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EP0906514A1 - Rotor for a turbomachine with blades insertable into grooves and blades for a rotor - Google Patents

Rotor for a turbomachine with blades insertable into grooves and blades for a rotor

Info

Publication number
EP0906514A1
EP0906514A1 EP97928110A EP97928110A EP0906514A1 EP 0906514 A1 EP0906514 A1 EP 0906514A1 EP 97928110 A EP97928110 A EP 97928110A EP 97928110 A EP97928110 A EP 97928110A EP 0906514 A1 EP0906514 A1 EP 0906514A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
blade
groove
turbomachine
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
EP97928110A
Other languages
German (de)
French (fr)
Other versions
EP0906514B1 (en
Inventor
Carsten Bartsch
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP0906514A1 publication Critical patent/EP0906514A1/en
Application granted granted Critical
Publication of EP0906514B1 publication Critical patent/EP0906514B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • F04D29/38—Blades
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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

Definitions

  • Rotor for a turbo machine with blades which can be fitted in grooves and blade for a rotor
  • the present invention relates to a rotor for a turbomachine with blades which can be fitted in grooves, the grooves being arranged obliquely to the axis of rotation of the rotor, and a blade for a rotor.
  • the object of the present invention is now to reduce the strength problems occurring during the operation of a rotor and to specify a suitable combination of blade root and groove.
  • a rotor for a turbomachine with the features of claim 1 and a blade with the features of claim 6 serve to achieve this object.
  • Advantageous features and combinations result from the features disclosed in the respective dependent claims.
  • a rotor according to the invention with blades which can be fitted in grooves, in which the grooves are inclined to the axis of rotation of the rotor are attached, has at least a part of its blades a blade root with at least two areas with different stiffness, which are adapted, preferably adjusted, to different areas of the stiffness of the groove into which the blade root can be attached.
  • a preferred embodiment provides that a correspondingly adapted region of the blade root and a region of the groove that is stiffer in comparison lie opposite or opposite one another. This ensures that the corresponding stiffness of the groove and
  • Blade root correspond so that there is an overall equalization of the stresses that occur.
  • the flow of force during the transmission of force from the blade root into the groove can be designed inexpensively with a corresponding adaptation. It is also expedient if there is a region of reduced stiffness of the blade root in the groove area of the highest occurring stress, in general in particular in the area of the pointed corners of the groove in the rotor, so that no stresses occur during operation of the turbomachine which could destroy or Material fatigue leads to prolonged operation of the turbomachine.
  • FIG. 1 shows a cross section of a rotor with blades adapted and used according to the invention
  • FIG. 2 shows the rotor from FIG. 1 in a top view without inserted blades
  • FIG. 3 shows a blade root according to the invention
  • FIG. 4 shows the blade root from FIG. 3 used in a rotor disk
  • FIG. 5 shows another foot used according to the invention.
  • the rotor 1 of the turbomachine is preferably formed from rotor disks 1 which are arranged axially one behind the other and are toothed together (Hirth toothing) and are connected to one another by a tie rod, not shown.
  • FIG. 1 shows a section of a rotor disk 1 with blades 3 inserted in grooves 2.
  • Each blade 3 has areas with different stiffness.
  • a recess 5 is made in the blade root 4 in such a way that the groove 2, which has an unevenly high rigidity over its groove depth, is opposite an adapted rigidity of the blade root 4. Since, in particular at the sharp corner 6 (see FIG. 2) of a groove 2, which lies at the end of the groove, increased voltages occur during operation of the gas turbine compressor, in this area the blade root 4 has the recess 5 in such a way that it is connected to it Body is slightly compliant.
  • An advantageous embodiment of the recess 5 provides this in the form of a cutout, which runs obliquely downwards on the end face 8 of the blade root 4.
  • FIG. 2 shows the rotor disk 1 from FIG. 1 in a top view.
  • the grooves 2 are made at an installation angle ⁇ to the axis of rotation of the rotor disk 1, which can be much larger than conventional installation angles due to the adapted blade feet 4. This is particularly important for gas turbines and their compressors with a low mass flow. There larger blade angles and thus larger installation angles ß may be required. This leads in turn to increased local stresses in the groove 2, since there are reduced stiffnesses in particular in the pointed corners 6 due to the increased angles.
  • the pointed corners 6 are places of local high tension. They are shown as the ends of the groove width D indicated in dashed lines and lying inside the rotor disk 1. Seen over the groove length L, it has different ranges of different stresses not only in its depth but also in its extent, which therefore have a different influence on the strength when the blade root 4 is installed and the operation of the turbomachine.
  • FIG. 3 shows a blade root 4 according to the invention with an indicated extension of the blade leaf 7 of the blade 3.
  • This has a recess 5, starting at both end faces 8, which run out of the blade root 4 at an angle downwards.
  • This reduction in material in the blade root 4 leads to a reduced stiffness in areas of the end faces 8 and also in adjacent areas of the blade root 4. Areas adapted in this way have greater elasticity, so that deformations occurring during operation, in particular also at the pointed corners 6, are more favorable to be caught.
  • FIG. 4 shows the blade 3 from FIG. 3 in the installed state.
  • the reduction in material 5 in the blade root 4 leads to the fact that lines of force in the blade root 4 are interrupted and at these points the blade root 4 with respect to loads which arise due to the effective blade forces on the blade blade 7, via the adapted blade root 4 in the central region of the groove length L deflected and received there via the groove 2.
  • FIG. 5 shows a further embodiment of the invention.
  • the built-in blade root 4 has a recess 5 in a rather elongated shape, which pulls downwards out of the blade root 4 towards the center of the groove depth.
  • This recess can not only be achieved by milling, but also by means of a hole or similar machining methods.
  • recesses 5 are to be understood as adaptations to the rigidity of regions of the blade root 4.
  • all measures that change the rigidity of a blade root in at least one area can be used.
  • the invention creates a reduction of local stresses of 30% and more, depending on the size of the recess and the inclination of the installation angle.
  • the advantage of the invention is its low cost, its effectiveness and also the subsequent rigidity adjustment of blade bases in turbo machines that have already been put into operation.
  • Another advantage of the invention is the interchangeability of the blades. In this way, blade feet with and without material reduction can also be mounted together in one rotor disk.

Landscapes

  • 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 rotor (1) for a turbomachine has blades (3) that can be inserted into grooves (2) which are inclined relative to the axis of rotation of the rotor. At least one blade foot (4) has at least two areas with different degrees of stiffness adapted to areas of the groove (2) into which the blade foot (4) is to be inserted and which preferably have the same degrees of stiffness as the corresponding areas of the blade foot. Also disclosed is a blade (3) for a rotor (1). The invention is particularly suitable for gas turbine compressors and strongly reduces local stresses in the grooves.

Description

Beschreibungdescription

Rotor für eine Turbomaschine mit in Nuten anbringbaren Schau¬ feln sowie Schaufel für einen RotorRotor for a turbo machine with blades which can be fitted in grooves and blade for a rotor

Die vorliegende Erfindung betrifft einen Rotor für eine Turbo¬ maschine mit in Nuten anbringbaren Schaufeln, wobei die Nuten schräg zur Rotationsachse des Rotors angebracht sind, sowie eine Schaufel für einen Rotor.The present invention relates to a rotor for a turbomachine with blades which can be fitted in grooves, the grooves being arranged obliquely to the axis of rotation of the rotor, and a blade for a rotor.

Bei Rotoren von Turbomaschinen können aufgrund der Rotation hohe Fliehkräfte auftreten. Bei in einem Rotor anbringbaren Schaufeln besteht zudem die Schwierigkeit, den Rotor so auszu¬ legen, daß er zum einen eine genügende Festigkeit aufweist, zum anderen aber gewisse Abmessungsgrenzen, die von den Belastungen der Turbomaschine abhängen, nicht überschreitet. Die Schaufeln, die in Nuten anbringbar sind, müssen dazu einen geeigneten Schaufelfuß aufweisen. Je nach Konstruktionsprinzip der Ver¬ bindung zwischen Schaufelfuß und Rotor treten zwischen diesen unterschiedliche Spannungen auf. Diese verteilen sich über den Schaufelfuß unterschiedlich. Ein Einflußparameter auf die auf¬ tretenden Spannungen beim Betrieb der Turbomaschine ist bei¬ spielsweise der Einbauwinkel des Schaufelfußes in die Welle.Due to the rotation, high centrifugal forces can occur in turbo machine rotors. In the case of blades which can be fitted in a rotor, there is also the difficulty of designing the rotor in such a way that on the one hand it has sufficient strength, but on the other hand it does not exceed certain dimensional limits which depend on the loads on the turbomachine. The blades, which can be fitted in grooves, must have a suitable blade root for this. Depending on the design principle of the connection between the blade root and the rotor, different stresses occur between them. These are distributed differently over the blade root. An influencing parameter on the stresses occurring during operation of the turbomachine is, for example, the installation angle of the blade root in the shaft.

Aufgabe der vorliegenden Erfindung ist es nun, die im Betrieb eines Rotors auftretenden Festigkeitsprobleme zu mindern und eine dazu geeignete Kombination von Schaufelfuß und Nut anzuge¬ ben.The object of the present invention is now to reduce the strength problems occurring during the operation of a rotor and to specify a suitable combination of blade root and groove.

Zur Lösung dieser Aufgabe dienen ein Rotor für eine Turboma¬ schine mit den Merkmalen des Anspruches 1 und eine Schaufel mit den Merkmalen des Anspruches 6. Vorteilhafte Merkmale und Kom¬ binationen ergeben sich aus den in den jeweils abhängigen An¬ sprüchen offenbarten Merkmalen.A rotor for a turbomachine with the features of claim 1 and a blade with the features of claim 6 serve to achieve this object. Advantageous features and combinations result from the features disclosed in the respective dependent claims.

Ein erfindungsgemäßer Rotor mit in Nuten anbringbaren Schau¬ feln, bei dem die Nuten schräg zu der Rotationsachse des Rotors angebracht sind, weist bei zumindest einem Teil seiner Schau¬ feln einen Schaufelfuß mit mindestens zwei Bereichen mit unter¬ schiedlicher Steifigkeit auf, die an unterschiedliche Bereiche der Steifigkeit der Nut, in die der Schaufelfuß anbringbar ist, angepaßt, vorzugsweise angeglichen, sind.A rotor according to the invention with blades which can be fitted in grooves, in which the grooves are inclined to the axis of rotation of the rotor are attached, has at least a part of its blades a blade root with at least two areas with different stiffness, which are adapted, preferably adjusted, to different areas of the stiffness of the groove into which the blade root can be attached.

Eine bevorzugte Ausgestaltung sieht vor, daß ein entsprechend angepaßter Bereich des Schaufelfußes und ein demgegenüber stei¬ ferer Bereich der Nut aneinander- oder gegenüberliegen. Dadurch wird erreicht, daß entsprechende Steifigkeiten von Nut undA preferred embodiment provides that a correspondingly adapted region of the blade root and a region of the groove that is stiffer in comparison lie opposite or opposite one another. This ensures that the corresponding stiffness of the groove and

Schaufelfuß sich so entsprechen, daß es zu einer Vergleichmä¬ ßigung der auftretenden Spannungen insgesamt kommt. Insbeson¬ dere der Kraftfluß bei der Kraftübertragung vom Schaufelfuß in die Nut ist bei entsprechender Anpassung günstig gestaltbar. Günstig ist es weiterhin, wenn im Nutbereich höchster auftre¬ tender Spannung, im allgemeinen insbesondere im Bereich der spitzen Ecken der Nut in dem Rotor, ein Bereich verminderter Steifigkeit des Schaufelfußes anliegt, so daß bei Betrieb der Turbomaschine keine Spannungen auftreten, die zur Zerstörung oder Materialermüdung über längeren Betrieb der Turbomaschine führen.Blade root correspond so that there is an overall equalization of the stresses that occur. In particular, the flow of force during the transmission of force from the blade root into the groove can be designed inexpensively with a corresponding adaptation. It is also expedient if there is a region of reduced stiffness of the blade root in the groove area of the highest occurring stress, in general in particular in the area of the pointed corners of the groove in the rotor, so that no stresses occur during operation of the turbomachine which could destroy or Material fatigue leads to prolonged operation of the turbomachine.

Eine vorteilhafte Ausgestaltung der Erfindung wird anhand der Ausführungsbeispiele der folgenden Zeichnungen erläutert. Wei- tere vorteilhafte Ausgestaltungen ergeben sich durch geeignete Kombinationen der offenbarten Markmale der Erfindung. Es zei¬ gen:An advantageous embodiment of the invention is explained using the exemplary embodiments of the following drawings. Further advantageous configurations result from suitable combinations of the disclosed features of the invention. It shows:

Figur 1 einen Rotor mit erfindungsgemäß angepaßten und ein- gesetzten Schaufeln im Querschnitt,FIG. 1 shows a cross section of a rotor with blades adapted and used according to the invention,

Figur 2 den Rotor aus Figur 1 in einer Aufsicht ohne einge¬ setzte Schaufeln,FIG. 2 shows the rotor from FIG. 1 in a top view without inserted blades,

Figur 3 einen erfindungsgemäßen Schaufelfuß, Figur 4 den in einer Läuferscheibe eingesetzten Schaufelfuß aus Figur 3,FIG. 3 shows a blade root according to the invention, FIG. 4 shows the blade root from FIG. 3 used in a rotor disk,

Figur 5 einen weiteren erfindungsgemäßen eingesetzten Schau- feifuß.FIG. 5 shows another foot used according to the invention.

Eine vorteilhafte und bevorzugte Ausgestaltung der Erfindung wird im folgenden anhand eines Gasturbinenverdichters, welcher eine bevorzugte Turbomaschine zur Anwendung der Erfindung ist, dargestellt. Der Rotor 1 der Turbomaschine ist vorzugsweise aus axial hintereinander angeordneten, miteinander verzahnten (Hirthverzahnung) , durch einen nicht dargestellten Zuganker miteinander verbundenen Läuferscheiben 1 gebildet.An advantageous and preferred embodiment of the invention is illustrated below with the aid of a gas turbine compressor, which is a preferred turbomachine for the application of the invention. The rotor 1 of the turbomachine is preferably formed from rotor disks 1 which are arranged axially one behind the other and are toothed together (Hirth toothing) and are connected to one another by a tie rod, not shown.

Figur 1 zeigt einen Abschnitt einer Läuferscheibe 1 mit in Nu¬ ten 2 eingesetzten Schaufeln 3. Jede Schaufel 3 weist Bereiche mit unterschiedlicher Steifigkeit auf. Passend dazu ist im Schaufelfuß 4 eine Aussparung 5 so angebracht, daß der Nut 2, die eine ungleichmäßig große Steifigkeit über ihre Nuttiefe aufweist, eine angepaßte Steifigkeit des Schaufelfußes 4 gegen¬ überliegt. Da insbesondere am spitzen Eck 6 (siehe Figur 2) ei¬ ner Nut 2, welches am Nutende liegt, im Betrieb des Gasturbi¬ nenverdichters erhöhte Spannungen auftreten, weist in diesem Bereich der Schaufelfuß 4 die Aussparung 5 so ausgebildet auf, daß er an dieser Stelle leicht nachgiebig ist. Eine vorteil¬ hafte Ausgestaltung der Aussparung 5 sieht diese in der Form einer Ausfräsung vor, die an der Stirnseite 8 des Schaufelfußes 4 schräg nach unten aus diesem herausläuft.FIG. 1 shows a section of a rotor disk 1 with blades 3 inserted in grooves 2. Each blade 3 has areas with different stiffness. Appropriately, a recess 5 is made in the blade root 4 in such a way that the groove 2, which has an unevenly high rigidity over its groove depth, is opposite an adapted rigidity of the blade root 4. Since, in particular at the sharp corner 6 (see FIG. 2) of a groove 2, which lies at the end of the groove, increased voltages occur during operation of the gas turbine compressor, in this area the blade root 4 has the recess 5 in such a way that it is connected to it Body is slightly compliant. An advantageous embodiment of the recess 5 provides this in the form of a cutout, which runs obliquely downwards on the end face 8 of the blade root 4.

Figur 2 zeigt die Läuferscheibe 1 aus der Figur 1 in einer Auf¬ sicht. Die Nuten 2 sind in einem Einbauwinkel ß zur Rotati¬ onsachse der Läuferscheibe 1 angebracht, der auf Grund der an¬ gepaßten Schaufelfüße 4 sehr viel größer sein kann gegenüber herkömmlichen Einbauwinkeln. Dieses spielt insbesondere für Gasturbinen und deren Verdichter mit geringem Massenstrom eine besondere Rolle. Dort können größere Schaufelwinkel und damit größere Einbauwinkel ß erforderlich sein. Dieses führt wiederum zu erhöhten lokalen Spannungen in der Nut 2, da insbesondere in den spitzen Ecken 6 durch die erhöhten Winkel reduzierte Stei- figkeiten vorliegen. Die spitzen Ecken 6 sind Orte lokaler ho¬ her Spannung. Sie sind als Enden der gestrichelt angedeuteten, in der Läuferscheibe 1 innenliegenden Nutbreite D eingezeich¬ net. Über die Nutlänge L gesehen, besitzt diese nicht nur in ihrer Tiefe, sondern auch in ihrer Erstreckung unterschiedliche Bereiche unterschiedlicher Spannungen, die daher unterschiedli¬ chen Einfluß auf die Festigkeit bei eingebautem Schaufelfuß 4 und Betrieb der Turbomaschine haben.FIG. 2 shows the rotor disk 1 from FIG. 1 in a top view. The grooves 2 are made at an installation angle β to the axis of rotation of the rotor disk 1, which can be much larger than conventional installation angles due to the adapted blade feet 4. This is particularly important for gas turbines and their compressors with a low mass flow. There larger blade angles and thus larger installation angles ß may be required. This leads in turn to increased local stresses in the groove 2, since there are reduced stiffnesses in particular in the pointed corners 6 due to the increased angles. The pointed corners 6 are places of local high tension. They are shown as the ends of the groove width D indicated in dashed lines and lying inside the rotor disk 1. Seen over the groove length L, it has different ranges of different stresses not only in its depth but also in its extent, which therefore have a different influence on the strength when the blade root 4 is installed and the operation of the turbomachine.

Figur 3 zeigt einen erfindungsgemäßen Schaufelfuß 4 mit ange¬ deuteter Verlängerung des Schaufelblattes 7 der Schaufel 3. Dieser weist eine Aussparung 5 beginnend jeweils an beiden Stirnflächen 8 auf, die schräg nach unten aus dem Schaufelfuß 4 herauslaufen. Diese Materialverminderung im Schaufelfuß 4 führt zu einer verminderten Steifigkeit in Bereichen der Stirnflächen 8 und auch in anliegenden Bereichen des Schaufelfußes 4. Derar¬ tig angepaßte Bereiche weisen eine größere Elastizität auf, so daß auftretende Verformungen im Betrieb, insbesondere auch an den spitzen Ecken 6 günstiger aufgefangen werden.FIG. 3 shows a blade root 4 according to the invention with an indicated extension of the blade leaf 7 of the blade 3. This has a recess 5, starting at both end faces 8, which run out of the blade root 4 at an angle downwards. This reduction in material in the blade root 4 leads to a reduced stiffness in areas of the end faces 8 and also in adjacent areas of the blade root 4. Areas adapted in this way have greater elasticity, so that deformations occurring during operation, in particular also at the pointed corners 6, are more favorable to be caught.

Figur 4 zeigt die Schaufel 3 aus Figur 3 in eingebautem Zu¬ stand. Die Materialverminderung 5 im Schaufelfuß 4 führt dazu, daß Kraftlinien im Schaufelfuß 4 unterbrochen werden und an diesen Stellen der Schaufelfuß 4 gegenüber Belastungen, die auf Grund der wirkenden Schaufelkräfte am Schaufelblatt 7 aufkom¬ men, über den angepaßten Schaufelfuß 4 in den mittleren Bereich der Nutlänge L umgelenkt und dort über die Nut 2 aufgenommen werden.FIG. 4 shows the blade 3 from FIG. 3 in the installed state. The reduction in material 5 in the blade root 4 leads to the fact that lines of force in the blade root 4 are interrupted and at these points the blade root 4 with respect to loads which arise due to the effective blade forces on the blade blade 7, via the adapted blade root 4 in the central region of the groove length L deflected and received there via the groove 2.

Figur 5 zeigt eine weitere Ausführungsform der Erfindung. Der eingebaute Schaufelfuß 4 weist eine Aussparung 5 in einer eher länglichen Form auf, die sich zur Mitte der Nuttiefe hin nach unten aus dem Schaufelfuß 4 herauszieht. Diese Aussparung kann nicht nur mittels Fräsung sondern auch über eine Bohrung oder ähnliche spanende Bearbeitungsweisen erzielt werden. Im Sinne 5 der Erfindung sind aber nicht nur Aussparungen 5 als Anpassun¬ gen der Steifigkeit von Bereichen des Schaufelfußes 4 zu ver¬ stehen. Vielmehr sind alle Maßnahmen, die die Steifigkeit eines Schaufelfußes in mindestens einem Bereich ändern, anwendbar. Beispielsweise ist auch das Einsetzen oder Verarbeiten eines anderen Materials im Schaufelfuß möglich, welches diesem gegen¬ über eine höhere Elastizität aufweist. Insbesondere günstig ist es, daß bei Verdichtern bzw. allgemein Turbomaschinen, die in wechselndem Betrieb gefahren werden, eine Anpassung der Berei- ehe des Schaufelfußes 4 an denjenigen Betriebsbereich der Tur¬ bomaschine angelehnt ist, in dem dieser überwiegend gefahren wird.Figure 5 shows a further embodiment of the invention. The built-in blade root 4 has a recess 5 in a rather elongated shape, which pulls downwards out of the blade root 4 towards the center of the groove depth. This recess can not only be achieved by milling, but also by means of a hole or similar machining methods. For the purpose of 5 of the invention, however, not only recesses 5 are to be understood as adaptations to the rigidity of regions of the blade root 4. Rather, all measures that change the rigidity of a blade root in at least one area can be used. For example, it is also possible to insert or process another material in the blade root which has a higher elasticity than this. It is particularly favorable that, in the case of compressors or, in general, turbomachines which are operated in alternating operation, an adaptation of the area of the blade root 4 to the operating region of the turbomachine in which the latter is predominantly operated is based.

Die Erfindung schafft bei diesem angeführten Beispiel je nach Größe der Aussparung und Schräge des Einbauwinkels eine Redu¬ zierung von lokalen Spannungen von 30 % und mehr. Der Vorteil der Erfindung ist ihr geringer Kostenaufwand, ihre Effektivität sowie auch die nachträgliche Steifigkeitsanpassung von Schau¬ felfüßen bei schon in Betrieb genommenen Turbomaschinen. Ein weiterer Vorteil der Erfindung ist die Austauschbarkeit der Schaufeln. So können auch Schaufelfüße mit und ohne Material- Verminderung in einer Läuferscheibe gemeinsam angebracht sein. In this example, the invention creates a reduction of local stresses of 30% and more, depending on the size of the recess and the inclination of the installation angle. The advantage of the invention is its low cost, its effectiveness and also the subsequent rigidity adjustment of blade bases in turbo machines that have already been put into operation. Another advantage of the invention is the interchangeability of the blades. In this way, blade feet with and without material reduction can also be mounted together in one rotor disk.

Claims

Patentansprüche claims 1. Rotor (1) für eine Turbomaschine mit einer Rotationsachse (la) , insbesondere einen Turboverdichter, mit in Nuten (2) an- bringbaren Schaufeln (3) , wobei die Nuten (2) schräg zur Rota¬ tionsachse (la) angebracht sind, d a d u r c h g e k e n n z e i c h n e t, daß zumindest ein Schaufelfuß (4) mindestens zwei Bereiche mit unterschiedlicher Steifigkeit aufweist, die an unterschiedliche Bereiche der Steifigkeit der Nut (2) , in die der Schaufelfuß (4) anbringbar ist, angepaßt, vorzugsweise angeglichen, sind.1. Rotor (1) for a turbomachine with an axis of rotation (la), in particular a turbocompressor, with blades (3) which can be fitted in grooves (2), the grooves (2) being arranged obliquely to the axis of rotation (la) , characterized in that at least one blade root (4) has at least two areas with different stiffness, which are adapted, preferably adjusted, to different areas of the stiffness of the groove (2) into which the blade root (4) can be attached. 2. Rotor (1) nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, daß ein entspre- chend angepaßter Bereich des Schaufelfußes (4) und ein demge¬ genüber steiferer Bereich der Nut (2) aneinander- oder gegen¬ überliegen.2. The rotor (1) according to claim 1, which also has a correspondingly adapted area of the blade root (4) and a stiffer area of the groove (2) in relation to one another or opposite one another. 3. Rotor (1) nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, daß an einem Nut- bereich höchster auftretender Spannung, insbesondere bei Be¬ trieb der Turbomaschine, ein Bereich verminderter Steifigkeit des Schaufelfußes (4) anliegt.3. The rotor (1) according to claim 1 or 2, which also means that a region of reduced stiffness of the blade root (4) is present in a groove area of the highest voltage occurring, in particular when the turbomachine is operating. 4. Rotor (1) nach Anspruch 1, 2 oder 3, d a d u r c h g e k e n n z e i c h n e t , daß an einem Nutende, insbesondere an einer spitzen Ecke (6) , ein Bereich verminderter Steifigkeit des eingebauten Schaufelfußes (4) an¬ liegt.4. rotor (1) according to claim 1, 2 or 3, d a d u r c h g e k e n n z e i c h n e t that at a groove end, in particular at an acute corner (6), an area of reduced stiffness of the built-in blade root (4) is applied. 5. Rotor (1) nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß eine Anglei- chung zwischen den Belastungen an der Nut (2) und den Belastun¬ gen am Schaufelfuß (4) entsprechend den Kräften ausgelegt ist, die in dem überwiegend gefahrenen Betriebsbereich der Turboma¬ schine herrschen. 75. Rotor (1) according to one of the preceding claims, characterized in that an alignment between the loads on the groove (2) and the conditions on the blade root (4) is designed according to the forces which are in the predominantly driven operating area the turbo machine prevail. 7 6. Schaufel (3) für einen Rotor (1) einer Turbomaschine, ins¬ besondere nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß der Schaufel- fuß (4) zusätzlich zu seiner an eine Nutgeometrie angepaßten Form eine Steifigkeitsminderung aufweist, insbesondere eine Ma¬ terialverminderung (5) , vorzugsweise mindestens eine Aussparung (5) .6. Blade (3) for a rotor (1) of a turbomachine, in particular according to one of the preceding claims, characterized in that the blade base (4) has a reduction in rigidity, in particular a dimension, in addition to its shape adapted to a groove geometry material reduction (5), preferably at least one recess (5). 7. Schaufel (3) nach Anspruch 6, d a d u r c h g e k e n n z e i c h n e t, daß eine Ausspa¬ rung (5) , vorzugsweise eine Bohrung oder Ausfräsung, von der Stirnseite (8) des Schaufelfußes (4) in dessen Inneres ver¬ läuft. 7. blade (3) according to claim 6, d a d u r c h g e k e n n z e i c h n e t that a recess (5), preferably a bore or milling, runs from the end face (8) of the blade root (4) in the interior thereof.
EP97928110A 1996-06-21 1997-06-09 Rotor for a turbomachine with blades insertable into grooves and blades for a rotor Expired - Lifetime EP0906514B1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE19624924 1996-06-21
DE19624924 1996-06-21
DE19642537 1996-10-15
DE19642537 1996-10-15
PCT/DE1997/001159 WO1997049921A1 (en) 1996-06-21 1997-06-09 Rotor for a turbomachine with blades insertable into grooves and blades for a rotor

Publications (2)

Publication Number Publication Date
EP0906514A1 true EP0906514A1 (en) 1999-04-07
EP0906514B1 EP0906514B1 (en) 2001-10-24

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Application Number Title Priority Date Filing Date
EP97928110A Expired - Lifetime EP0906514B1 (en) 1996-06-21 1997-06-09 Rotor for a turbomachine with blades insertable into grooves and blades for a rotor

Country Status (6)

Country Link
US (1) US6065938A (en)
EP (1) EP0906514B1 (en)
JP (1) JP2000512707A (en)
KR (1) KR20000022064A (en)
DE (1) DE59705094D1 (en)
WO (1) WO1997049921A1 (en)

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Also Published As

Publication number Publication date
DE59705094D1 (en) 2001-11-29
JP2000512707A (en) 2000-09-26
WO1997049921A1 (en) 1997-12-31
US6065938A (en) 2000-05-23
KR20000022064A (en) 2000-04-25
EP0906514B1 (en) 2001-10-24

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