EP1733124A1 - Non-positive-displacement machine and rotor for a non-positive-displacement machine - Google Patents

Non-positive-displacement machine and rotor for a non-positive-displacement machine

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Publication number
EP1733124A1
EP1733124A1 EP05716050A EP05716050A EP1733124A1 EP 1733124 A1 EP1733124 A1 EP 1733124A1 EP 05716050 A EP05716050 A EP 05716050A EP 05716050 A EP05716050 A EP 05716050A EP 1733124 A1 EP1733124 A1 EP 1733124A1
Authority
EP
European Patent Office
Prior art keywords
rotor
groove
annular groove
compressor
blade
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
EP05716050A
Other languages
German (de)
French (fr)
Other versions
EP1733124B1 (en
Inventor
Bernard Becker
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
Original Assignee
Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05716050A priority Critical patent/EP1733124B1/en
Publication of EP1733124A1 publication Critical patent/EP1733124A1/en
Application granted granted Critical
Publication of EP1733124B1 publication Critical patent/EP1733124B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2250/293—Three-dimensional machined; miscellaneous lathed, e.g. rotation symmetrical
    • 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

Definitions

  • the invention relates to a rotor for a turbomachine according to the preamble of claim 1 and a turbomachine with a rotor.
  • a fastening of rotor blades of a compressor to the disk of the compressor rotor is known from US Pat. No. 5,211,407, in which the rotor blades are secured against axial displacement by means of an annular holding segment.
  • the disk has hooks which extend radially inwards on the end face between two moving blade holding grooves and into which a holding segment is hooked.
  • the holding segment forms a stop for the moving blade held in the holding groove and thus secures it against axial displacement.
  • DE 26 06 565 describes a method for assembling rotor blades in a disk.
  • the end regions of a platform of a moving blade are deformed in such a way that, after a caulking process, the material regions of the platform, which face the outer circumference of the disc, rest firmly against the disc in order to achieve friction damping.
  • CH 489 698 A shows a device for securing rotor blades of turbines, which are held in a form-fitting manner in axial grooves.
  • a hammer-shaped groove with undercuts is arranged on the front side of a shaft bundle in such a way that the undercut cuts from below the groove base of the retaining grooves of the rotor blades.
  • a securing element can be inserted into the hammer-shaped groove after the installation of the rotor blades and engages in a correspondingly shaped recess in the blade root. It is also known that blade roots of rotor blades of a compressor are secured by plastic deformation against axial displacement.
  • FIG. 7 shows a section of a compressor disk 19 according to the prior art.
  • Retaining grooves 21 are provided in the outer circumference 23 of the compressor disk 19 for receiving rotor blades.
  • recesses 29 are arranged on the two end faces 25 of the compressor disk 23, each of which merges into the base 27 of the radially outer retaining groove 21.
  • FIG. 8 shows the cross section through a compressor disk 19 according to FIG. 7 along the section VIII-VIII.
  • the recess 29 is designed as a chamfer 30 with an angle of 45 °.
  • the protrusion assumes a rounded shape on its side facing the chamfer during the caulking process, this protrudes only partially against the chamfer, which can lead to a lower holding force.
  • the solution to the problem provides that at least in one end face of the Wellenbun ⁇ -s is provided an axially extending annular groove coaxial to the axis of rotation of the rotor, which intersects the bottom of the groove of each holding groove and is plastically displaced as deformation material of the blade root of the rotor blade into the annular groove ,
  • the invention is based on the knowledge that a receiving area, which lies below the groove base of the holding groove in the coaxial annular groove and serves to receive the material of the blade root, has a more favorable shape for the projection formed by the caulking.
  • the material of the blade root which is plastically deformed after caulking, then lies better against the annular groove, so that a lossy axial play of the blade is avoided. Additional fastening components are not required.
  • each chamfer has been produced in a separate milling process in the prior art.
  • the ring groove can be produced during the turning process with which the contour of the end face is produced.
  • the receiving area is created below each holding groove, into which the material of the blade root can be displaced. This reduces the manufacturing cost and the manufacturing time of the rotor.
  • the annular groove has an annular groove base and two flanks, with each flank the annular groove merges into the base of the annular groove. This avoids notch stresses in the shaft collar that would be generated in the event of a sharp transition from the flank to the ring groove base.
  • a projection can be formed by the control process, which has an angle of 50 ° to 90 ° to the groove base of the holding groove. The most effective portion of the projection is that which is formed at an angle of 90 ° to the groove base of the holding groove.
  • the Tdfellenbund is expediently formed by a disc, in particular by a compressor disc.
  • the ring groove can be created when the compressor disc is rotated, so that there is no need for individual milling j of the chamfer.
  • the blade is arranged with its blade root complementary to the retaining groove in the respective retaining groove, material of the blade root protruding into the annular groove. After the rotor blade has been introduced into the retaining groove, material of the blade root is deformed by prying into the annular groove, thus creating a mechanical lock against axial displacement.
  • the retaining groove can be dovetail or fir-tree-shaped in cross section.
  • each end face has one Slice an annular groove on :.
  • each side of the blade root facing the end face is deformed by a caulking process and the rotor blade is secured on both sides against axial displacement in both directions.
  • the object directed to the turbomachine is achieved by equipping it with a rotor according to one of claims 1 to 7.
  • the advantages listed for the rotor also apply analogously to the turbomachine, in particular if it is a compressor.
  • FIG. 1 shows a compressor disk according to the invention in a perspective view
  • FIG. 2 shows a section through a compressor disk according to FIG. 1,
  • FIG. 3 shows a section through a compressor disk according to FIG. 1 with a plastically deformed blade root of a moving blade
  • FIG. 4 shows a partial side view of the compressor disk according to FIG. 3,
  • Figure 7 is a perspective view of the compressor disc with holding grooves according to the prior art.
  • the gas turbine essentially has a compressor, a combustion chamber and a turbine unit along a rotor.
  • the air drawn in and compressed by the compressor is mixed with a fuel and burned in the combustion chamber to form a hot gas, which then relaxes in the turbine unit on the rotor of the gas turbine in a work-performing manner.
  • the rotor of the gas turbine drives the compressor and a working machine, for example a generator.
  • two blade rings each form a compressor stage, wherein, viewed in the direction of flow, an adjustable ring attached to the rotor from rotor blades follows a fixed ring of guide vanes.
  • two blade rings form a turbine stage, a fixed guide blade ring, viewed in the direction of flow, followed by a rotatable ring attached to the rotor from rotor blades.
  • the rotor of the gas turbine has a disk or a shaft collar for each rotor blade ring, to which the rotor blades of the respective ring are fastened.
  • FIG. 1 shows a segment of such a disc as a compressor disc 19 according to the invention.
  • the compressor disc forms a shaft collar. 22, which has on its outer periphery 23 transversely extending retaining grooves 21 for receiving blades 16.
  • an annular groove 31 is provided which is arranged coaxially to the fulcrum of the rotor and extends in the axial direction A.
  • the annular groove 31 can be produced during the manufacture of the compressor disc 19 when the end face 25 is rotated and thus within the previous work step.
  • the annular groove 31 intersects each holder 21 in the region of the groove base 27.
  • a receiving region 34 is thus available, into which the material of the blade root 33 can be plastically displaced, for example by prying.
  • FIG. 2 shows a section through the cross section of a compressor disk 19 according to FIG. 1.
  • the shaft collar 22 formed by the compressor disk 19 has the annular groove 31 which is U-shaped in cross section on each end face 25.
  • Each annular groove 31 extends with a depth T in the axial direction, so that the axial length of the groove base 27 of the holding groove 21 is shortened compared to a disk thickness D (see FIG. 1).
  • the annular groove 31 has a flank 37 in cross section as a side wall, which has a rounding 41, which as
  • Radius, ellipse, concave shape or the like can be formed, into the annular groove base 39.
  • the annular groove 31 is provided on both end faces 25 of the compressor disc 19, so that each rotor blade 16 can be axially secured by two prying processes.
  • FIG. 3 shows the section through a compressor disk 19 with a rotor blade 16, the blade root 33 of which is already plastically deformed.
  • the material of the blade root 33 protrudes as
  • the annular groove base 39 serves as an abutment for the projection 35, which thus secures the moving blade 16 against axial displacement.
  • FIG. 4 shows a detail from the side view of the compressor disk 19 according to FIG. 3.
  • the blade root 33 of the blade 16 is deformed by the caulking process.
  • a caulking 36 is arranged in the lower region of the blade root 33 and covers approximately a third of the width of the blade root 33.
  • An annular groove 31 to the groove base 27 is tangent, which forms a tangent angle ⁇ with the groove base 27 of the holding groove 21. closes. This lies in an imaginary plane that is spanned by the axis of rotation of the rotor and by the radial direction of the rotor, which runs through a holding groove 21.
  • the tangent angle ⁇ has a size of 50 ° to 90 °.

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  • 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 for a non-positive-displacement machine, particularly a rotor for a compressor of a gas turbine, on which at least one shaft collar (22) with an outer periphery (23) and with two radially extending faces (25) are placed. The rotor also comprises a multitude of retaining grooves (21) for moving blades (16), said retaining grooves being provided on the outer periphery (23) and extending transversal to the peripheral direction, and each retaining groove (21) has a groove bottom (27). In order to provide a rotor for a non-positive-displacement machine that makes it possible to reduce flow losses while having a simple geometrical design of the attachment of moving blades, the invention provides that an annular groove (31), which extends in an axial direction and which is coaxial to the rotation axis of the rotor, is provided at least on one face (25) of the shaft collar (22). This annular groove is joined to the groove bottom (27) of the retaining grooves (21) whereby enabling material of the foot (33) of the moving blade (16) to be plastically forced into the annular groove (31).

Description

Beschreibungdescription
Strömungsmaschine und Rotor für eine StrömungsmaschineFluid machine and rotor for a fluid machine
Die Erfindung betrifft einen Rotor für eine Strömungsmaschine nach dem Oberbegriff des Anspruchs 1 und eine Strömungsmaschine mit einem Rotor.The invention relates to a rotor for a turbomachine according to the preamble of claim 1 and a turbomachine with a rotor.
Aus der US 5,211,407 ist eine Befestigung von Laufschaufeln eines Verdichters an der Scheibe des Verdichterrotors bekannt, bei der die Sicherung der Laufschaufeln gegen axiales Verschieben durch ein ringförmiges Haltesegment erfolgt . Die Scheibe weist dazu an der Stirnseite zwischen zwei Laufschaufelhaltenuten sich radial nach innen erstreckende Haken auf, in die ein Haltesegment eingehakt wird. Das Haltesegment bildet einen Anschlag für die in der Haltenut gehaltene Laufschaufel und sichert so diese gegen axiales Verschieben.A fastening of rotor blades of a compressor to the disk of the compressor rotor is known from US Pat. No. 5,211,407, in which the rotor blades are secured against axial displacement by means of an annular holding segment. For this purpose, the disk has hooks which extend radially inwards on the end face between two moving blade holding grooves and into which a holding segment is hooked. The holding segment forms a stop for the moving blade held in the holding groove and thus secures it against axial displacement.
Zu dem ist in der DE 26 06 565 ein Verfahren zur Montage von Laufschaufeln in einer Scheibe beschrieben. Dabei werden die stirnseitigen Bereiche einer Plattform einer Laufschaufel derartig verformt, dass nach einem Anstemmvorgang die Materialbereiche der Plattform, welche dem Außenumfang der Scheibe zugewandt sind, an der Scheibe fest anliegen, um eine Rei- bungsdämpfung zu erzielen.In addition, DE 26 06 565 describes a method for assembling rotor blades in a disk. The end regions of a platform of a moving blade are deformed in such a way that, after a caulking process, the material regions of the platform, which face the outer circumference of the disc, rest firmly against the disc in order to achieve friction damping.
Außerdem zeigt die CH 489 698 A eine Vorrichtung zur Sicherung von einzeln in axialen Nuten formschlüssig gehaltenen Laufschaufeln von Turbinen. An der Stirnseite eines Wellen- bundes ist eine hammerförmige Nut mit Hinterschneidungen derartig angeordnet, dass die Hinterschneidung von unten den Nutgrund der Haltenuten der Laufschaufeln schneidet. Zur Axialsicherung der Laufschaufeln ist nach der Montage der Laufschaufeln in die hammerförmige Nut ein Sicherungselement ein- schiebbar, welches in eine im Schaufelfuß korrespondierend geformte Ausnehmung eingreift. Ferner ist bekannt, class Laufschaufelfüße von Laufschaufeln eines Verdichters duirch plastisches Verformen gegen axiale Verschiebung gesicheirt werden.In addition, CH 489 698 A shows a device for securing rotor blades of turbines, which are held in a form-fitting manner in axial grooves. A hammer-shaped groove with undercuts is arranged on the front side of a shaft bundle in such a way that the undercut cuts from below the groove base of the retaining grooves of the rotor blades. To secure the rotor blades axially, a securing element can be inserted into the hammer-shaped groove after the installation of the rotor blades and engages in a correspondingly shaped recess in the blade root. It is also known that blade roots of rotor blades of a compressor are secured by plastic deformation against axial displacement.
Figur 7 zeigt dazu einen Ausschnitt einer Verdichterscheibe 19 nach dem Stand der Technik. Zur Aufnahme von Laufschaufein sind Haltenuten 21 in. dem Außenumfang 23 der Verdichterscheibe 19 vorgesehen. Ferner sind Ausnehmungen 29 an den beiden Stirnseiten 25 der Verdichterscheibe 23 angeordnet, die jeweils in den Ntαtgrund 27 der radial außen liegenden Haltenut 21 übergehen.7 shows a section of a compressor disk 19 according to the prior art. Retaining grooves 21 are provided in the outer circumference 23 of the compressor disk 19 for receiving rotor blades. Furthermore, recesses 29 are arranged on the two end faces 25 of the compressor disk 23, each of which merges into the base 27 of the radially outer retaining groove 21.
Figur 8 zeigt den Querschnitt durch eine Verdichterscheibe 19 gemäß Figur 7 entlang des Schnitts VIII-VIII. Die Ausnehmung 29 ist als Fase 30 mit einem Winkel von 45° ausgebildet.FIG. 8 shows the cross section through a compressor disk 19 according to FIG. 7 along the section VIII-VIII. The recess 29 is designed as a chamfer 30 with an angle of 45 °.
Nach dem Einbringen einer Laufschaufel 16 wird beidseitig durch einen Anstemmvorgang Material des Laufschaufelfußes 33 in den Bereich der Fase 30 plastisch verformt. Der so am Laufschaufelfuß 33 gebildete Vorsprung sichert dann die Laufschaufel 16 gegen axiales Verschieben, indem der Vorsprung an der zur Verschieberichtung um 45° geneigten Fase 30 anliegt.After the introduction of a moving blade 16, material of the moving blade foot 33 is plastically deformed on both sides in the region of the chamfer 30 by means of a caulking process. The projection thus formed on the blade root 33 then secures the blade 16 against axial displacement, in that the projection rests on the chamfer 30 which is inclined at 45 ° to the direction of displacement.
Da jedoch beim Anstemmvorgang der Vorsprung an seiner der Fase zugewandten Seite eine abgerundete Form annimmt, liegt dieser nur teilweise an der Fase an, was zu einer geringeren Haltekraft führen kann.However, since the protrusion assumes a rounded shape on its side facing the chamfer during the caulking process, this protrudes only partially against the chamfer, which can lead to a lower holding force.
Beim Anfahren des kalten Verdichters und nach dem Abschalten des warmen Verdichter-s können durch unterschiedliche Wärmedehnungen von Laufscb-aufel und Scheibe axiale gerichtete Spannungen in der Laufschaufelbefestigung entstehen, die bei wiederholtem Auftreten den Vorsprung verformen können. Dieser auch als "Blade Walk" bekannte Effekt kann zu dem axialen Spiel der Verdichterlaufschaufein und dieses zu Strömungsverlusten im Verdichter führen. Daher ist es Aufgabe der Erfindung, einen Rotor für eine Strömungsmaschine anzugeben, der ohne zusätzliche Bauteile eine sicherere Befestigung von Laufschaufeln bei einfacher geometrischer Ausgestaltung am Rotor ermöglicht.When the cold compressor is started up and after the warm compressor is switched off, different thermal expansions of the rotor blade and disc can result in axial stresses in the rotor blade attachment, which can deform the projection if it occurs repeatedly. This effect, also known as "blade walk", can lead to the axial play of the compressor blades and this can lead to flow losses in the compressor. It is therefore an object of the invention to provide a rotor for a turbomachine which enables a more secure attachment of rotor blades with a simple geometric design to the rotor without additional components.
Die auf den Rotor gerichtete Aufgabe wird durch die Merkmale des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.The object directed to the rotor is achieved by the features of claim 1. Advantageous refinements are specified in the subclaims.
Die Lösung der Aufgabe sieht vor, dass zumindest in einer Stirnfläche des Wellenbunα-s eine sich in Axialrichtung erstreckende zur Drehachse des Rotors koaxiale Ringnut vorgesehen ist, die den Nutgrund jeder Haltenut schneidet und als Verformung Material des Schaufelfußes der Laufschaufei in die Ringnut plastisch verdrängt ist.The solution to the problem provides that at least in one end face of the Wellenbunα-s is provided an axially extending annular groove coaxial to the axis of rotation of the rotor, which intersects the bottom of the groove of each holding groove and is plastically displaced as deformation material of the blade root of the rotor blade into the annular groove ,
Die Erfindung geht dabei von der Erkenntnis aus, dass ein Aufnahmebereich, welcher unterhalb des Nutgrunds der Haltenut in der koaxialen Ringnut liegt und zur Aufnahme des Materials des Schaufelfußes dient, eine für den durch die Anstemmung geformten Vorsprung günstigere Form aufweist. Das nach einer Anstemmung plastisch verformte Material des Laufschaufelfußes liegt dann besser an der Ringnut an, so dass ein verlustbehaftetes axiales Spiel de-tr Laufschaufei vermieden wird. Zusätzliche Befestigungsbauteile entfallen.The invention is based on the knowledge that a receiving area, which lies below the groove base of the holding groove in the coaxial annular groove and serves to receive the material of the blade root, has a more favorable shape for the projection formed by the caulking. The material of the blade root, which is plastically deformed after caulking, then lies better against the annular groove, so that a lossy axial play of the blade is avoided. Additional fastening components are not required.
Bisher wurde beim Stand der Technik jede Fase in einem separaten Fräsvorgang hergestellt . Die Ringnut hingegen kann während des Drehvorgangs hergestellt werden, mit dem die Kontur der Stirnseite hergestellt wird. Somit wird in nur einem Herstellungsvorgang unterhalb jeder Haltenut der Aufnahmebereich geschaffen, in den Material des Schaufelfußes verdrängbar ist. Dies reduziert die Herstellungskosten und die Herstellungszeit des Rotors.So far, each chamfer has been produced in a separate milling process in the prior art. The ring groove, on the other hand, can be produced during the turning process with which the contour of the end face is produced. Thus, in just one manufacturing process, the receiving area is created below each holding groove, into which the material of the blade root can be displaced. This reduces the manufacturing cost and the manufacturing time of the rotor.
Im Rahmen einer vorteilhaften Weiterbildung weist die Ringnut einen Ringnutgrund und zwei Flanken auf, bei der jede Flanke der Ringnut über eine Rundung in den Ringnutgrund übergeht . Hierdurch werden Kerbspanm-mgen in dem Wellenbund vermieden, die bei einem spitzen Übergang von Flanke zum Ringnutgrund erzeugt werden würden.In the context of an advantageous development, the annular groove has an annular groove base and two flanks, with each flank the annular groove merges into the base of the annular groove. This avoids notch stresses in the shaft collar that would be generated in the event of a sharp transition from the flank to the ring groove base.
An der vom Nutgrund der Haltenut und der von der Innenfläche der Ringnut gebildeten Scb-nittkante schließen diese einen Tangentenwinkel ein, der in einer Ebene liegt, die vom Radius des Rotors und der Drehachse des Rotors aufgespannt wird. Da- bei kann der Nutgrund der Haltenut die radial weiter innen liegende Rundung der Ringnut schneiden. Der Tangentenwinkel kann auf Grund der Rundung dabei in einer Größenordnung zwischen 50° und 90° liegen, so dass die Form des Aufnahmebe- reichs der Form des Vorsprungs geometrisch sehr nahe kommt. Somit kann durch den Ansteτnmvorgang ein Vorsprung geformt werden, der einem Winkel von 50° bis 90° zum Nutgrund der Haltenut aufweist. Der wirksamste Anteil des Vorsprungs ist der, welcher in einen Winkel von 90° zum Nutgrund der Haltenut ausgebildet ist.At the cutting edge formed by the groove base of the holding groove and the cutting edge formed by the inner surface of the annular groove, these enclose a tangent angle that lies in a plane that is spanned by the radius of the rotor and the axis of rotation of the rotor. The groove base of the holding groove can cut the radially inner curvature of the ring groove. Because of the rounding, the tangent angle can be in the order of magnitude between 50 ° and 90 °, so that the shape of the receiving area comes very close geometrically to the shape of the projection. Thus, a projection can be formed by the control process, which has an angle of 50 ° to 90 ° to the groove base of the holding groove. The most effective portion of the projection is that which is formed at an angle of 90 ° to the groove base of the holding groove.
Zweckmäßigerweise ist der Ttfellenbund durch eine Scheibe, insbesondere durch eine Verdichterscheibe gebildet. Die Ringnut kann beim Drehen der Verdichterscheibe hergestellt werden, so dass das einzelne Fräsen j der Fase entfällt.The Tdfellenbund is expediently formed by a disc, in particular by a compressor disc. The ring groove can be created when the compressor disc is rotated, so that there is no need for individual milling j of the chamfer.
In einer vorteilhaften Ausgestaltung ist die Laufschaufel mit ihrem zur Haltenut komplementär ausgebildetem Schaufelfuß in der jeweiligen Haltenut angeordnet, wobei Material des Schaufelfußes in die Ringnut hineinragt. Nach dem Einbringen der Laufschaufei in die Haltenut wird Material des Schaufelfußes durch Anstemmen in die Ringnut hinein verformt und somit eine mechanische Sicherung gegen axiales Verschieben erzeugt. Die Haltenut kann im Querschnitt schwalbenschwanzförmig oder tannenbaumförmig sein.In an advantageous embodiment, the blade is arranged with its blade root complementary to the retaining groove in the respective retaining groove, material of the blade root protruding into the annular groove. After the rotor blade has been introduced into the retaining groove, material of the blade root is deformed by prying into the annular groove, thus creating a mechanical lock against axial displacement. The retaining groove can be dovetail or fir-tree-shaped in cross section.
Damit die Laufschaufel gegen axiales Verschieben in beide Richtungen gesichert ist, weist jede Stirnfläche einer Scheibe eine Ringnut auf:. Somit wird jede Seite des zur Stirnfläche gewandten Schaufelfußes durch einen Anstemmvorgang verformt und die beidseitig Laufschaufel gegen axiales Verschieben in beide Richtungen gesichert .So that the rotor blade is secured against axial displacement in both directions, each end face has one Slice an annular groove on :. Thus, each side of the blade root facing the end face is deformed by a caulking process and the rotor blade is secured on both sides against axial displacement in both directions.
Die auf die Strömungsmaschine gerichtete Aufgabe wird gelöst, indem diese mit einem Rotor nach einem der Ansprüche 1 bis 7 ausstattet. Dabei gelten die für den Rotor aufgeführten Vorteile sinngemäß auch für- die Strömungsmaschine, insbesondere, wenn diese ein Verdichter ist.The object directed to the turbomachine is achieved by equipping it with a rotor according to one of claims 1 to 7. The advantages listed for the rotor also apply analogously to the turbomachine, in particular if it is a compressor.
Die Erfindung wird anhand einer Zeichnung erläutert . Es zeigt :The invention is explained with reference to a drawing. It shows :
Figur 1 eine erfindungsgemäße Verdichterscheibe in einer perspektivischen Ansicht,FIG. 1 shows a compressor disk according to the invention in a perspective view,
Figur 2 einen Schnitt durch eine Verdichterscheibe gemäß Figur 1,FIG. 2 shows a section through a compressor disk according to FIG. 1,
Figur 3 einen Schnitt durch eine Verdichterscheibe gemäß Figur 1 mit einem plastisch verformten Schaufelfuß einer Laufschaufel,FIG. 3 shows a section through a compressor disk according to FIG. 1 with a plastically deformed blade root of a moving blade,
Figur 4 eine Ausschnittsweise Seitenansicht der Verdichterscheibe gemäß Figur 3 ,FIG. 4 shows a partial side view of the compressor disk according to FIG. 3,
Figur 5, 6 Detail durch den Schnitt einer Verdichterscheibe mit einer Ringnut,5, 6 detail through the section of a compressor disc with an annular groove,
Figur 7 eine perspektivisch dargestellte Verdichterscheibe mit Haltenuten nach dem Stand der Technik undFigure 7 is a perspective view of the compressor disc with holding grooves according to the prior art and
Figur 8 einen Schnitt durch die Verdichterscheibe gemäß Figur 7. Gasturbinen und deren Arbeitsweisen sind allgemein bekannt. Die Gasturbine weist im Wesentlichen entlang eines Rotors einen Verdichter, eine Brennkammer und eine Turbineneinheit auf. Die vom Verdichter angesaugte und verdichtete Luft wird mit einem Brennstoff gemischt und in der Brennkammer zu einem Heißgas verbrannt, welches sich anschließend in der Turbineneinheit am Rotor der Gasturbine arbeitsleistend entspannt. Der Rotor der Gasturbine treibt dabei den Verdichter und eine Arbeitsmaschine, beispielsweise einen Generator an.8 shows a section through the compressor disc according to FIG. 7. Gas turbines and their working methods are generally known. The gas turbine essentially has a compressor, a combustion chamber and a turbine unit along a rotor. The air drawn in and compressed by the compressor is mixed with a fuel and burned in the combustion chamber to form a hot gas, which then relaxes in the turbine unit on the rotor of the gas turbine in a work-performing manner. The rotor of the gas turbine drives the compressor and a working machine, for example a generator.
Im Verdichter bilden jeweils zwei Schaufelkränze eine Verdichterstufe, wobei in Strömungsrichtung gesehen jeweils ein am Rotor befestigter -otierbarer Kranz aus Laufschaufein einem feststehenden Kranz von Leitschaufeln folgt. Gleich- falls bilden jeweils zwei Schaufelkränze eine Turbinenstufe, wobei in Strömungsrichtung gesehen jeweils ein feststehender Leitschaufelkranz ein am Rotor befestigter rotierbarer Kranz aus Laufschaufein folgt . Der Rotor der Gasturbine weist für jeden Laufschaufelkranz eine Scheibe oder einen Wellenbund auf, an der die Laufschaufeln des jeweiligen Kranzes befestigt sind.In the compressor, two blade rings each form a compressor stage, wherein, viewed in the direction of flow, an adjustable ring attached to the rotor from rotor blades follows a fixed ring of guide vanes. Likewise, in each case two blade rings form a turbine stage, a fixed guide blade ring, viewed in the direction of flow, followed by a rotatable ring attached to the rotor from rotor blades. The rotor of the gas turbine has a disk or a shaft collar for each rotor blade ring, to which the rotor blades of the respective ring are fastened.
Figur 1 zeigt ein Segment einer solchen Scheibe als Verdichterscheibe 19 gemäß der Erfindung. Die Verdichterscheibe formt einen Wellenbund. 22, der an seinem Außenumfang 23 sich quer erstreckende Haltenuten 21 zur Aufnahme von Laufschaufeln 16 aufweist. Im Bereich des Nutgrundes 27 der Haltenut 21 ist eine koaxial zum Drehpunkt des Rotors angeordnete und sich in Axialrichtung A erstreckende Ringnut 31 vorgesehen. Die Ringnut 31 ist während der Herstellung der Verdichterscheibe 19 beim Drehen der Stirnseite 25 und somit innerhalb des bisherigen Arbeitsschritts herstellbar. Die Ringnut 31 schneidet jede Haltem-it 21 im Bereich des Nutgrunds 27. Somit steht ein Aufnahmebereich 34 zur Verfügung, in den Material des Schaufelfußes 33 z.B. durch Anstemmen plastisch verdrängbar ist. Figur 2 zeigt einen Ausschnitt durch den Querschnitt einer Verdichterscheibe 19 gemäß Figur 1. Der durch die Verdichterscheibe 19 gebildete Wellenbund 22 weist an jeder Stirnseite 25 die im Querschnitt U-förmige Ringnut 31 auf. Mit einer Tiefe T erstreckt sich jede Ringnut 31 in Axialrichtung, so dass die axiale Länge des Nutgrunds 27 der Haltenut 21 gegenüber einer Scheibendicke D (siehe Figur 1) verkürzt ist.Figure 1 shows a segment of such a disc as a compressor disc 19 according to the invention. The compressor disc forms a shaft collar. 22, which has on its outer periphery 23 transversely extending retaining grooves 21 for receiving blades 16. In the area of the groove base 27 of the holding groove 21, an annular groove 31 is provided which is arranged coaxially to the fulcrum of the rotor and extends in the axial direction A. The annular groove 31 can be produced during the manufacture of the compressor disc 19 when the end face 25 is rotated and thus within the previous work step. The annular groove 31 intersects each holder 21 in the region of the groove base 27. A receiving region 34 is thus available, into which the material of the blade root 33 can be plastically displaced, for example by prying. FIG. 2 shows a section through the cross section of a compressor disk 19 according to FIG. 1. The shaft collar 22 formed by the compressor disk 19 has the annular groove 31 which is U-shaped in cross section on each end face 25. Each annular groove 31 extends with a depth T in the axial direction, so that the axial length of the groove base 27 of the holding groove 21 is shortened compared to a disk thickness D (see FIG. 1).
Die Ringnut 31 weist im Querschnitt als Seitenwand jeweils eine Flanke 37 auf, die über eine Rundung 41, welche alsThe annular groove 31 has a flank 37 in cross section as a side wall, which has a rounding 41, which as
Radius, Ellipse, konkave Form oder vergleichbarem ausgebildet sein kann, in den Ringnutgrund 39 übergeht.Radius, ellipse, concave shape or the like can be formed, into the annular groove base 39.
Die Ringnut 31 ist a.n beiden Stirnseiten 25 der Verdichter- scheibe 19 vorgesehen, so dass jede Laufschaufei 16 durch zwei Anstemmvorgänge axial gesichert werden kann.The annular groove 31 is provided on both end faces 25 of the compressor disc 19, so that each rotor blade 16 can be axially secured by two prying processes.
Figur 3 zeigt den Schnitt durch eine Verdichterscheibe 19 mit einer Laufschaufei 16, deren Schaufelfuß 33 bereits plastisch deformiert ist. Das Material des Schaufelfußes 33 ragt alsFIG. 3 shows the section through a compressor disk 19 with a rotor blade 16, the blade root 33 of which is already plastically deformed. The material of the blade root 33 protrudes as
Vorsprung 35 radial nach innen in die Ringnut 31 hinein. Der Ringnutgrund 39 dient als Widerlager für den Vorsprung 35, der so die LaufSchaufel 16 gegen axiales Verschieben sichert.Projection 35 radially inward into the annular groove 31. The annular groove base 39 serves as an abutment for the projection 35, which thus secures the moving blade 16 against axial displacement.
In Figur 4 ist ein Ausschnitt aus der Seitenansicht der Verdichterscheibe 19 gemäß Figur 3 gezeigt. Der Laufschaufelfuß 33 der Laufschaufel 16 ist durch den Anstemmvorgang deformiert. Eine Anstemmung 36 ist dabei im unteren Bereich des Schaufelfußes 33 angeordnet und überdeckt ca. ein Drittel der Breite des Schaufelffußes 33.FIG. 4 shows a detail from the side view of the compressor disk 19 according to FIG. 3. The blade root 33 of the blade 16 is deformed by the caulking process. A caulking 36 is arranged in the lower region of the blade root 33 and covers approximately a third of the width of the blade root 33.
Fig. 5 und 6 zeigen den Schnitt durch die Verdichterscheibe 19 mit der koaxialen Ringnut 31 im Detail.5 and 6 show the section through the compressor disk 19 with the coaxial annular groove 31 in detail.
An der Krümmung der Ringnut 31 im Bereich des Übergangs vonAt the curvature of the annular groove 31 in the area of the transition from
Ringnut 31 zum Nutgrund 27 liegt eine Tangente an, welche mit dem Nutgrund 27 der Haltenut 21 einen Tangentenwinkel α ein- schließt. Dieser liegt in einer gedachten Ebene, die von der Drehachse des Rotors und von der radialen Richtung des Rotors aufgespannt wird, welche durch eine Haltenut 21 verläuft. Je nach Abstand des Nutgrunds 27 zur Drehachse des Rotors weist der Tangentenwinkiel α eine Größe von 50° bis 90° auf.An annular groove 31 to the groove base 27 is tangent, which forms a tangent angle α with the groove base 27 of the holding groove 21. closes. This lies in an imaginary plane that is spanned by the axis of rotation of the rotor and by the radial direction of the rotor, which runs through a holding groove 21. Depending on the distance of the groove base 27 to the axis of rotation of the rotor, the tangent angle α has a size of 50 ° to 90 °.
Schneidet der Ringnutgrund 39 den Nutgrund 27 der Haltenut 21, so liegt ein Tangentenwinkel α von 90° vor. Ist jedoch die Ringnut 21 radial weiter außen angeordnet, so dass die radial innere Rundung 41 den Nutgrund 27 der Haltenut 21 schneidet, so verkleinert sich der Tangentenwinkel α entsprechend der gewählten Rundung 41.If the ring groove base 39 intersects the groove base 27 of the holding groove 21, there is a tangent angle α of 90 °. However, if the annular groove 21 is arranged radially further outward so that the radially inner curve 41 intersects the groove base 27 of the holding groove 21, the tangent angle α decreases in accordance with the selected curve 41.
Je größer der Tangentenwinkel α ist, umso besser kann der Vorsprung 35 die Laufschaufel 16 gegen axiales Verschieben sichern, da dieser sich am Ringnutgrund 39 abstützt.The larger the tangent angle α, the better the projection 35 can secure the moving blade 16 against axial displacement, since this is supported on the annular groove base 39.
Verglichen mit dem Stand der Technik nach Figur 7, bei dem ein durch die Fase 30 gebildeter Tangentenwinkel von 45° vorliegt, kann mit der erfindungsgemäßen Ausgestaltung eine wirksamere Axialsicherung der Laufschaufei 16 erzielt werden. Compared to the prior art according to FIG. 7, in which there is a tangent angle of 45 ° formed by the chamfer 30, a more effective axial securing of the rotor blade 16 can be achieved with the configuration according to the invention.

Claims

Patentansprüche claims
1. Rotor für eine Strömungsmaschine, insbesondere Rotor für einen Verdichter einer Gasturbine, auf dem zumindest ein Wellenbund (22) mit einem Außenumfang (23) und mit zwei sich radial erstreckenden Stirnflächen (25) angeordnet ist, mit einer Vielzahl von im Außenumfang (23) vorgesehenen, sich quer zur Umfangsrichtung erstreckenden Haltenuten (21) für Laufschaufeln (16) , in denen jeweils eine Lauf- schaufel (16) mit einem zur Haltenut (21) korrespondierend geformten Schaufelfuß (33) angeordnet ist, die jeweils durch eine stirnseitige Verformung in Axialrichtung gesichext sind, dadurch gekennzeichnet, dass zumindest in einer Stirnfläche (25) des Wellenbunds (22) eine sich in Axialrichtung erstreckende zur Drehachse des Rotors koaxiale Ringnut (31) vorgesehen ist, die den Nutgrund (27) jeder Haltenut (21) schneidet und als Verformung Material des Schaufelfußes (33) der Lauf- schaufel (16) in die Ringnut (31) plastisch verdrängt ist .1. Rotor for a turbomachine, in particular rotor for a compressor of a gas turbine, on which at least one shaft collar (22) with an outer circumference (23) and with two radially extending end faces (25) is arranged, with a plurality of in the outer circumference (23 ) provided, which extend transversely to the circumferential direction, for rotor blades (16), in each of which a rotor blade (16) with a blade root (33) corresponding to the retaining groove (21) is arranged, each of which is deformed by an end face are sextext in the axial direction, characterized in that at least in one end face (25) of the shaft collar (22) is provided an axial groove (31) which extends in the axial direction and coaxial to the axis of rotation of the rotor and which intersects the groove base (27) of each holding groove (21) and the material of the blade root (33) of the rotor blade (16) is plastically displaced into the annular groove (31) as the deformation.
2. Rotor nach Anspruch 1 , dadurch gekennzeichnet, dass die Ringnut (31) einen Ringnutgrund (39) und zwei Flanken (37) aufweist, wobei jede Flanke (37) der Ringnut (31) über eine Rundung (41) in den Ringnutgrund (39) übergeht .2. Rotor according to claim 1, characterized in that the annular groove (31) has an annular groove base (39) and two flanks (37), each flank (37) of the annular groove (31) via a rounding (41) in the annular groove base ( 39) passes over.
Rotor nach Anspruch 1 oder 2 , dadurch gekennzeichnet, dass der Wellenbund (22) durch eine Scheibe, insbesondere mittels einer Verdichterscheibe (19) gebildet ist. Rotor according to claim 1 or 2, characterized in that the shaft collar (22) is formed by a disk, in particular by means of a compressor disk (19).
4. Rotor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass jede Haltenut (21) im Querschnitt Schwalbenschwanz- förmig ist.4. Rotor according to one of claims 1 to 3, characterized in that each holding groove (21) is dovetail-shaped in cross section.
5. Rotor nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass jede Haltenut (21) im Querschnitt tannenbaumformig ist.5. Rotor according to one of claims 1 to 4, characterized in that each retaining groove (21) is shaped like a fir tree in cross section.
6. Rotor nach einem der Ansprüche 3 bis 5, dadurch gekennzeichnet, dass jede Stirnfläche (25) einer Scheibe eine Ringnut (31) aufweist.6. Rotor according to one of claims 3 to 5, characterized in that each end face (25) of a disc has an annular groove (31).
7. Strömungsmaschine mit einem Rotor nach einem der Ansprüche 1 bis 6.7. turbomachine with a rotor according to one of claims 1 to 6.
8. Strömungsmaschine nach Anspruch 7, dadurch gekennzeichnet, dass die Strömungsmaschine als Verdichter, insbesondere als der einer Gasturbine ausgebildet ist. 8. Turbomachine according to claim 7, characterized in that the turbomachine is designed as a compressor, in particular as that of a gas turbine.
EP05716050A 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine Not-in-force EP1733124B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05716050A EP1733124B1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04008485A EP1584791A1 (en) 2004-04-07 2004-04-07 Turbo-machine and rotor therefor
EP05716050A EP1733124B1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine
PCT/EP2005/002710 WO2005100751A1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine

Publications (2)

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EP1733124A1 true EP1733124A1 (en) 2006-12-20
EP1733124B1 EP1733124B1 (en) 2011-05-04

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EP04008485A Withdrawn EP1584791A1 (en) 2004-04-07 2004-04-07 Turbo-machine and rotor therefor
EP05716050A Not-in-force EP1733124B1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine

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EP (2) EP1584791A1 (en)
CN (1) CN100404795C (en)
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WO (1) WO2005100751A1 (en)

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DE102010053141B4 (en) * 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbine aggregate with possible over-rotation of the foot of a blade to the installation of a last blade
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US8764402B2 (en) 2011-06-09 2014-07-01 General Electric Company Turbomachine blade locking system
US11098729B2 (en) * 2016-08-04 2021-08-24 General Electric Company Gas turbine wheel assembly, method of modifying a compressor wheel, and method of mounting a blade to a gas turbine wheel
US20180112544A1 (en) * 2016-10-26 2018-04-26 Siemens Aktiengesellschaft Turbine rotor blade, turbine rotor arrangement and method for manufacturing a turbine rotor blade
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EP1584791A1 (en) 2005-10-12
DE502005011334D1 (en) 2011-06-16
EP1733124B1 (en) 2011-05-04
WO2005100751A1 (en) 2005-10-27
CN100404795C (en) 2008-07-23
US7628589B2 (en) 2009-12-08
CN1950590A (en) 2007-04-18
US20080267781A1 (en) 2008-10-30

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