as possible, the grooves on 11 executed in the art with a minimum insertion depth T = T m in. This minimum insertion depth Tmi n enables a shoulder depth A of the shoulder 14 which is just sufficient to ensure sufficient initial strength of the rotor 10 in the region of the prevailing extreme operating conditions (high speeds, temperatures up to 500 ° C.) and the properties of the selected rotor material To allow shoulders 14.

Es hat sich nun jedoch in der Praxis herausgestellt, dass die Verwendung einer Eindrehung mit der minimalen Eindrehtiefe Tmin dazu führen kann, dass der Rotor 10 im Bereich der Eindrehung 11 über die zulässigen Festigkeitsgrenzen hinaus beansprucht wird, was zu einer Reduktion der Rotor-Lebensdauer führen kann. DARSTELLUNG DER ERFINDUNGHowever, it has now been found in practice that the use of a recess with the minimum insertion depth Tmin can result in the rotor 10 being stressed beyond the permissible strength limits in the region of the recess 11, which leads to a reduction in the rotor service life can. PRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, einen Rotor für einen Verdichter zu schaffen, der dieses Lebensdauerproblem beseitigt.It is therefore an object of the invention to provide a rotor for a compressor which eliminates this life problem.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, eine Eindrehtiefe der Eindrehung vorzusehen, die wesentlich grosser ist als die minimale Eindrehtiefe.The object is achieved by the entirety of the features of claim 1. The essence of the invention is to provide an insertion depth of the insertion that is significantly greater than the minimum insertion depth.

Bevorzugt soll die Eindrehtiefe mehr als 10% grosser sein als die minimale Eindrehtiefe. Besonders bewährt hat es sich, wenn die Eindrehtiefe etwa 40% grosser ist als die minimale Eindrehtiefe.The insertion depth should preferably be more than 10% greater than the minimum insertion depth. It has proven particularly useful when the screwing depth is about 40% greater than the minimum screwing depth.

Eine bevorzugte Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die Laufschaufeln einen der Eindrehtiefe angepassten Schaufelfuss aufweisen, und dass zur Gewichtsreduktion im Schaufelfuss Ausnehmungen vorgesehen sind. Hierdurch lassen sich Gewichtszunahmen der Laufschaufel aufgrund des verlängerten Schaufelfusses kompensieren und die beim Betrieb auftretenden Kräfte verringern.A preferred embodiment of the invention is characterized in that the moving blades have a blade root that is adapted to the screwing depth, and that recesses are provided in the blade root to reduce weight. As a result, the increase in weight of the moving blade due to the extended blade root can be compensated and the forces occurring during operation can be reduced.

Bei einer bevorzugten Weiterbildung der Ausgestaltung ist im Schaufelfuss oberhalb des Unterteils eine Ausnehmung in Form eines in Umfangsrichtung durch den Schaufelfuss hindurchgehenden Loches vorgesehen, wobei das Loch insbesondere als sich in radialer Richtung erstreckendes Langloch ausgebildet ist.In a preferred development of the embodiment, a recess is provided in the blade root above the lower part in the form of a hole passing through the blade root in the circumferential direction, the hole being designed in particular as an elongated hole extending in the radial direction.

Es kann aber auch von Vorteil sein, wenn auf der Unterseite des Unterteils des Schaufelfusses zur Gewichtsreduktion Ausnehmungen vorgesehen sind.However, it can also be advantageous if recesses are provided on the underside of the lower part of the blade root for weight reduction.

KURZE ERLÄUTERUNG DER FIGUREN Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigenBRIEF EXPLANATION OF THE FIGURES The invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. Show it

Fig. 1 in einem ausschnittweise dargestellten Längsschnitt die Befestigung einer Laufschaufel im Rotor eines Hochdruck- Verdichters nach dem Stand der Technik undFig. 1 in a fragmentary longitudinal section, the attachment of a rotor blade in the rotor of a high-pressure compressor according to the prior art and

Fig. 2 in einer zu Fig. 1 vergleichbaren Darstellung ein Ausführungsbeispiel für eine Laufschaufelbefestigung nach der Erfindung.Fig. 2 in a representation comparable to Fig. 1 shows an embodiment for a blade attachment according to the invention.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS OF CARRYING OUT THE INVENTION

Bei dem in Fig. 2 dargestellten Ausführungsbeispiel der Erfindung ist in dem Rotor 20 die Laufschaufel 25 mit dem Schaufelblatt 22, der Plattform 28 und dem Schaufelfuss 26 mittels einer Eindrehung 21 befestigt. In der Eindrehung 21 sind auch hier wieder seitliche Schultern 24 ausgebildet, hinter die der Schaufelfuss 26 mit seinem verbreiterten Unterteil 27 greift und sich beim Auftreten von Fliehkräften an den Anpressflächen 23 abstützt.In the exemplary embodiment of the invention shown in FIG. 2, the rotor blade 25 is fastened in the rotor 20 with the airfoil 22, the platform 28 and the blade root 26 by means of a recess 21. In the recess 21, lateral shoulders 24 are again formed here, behind which the blade root 26 engages with its widened lower part 27 and is supported on the contact surfaces 23 when centrifugal forces occur.

Um die dabei entstehende Belastung der Schultern 24 besser auffangen zu können und damit die durch Festigkeitsprobleme bedingte Lebensdauerbegrenzung zu beseitigen, wird die Eindrehung 21 nun mit einerIn order to be able to better absorb the resulting load on the shoulders 24 and thus to eliminate the service life limitation caused by strength problems, the recess 21 is now with a

Eindrehtiefe T ausgeführt, die wesentlich, insbesondere mehr als 10%, grosser ist als die im Stand der Technik verwendete minimale Eindrehtiefe Tmin. Hierdurch ist es möglich, die Schultertiefe der Schultern 24 auf einen Wert B zu bringen, der wesentlich grosser ist als die Schultertiefe A bei der vorbekannten Befestigung gemäss Fig. 1. Im Ausführungsbeispiel der Fig. 2 ist die Eindrehtiefe T etwa 40% grosser als die minimale Eindrehtiefe Tmin, was sich in der Praxis bewährt hat. Mit der Erhöhung der Eindrehtiefe T und der Schultertiefe B vergrössert sich auch die Höhe des Schaufelfusses 26. Durch die Verlängerung des Schaufelfusses 26 erhöht sich zwangsläufig auch das Schaufelgewicht, was zu erhöhten Fliehkräften und damit zu einer erhöhten mechanischen Beanspruchung des Rotors 20 führen würde. Es ist daher besonders vorteilhaft, wenn zumindest ein Teil des durch die Verlängerung verursachten Gewichtszuwachses durch geeignete Massnahmen wieder beseitigt wird. Die Massnahmen bestehen darin, an der Laufschaufel 25 im Bereich des Schaufelfusses 26 an für die mechanische Festigkeit unkritischen Stellen durch das Vorsehen von Ausnehmungen Material einzusparen. Eine erste bevorzugte Art der Ausnehmung ist ein Langloch 19, dass in Umfangsrichtung durch den Schaufelfuss 26 hindurchgeht und sich in radialer Richtung erstreckt. Das Langloch 19 ist dabei im schlanken Abschnitt des Schaufelfusses 26 angeordnet und befindet sich in der Mitte zwischen den beiden Schultern 24. Eine zweite bevorzugte Art der Ausnehmung sind randseitige, gerundete Vertiefungen 29 auf der Unterseite des Unterteils 27 des Schaufelfusses 26. Beide Arten von Ausnehmungen 19, 29 können wahlweise einzeln oder miteinander kombiniert werden, um die gewünschte Gewichtsreduktion durch Materialeinsparung zu verwirklichen. Screw-in depth T executed, which is significantly, in particular more than 10%, greater than the minimum screw-in depth Tmi n used in the prior art. This makes it possible to bring the shoulder depth of the shoulders 24 to a value B which is substantially greater than the shoulder depth A in the known attachment according to FIG. 1. In the exemplary embodiment in FIG. 2, the screwing depth T is approximately 40% greater than that minimum insertion depth Tm in , which has proven itself in practice. With the increase in the screw-in depth T and the shoulder depth B, the height of the blade root 26 also increases. By lengthening the blade root 26, the blade weight inevitably also increases, which would lead to increased centrifugal forces and thus to increased mechanical stress on the rotor 20. It is therefore particularly advantageous if at least part of the weight gain caused by the extension is eliminated again by suitable measures. The measures consist in saving material on the rotor blade 25 in the area of the blade root 26 at locations that are not critical for the mechanical strength by providing recesses. A first preferred type of recess is an elongated hole 19 that passes through the blade root 26 in the circumferential direction and extends in the radial direction. The elongated hole 19 is arranged in the slender section of the blade root 26 and is located in the middle between the two shoulders 24. A second preferred type of recess is rounded-sided recesses 29 on the underside of the lower part 27 of the blade root 26. Both types of recesses 19, 29 can be combined individually or with each other in order to achieve the desired weight reduction by saving material.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

10,20 Rotor10.20 rotor

11,21 Eindrehung (Umfangsnut)11.21 recess (circumferential groove)

12,22 Schaufelblatt12.22 airfoil

13,23 Anpressfläche13.23 contact surface

14,24 Schulter14.24 shoulder

15,25 Laufschaufel15.25 blade

16,26 Schaufelfuss16.26 blade root

17,27 Unterteil (Schaufelfuss)17.27 lower part (blade root)

18,28 Plattform18.28 platform

19 Langloch19 slot

29 Vertiefung29 deepening

A, B SchultertiefeA, B shoulder depth

' min minimale Eindrehtiefe'min minimum insertion depth

T Eindrehtiefe T insertion depth

Claims

PATENTANSPRÜCHE 1. Rotor (20) für einen Verdichter, insbesondere einer Gasturbine, welcher Rotor (20) eine Mehrzahl von Laufschaufeln (25) umfasst, die um die Drehachse des Rotors (20) herum in Form eines Kranzes angeordnet sind und jeweils mit einem Schaufelfuss (26) in einer umlaufenden Eindrehung (21) am Rotor (20) gehalten sind, wobei der Schaufelfuss (26) mit einem sich verbreiternden Unterteil (27) hinter zwei an den Seitenwänden der Eindrehung (21) ausgebildete Schultern (24) greift, dadurch gekennzeichnet, dass die Eindrehtiefe (T) der Eindrehung (21) wesentlich grosser ist als eine minimale Eindrehtiefe (Tmιn), welche unter den vorgegebenen Materialeigenschaften des Rotors (20) und Betriebsbedingungen des Verdichters eine für den Anfang ausreichende Festigkeit des Rotors (20) im Bereich der Schaufelbefestigung ergibt.1. Rotor (20) for a compressor, in particular a gas turbine, which rotor (20) comprises a plurality of rotor blades (25) which are arranged in the form of a ring around the axis of rotation of the rotor (20) and each with a blade root ( 26) are held in a circumferential recess (21) on the rotor (20), the blade root (26) with a widening lower part (27) engaging behind two shoulders (24) formed on the side walls of the recess (21), characterized that the screw-in depth (T) of the screw-in (21) is significantly greater than a minimum screw-in depth (T m ι n ), which, given the material properties of the rotor (20) and the operating conditions of the compressor, ensures that the rotor (20 ) results in the area of the blade attachment. 2. Rotor nach Anspruch 1 , dadurch gekennzeichnet, dass die Eindrehtiefe (T) mehr als 10% grosser ist als die minimale Eindrehtiefe (Tmin).2. Rotor according to claim 1, characterized in that the insertion depth (T) is more than 10% greater than the minimum insertion depth (T min ). 3. Rotor nach Anspruch 2, dadurch gekennzeichnet, dass die Eindrehtiefe (T) etwa 40% grosser ist als die minimale Eindrehtiefe (Tmin).3. Rotor according to claim 2, characterized in that the insertion depth (T) is approximately 40% greater than the minimum insertion depth (T m in). 4. Rotor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Laufschaufeln (25) einen der Eindrehtiefe (T) angepassten Schaufelfuss (26) aufweisen, und dass zur Gewichtsreduktion im Schaufelfuss (26) Ausnehmungen (19, 29) vorgesehen sind.4. Rotor according to one of claims 1 to 3, characterized in that the rotor blades (25) have a blade root (26) adapted to the insertion depth (T), and that recesses (19, 29) are provided in the blade root (26) for weight reduction , 5. Rotor nach Anspruch 4, dadurch gekennzeichnet, dass im Schaufelfuss (26) oberhalb des Unterteils (27) eine Ausnehmung in Form eines in Umfangsrichtung durch den Schaufelfuss (26) hindurchgehenden Loches (19) vorgesehen ist. 5. Rotor according to claim 4, characterized in that in the blade root (26) above the lower part (27) a recess in the form of a circumferential direction through the blade root (26) through hole (19) is provided. 6. Rotor nach Anspruch 5, dadurch gekennzeichnet, dass das Loch als sich in radialer Richtung erstreckendes Langloch (19) ausgebildet ist.6. Rotor according to claim 5, characterized in that the hole is designed as an elongated hole (19) extending in the radial direction. 7. Rotor nach einem der Ansprüche 4 bis 6, dadurch gekennzeichnet, dass auf der Unterseite des Unterteils (27) des Schaufelfusses (26) Ausnehmungen in Form von Vertiefungen (29) vorgesehen sind. 7. Rotor according to one of claims 4 to 6, characterized in that recesses in the form of depressions (29) are provided on the underside of the lower part (27) of the blade root (26).
EP04804578.5A 2003-12-06 2004-11-26 Rotor for a compressor Expired - Lifetime EP1690011B8 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10357134A DE10357134A1 (en) 2003-12-06 2003-12-06 Rotor for a compressor
PCT/EP2004/053114 WO2005054682A1 (en) 2003-12-06 2004-11-26 Rotor for a compressor

Publications (3)

Publication Number Publication Date
EP1690011A1 true EP1690011A1 (en) 2006-08-16
EP1690011B1 EP1690011B1 (en) 2017-04-26
EP1690011B8 EP1690011B8 (en) 2017-08-02

Family

ID=34625613

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04804578.5A Expired - Lifetime EP1690011B8 (en) 2003-12-06 2004-11-26 Rotor for a compressor

Country Status (5)

Country Link
US (1) US7513747B2 (en)
EP (1) EP1690011B8 (en)
CA (1) CA2548642C (en)
DE (1) DE10357134A1 (en)
WO (1) WO2005054682A1 (en)

Families Citing this family (15)

* 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
EP2320030B1 (en) 2009-11-10 2012-12-19 Alstom Technology Ltd Rotor and rotor blade for an axial turbomachine
EP2546465A1 (en) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Blade root, corresponding blade, rotor disc, and turbomachine assembly
FR2981132B1 (en) * 2011-10-10 2013-12-06 Snecma DISCHARGE COOLING TURBOMACHINE ASSEMBLY
US9109456B2 (en) * 2011-10-26 2015-08-18 General Electric Company System for coupling a segment to a rotor of a turbomachine
WO2014126704A1 (en) * 2013-02-12 2014-08-21 United Technologies Corporation Fan blade including external cavities
EP2860361B1 (en) 2013-10-08 2017-03-01 MTU Aero Engines GmbH Component support and fluid flow engine
US9739159B2 (en) 2013-10-09 2017-08-22 General Electric Company Method and system for relieving turbine rotor blade dovetail stress
KR101920070B1 (en) * 2016-12-23 2018-11-19 두산중공업 주식회사 Locking spacer for rotor blade
FR3100835B1 (en) * 2019-09-17 2022-10-07 Safran Aircraft Engines ROTOR BLADE FOR A TURBOMACHINE
DE102022200592A1 (en) * 2022-01-20 2023-07-20 Siemens Energy Global GmbH & Co. KG turbine blade and rotor
DE102022202368A1 (en) * 2022-03-10 2023-09-14 Siemens Energy Global GmbH & Co. KG Groove design of a disk for a turbine blade, rotor and process
US12055069B2 (en) * 2022-09-20 2024-08-06 Siemens Energy, Inc. System and method for reducing blade hook stress in a turbine blade
US12331658B2 (en) 2023-03-07 2025-06-17 Pratt & Whitney Canada Corp. Test blade for gas turbine engine and method of making
US12134973B2 (en) * 2023-03-28 2024-11-05 Pratt & Whitney Canada Corp. Test blade for gas turbine engine and method of making

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1638648A (en) * 1923-08-13 1927-08-09 Westinghouser Electric And Mfg Turbine-blade fastening
US2010022A (en) * 1931-06-27 1935-08-06 Holzwarth Gas Turbine Co Cooling of gas turbine blades
FR896520A (en) * 1942-08-13 1945-02-23 Sulzer Ag Axial turbo-machine
US2414278A (en) * 1943-07-23 1947-01-14 United Aircraft Corp Turbine blade mounting
GB723813A (en) * 1952-05-30 1955-02-09 Power Jets Res & Dev Ltd Improvements in or relating to bladed rotors for compressors, turbines and like fluid flow machines
GB751740A (en) * 1953-10-02 1956-07-04 English Electric Co Ltd Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors
US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
US3584971A (en) * 1969-05-28 1971-06-15 Westinghouse Electric Corp Bladed rotor structure for a turbine or a compressor
SU418618A1 (en) * 1972-01-25 1974-03-05
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US4875830A (en) 1985-07-18 1989-10-24 United Technologies Corporation Flanged ladder seal
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
JPH08121106A (en) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd Turbine moving blade
DE19615549B8 (en) * 1996-04-19 2005-07-07 Alstom Device for thermal protection of a rotor of a high-pressure compressor
EP0906514B1 (en) * 1996-06-21 2001-10-24 Siemens Aktiengesellschaft Rotor for a turbomachine with blades insertable into grooves and blades for a rotor
FR2758364B1 (en) * 1997-01-16 1999-02-12 Snecma TRIPOD BLADE BLADE DISC
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
DE10120532A1 (en) * 2001-04-26 2002-10-31 Alstom Switzerland Ltd Device and method for fastening a rotor blade along a circumferential groove running within a rotor of an axially flowed through turbomachine
US6832892B2 (en) * 2002-12-11 2004-12-21 General Electric Company Sealing of steam turbine bucket hook leakages using a braided rope seal

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005054682A1 *

Also Published As

Publication number Publication date
EP1690011B8 (en) 2017-08-02
US7513747B2 (en) 2009-04-07
CA2548642A1 (en) 2005-06-16
CA2548642C (en) 2011-04-19
WO2005054682A1 (en) 2005-06-16
US20060228216A1 (en) 2006-10-12
EP1690011B1 (en) 2017-04-26
DE10357134A1 (en) 2005-06-30

Similar Documents

Publication Publication Date Title
DE3413162C2 (en)
DE60318147T2 (en) Turbine blade with blade root notch
EP1690011B1 (en) Rotor for a compressor
EP2320030B1 (en) Rotor and rotor blade for an axial turbomachine
DE19828817C2 (en) Rotor for a turbo machine
EP2434098A1 (en) Blade assembly and corresponding gas turbine
EP1650405A1 (en) Rotor of a turbomachine, in particular gas turbine rotor
DE10358421A1 (en) Rotor for a turbomachine
EP2025867A1 (en) Rotor for an axial flow engine
DE60217039T2 (en) Blade blade foot and disc groove contour
EP3176386B1 (en) Inner shroud assembly, corresponding inner shroud, inner casing and turbomachine
DE102004031270B4 (en) Low-pressure fan with Y-shaped rotor blades
DE102010007335A1 (en) Impeller of a control stage of a steam turbine and steam turbine
EP0712995A1 (en) Bladed rotor
DE102008048261B4 (en) Axial turbomachinery rotor with a paddle lock and method of making the same
DE102007053135A1 (en) Gas turbine component, in particular aircraft engine component or compressor component
WO2001071166A1 (en) Turbine rotor blade
EP3441563B1 (en) Rotor for a turbo engine
EP3183430B1 (en) Turbine rotor blade
EP2322764A1 (en) Turbine blade attachment for a turbomachine
EP3246521B1 (en) Discharge area for guide blade cover and base panels
WO2010043666A1 (en) Axial turbomachine comprising a rotor blade ring and a damping device
EP3159483A1 (en) Blade support for fixing rotor blades of a thermal fluid flow engine
EP2455588B1 (en) Securing module for axial securing of a root of a turbo engine blade
DE102018217597A1 (en) Control wheel arrangement for a steam turbine and method for producing a control wheel arrangement

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060515

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LU MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20091020

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20161118

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LU MC NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 888151

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ANSALDO ENERGIA IP UK LIMITED

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502004015517

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170727

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170726

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170826

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502004015517

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20171121

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20171123

Year of fee payment: 14

Ref country code: IT

Payment date: 20171124

Year of fee payment: 14

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20180129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171126

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180731

Ref country code: BE

Ref legal event code: MM

Effective date: 20171130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171126

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 888151

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171126

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171126

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004015517

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20041126

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20181126

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170426

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181126

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190601

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181126

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170426