EP1733124B1 - 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 Download PDF

Info

Publication number
EP1733124B1
EP1733124B1 EP05716050A EP05716050A EP1733124B1 EP 1733124 B1 EP1733124 B1 EP 1733124B1 EP 05716050 A EP05716050 A EP 05716050A EP 05716050 A EP05716050 A EP 05716050A EP 1733124 B1 EP1733124 B1 EP 1733124B1
Authority
EP
European Patent Office
Prior art keywords
rotor
annular groove
blade
compressor
retaining
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.)
Not-in-force
Application number
EP05716050A
Other languages
German (de)
French (fr)
Other versions
EP1733124A1 (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
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 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

Links

Images

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.
  • the shows CH 489 698 A a device for securing individually in axial grooves positively held blades of turbines.
  • a hammer-shaped groove with undercuts is arranged such that the undercut cuts from below the groove bottom of the holding grooves of the blades.
  • a securing element can be inserted after assembly of the blades in the hammer-shaped groove, which engages in a recess formed in the blade root corresponding recess.
  • FIG. 7 shows a section of a compressor disk 19 according to the prior art.
  • retaining grooves 21 are provided in the outer periphery 23 of the compressor disk 19.
  • recesses 29 are arranged on the two end faces 25 of the compressor disk 23, which each pass into the groove bottom 27 of the radially outer holding 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 formed as a chamfer 30 at an angle of 45 °.
  • the solution of the problem provides that at least in an end face of the shaft collar an axially extending to the axis of rotation of the rotor coaxial annular groove is provided which intersects the groove bottom of each holding and plastic deformation is displaced as deformation material of the blade root of the blade into the annular groove.
  • the invention is based on the recognition that a receiving region, which lies below the groove bottom of the retaining groove in the coaxial annular groove and serves to receive the material of the blade root, has a shape which is more favorable for the projection formed by the chamfering.
  • the plastically deformed material of the blade root after a chamfer is then better at the annular groove, so that a lossy axial play of the blade is avoided. Additional fastening components omitted.
  • each bevel was made in a separate milling operation.
  • the annular groove can be made during the turning process, with which the contour of the front side is made.
  • the receiving area is created in the material of the blade root is displaceable. This reduces the manufacturing cost and the manufacturing time of the rotor.
  • the annular groove has an annular groove bottom and two flanks, in which each flank the annular groove passes over a curve in the Ringnutground.
  • the groove bottom of the retaining groove and formed by the inner surface of the annular groove cutting edge include this a tangent angle, which lies in a plane which is spanned by the radius of the rotor and the axis of rotation of the rotor.
  • the groove bottom of the retaining groove can cut the radially inner curve of the annular groove. Due to the rounding, the tangent angle may be on the order of between 50 ° and 90 °, so that the shape of the receiving region is geometrically very close to the shape of the projection.
  • a projection can be formed which has an angle of 50 ° to 90 ° to the groove bottom of the retaining groove. The most effective portion of the projection is that which is formed at an angle of 90 ° to the groove bottom of the retaining groove.
  • the shaft collar is formed by a disk, in particular by a compressor disk.
  • the annular groove can be produced when turning the compressor disk, so that the individual milling of each chamfer is eliminated.
  • the blade is arranged with its retaining foot for complementarily formed blade root in the respective retaining groove, wherein material of the blade root projects into the annular groove.
  • material of the blade root projects into the annular groove.
  • each face has a Disc an annular groove.
  • each side of the end face facing blade root is deformed by a Anstemmvorgang and secured the two-sided blade against axial displacement in both directions.
  • the task directed to the turbomachine is achieved by providing it with a rotor according to one of claims 1 to 7.
  • the advantages listed for the rotor apply mutatis mutandis to the turbomachine, especially if this is a compressor.
  • the gas turbine has a compressor, a combustion chamber and a turbine unit substantially along a rotor.
  • the sucked and compressed by the compressor air is mixed with a fuel and burned in the combustion chamber to a hot gas, which then relaxes work in the turbine unit on the rotor of the gas turbine.
  • the rotor of the gas turbine thereby drives the compressor and a working machine, for example a generator.
  • two blade rings each form a compressor stage, wherein, viewed in the flow direction, in each case a rotatable ring of rotor blades fastened to the rotor follows a stationary ring of stator blades.
  • two blade rings form a turbine stage, wherein in the flow direction, in each case a stationary vane ring follows a rotatable ring of rotor blades fastened to the rotor.
  • the rotor of the gas turbine has for each blade ring on a disc or a shaft collar on which the blades of the respective ring are attached.
  • FIG. 1 shows a segment of such a disk as the compressor disk 19 according to the invention.
  • the compressor disk forms a shaft collar 22 which has on its outer circumference 23 transversely extending retaining grooves 21 for receiving rotor blades 16.
  • a coaxial with the pivot point of the rotor and arranged in the axial direction A extending annular groove 31 is provided.
  • the annular groove 31 can be produced during the production of the compressor disk 19 during rotation of the front side 25 and thus within the previous working step.
  • the annular groove 31 intersects each retaining groove 21 in the region of the groove bottom 27.
  • a receiving region 34 is available into which the material of the blade root 33 can be plastically displaced, for example by chucking.
  • 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, on each end face 25, the annular groove 31 which is U-shaped in cross-section. With a depth T, each annular groove 31 extends in the axial direction, so that the axial length of the groove bottom 27 of the retaining groove 21 with respect to a disk thickness D (see FIG. 1 ) is shortened.
  • the annular groove 31 has in cross section as a side wall in each case a flank 37 which merges into the annular groove bottom 39 via a rounding 41, which may be designed as a radius, ellipse, concave shape or the like.
  • the annular groove 31 is provided on both end faces 25 of the compressor disk 19, so that each blade 16 can be axially secured by two Anstemmvortician.
  • FIG. 3 shows the section through a compressor disk 19 with a blade 16, the blade root 33 is already plastically deformed.
  • the material of the blade root 33 projects as a projection 35 radially inwardly into the annular groove 31.
  • the annular groove bottom 39 serves as an abutment for the projection 35, which thus secures the blade 16 against axial displacement.
  • FIG. 4 is a section of the side view of the compressor disk 19 according to FIG. 3 shown.
  • the blade root 33 of the blade 16 is deformed by the Anstemmvorgang.
  • An Anstemmung 36 is arranged in the lower region of the blade root 33 and covers about one third of the width of the blade root 33rd
  • FIGS. 5 and 6 show the section through the compressor disk 19 with the coaxial annular groove 31 in detail.
  • a tangent which ⁇ with the groove bottom 27 of the retaining groove 21 includes a tangent. This lies in an imaginary plane, which is spanned by the axis of rotation of the rotor and by the radial direction of the rotor, which extends through a retaining groove 21.
  • the tangent angle ⁇ has a size of 50 ° to 90 °. If the annular groove bottom 39 intersects the groove base 27 of the retaining groove 21, a tangent angle ⁇ of 90 ° is present. 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 retaining groove 21, then the tangent angle ⁇ decreases corresponding to the selected rounding 41.

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

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.From the US 5,211,407 an attachment of blades of a compressor to the disc of the compressor rotor is known in which the securing of the blades takes place against axial displacement by an annular retaining segment. The disc has on the front side between two blade retaining grooves radially inwardly extending hooks, in which a retaining segment is hooked. The retaining segment forms a stop for the blade held in the retaining 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 Reibungsdämpfung zu erzielen.To that is in the DE 26 06 565 a method for assembling blades in a disc described. In this case, the frontal areas of a platform of a blade are deformed such that after a Anstemmvorgang the material areas of the platform, which face the outer periphery of the disc, rest firmly against the disc to achieve a 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 Wellenbundes 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 einschiebbar, welches in eine im Schaufelfuß korrespondierend geformte Ausnehmung eingreift.In addition, the shows CH 489 698 A a device for securing individually in axial grooves positively held blades of turbines. On the front side of a shaft collar a hammer-shaped groove with undercuts is arranged such that the undercut cuts from below the groove bottom of the holding grooves of the blades. For axial securing of the blades, a securing element can be inserted after assembly of the blades in the hammer-shaped groove, which engages in a recess formed in the blade root corresponding recess.

Ferner ist bekannt, dass Laufschaufelfüße von Laufschaufeln eines Verdichters durch plastisches Verformen gegen axiale Verschiebung gesichert werden.It is also known that blade feet of blades of a compressor are secured against axial displacement by plastic deformation.

Figur 7 zeigt dazu einen Ausschnitt einer Verdichterscheibe 19 nach dem Stand der Technik. Zur Aufnahme von Laufschaufeln 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 Nutgrund 27 der radial außen liegenden Haltenut 21 übergehen. FIG. 7 shows a section of a compressor disk 19 according to the prior art. For receiving blades, retaining grooves 21 are provided in the outer periphery 23 of the compressor disk 19. Further, recesses 29 are arranged on the two end faces 25 of the compressor disk 23, which each pass into the groove bottom 27 of the radially outer holding 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 formed as a chamfer 30 at 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 blade 16, material of the blade root 33 is plastically deformed on both sides in the area of the chamfer 30 by a caulking process. The projection thus formed on the blade root 33 then secures the blade 16 against axial displacement by abutting the projection on the chamfer 30 inclined to the direction of displacement.

Da jedoch beim Anstentemmvorgang 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 on its side facing the chamfer takes on a rounded shape during Anstentemmvorgang, this is only partially on the chamfer, which can lead to a lower holding force.

Beim Anfahren des kalten Verdichters und nach dem Abschalten des warmen Verdichters können durch unterschiedliche Wärmedehnungen von Laufschaufel 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 Verdichterlaufschaufeln und dieses zu Strömungsverlusten im Verdichter führen.When starting the cold compressor and after switching off the hot compressor axial directional stresses in the blade attachment may arise due to different thermal expansion of the blade and disc, which can deform the projection at repeated occurrence. This effect, also known as "blade walk", can lead to the axial play of the compressor blades and this to flow losses in the compressor.

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.It is therefore an object of the invention to provide a rotor for a turbomachine, which enables a safer attachment of blades with a simple geometric design on 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 solved by the features of claim 1. Advantageous embodiments are specified in the subclaims.

Die Lösung der Aufgabe sieht vor, dass zumindest in einer Stirnfläche des Wellenbunds 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 Laufschaufel in die Ringnut plastisch verdrängt ist.The solution of the problem provides that at least in an end face of the shaft collar an axially extending to the axis of rotation of the rotor coaxial annular groove is provided which intersects the groove bottom of each holding and plastic deformation is displaced as deformation material of the blade root of the 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 der Laufschaufel vermieden wird. Zusätzliche Befestigungsbauteile entfallen.The invention is based on the recognition that a receiving region, which lies below the groove bottom of the retaining groove in the coaxial annular groove and serves to receive the material of the blade root, has a shape which is more favorable for the projection formed by the chamfering. The plastically deformed material of the blade root after a chamfer is then better at the annular groove, so that a lossy axial play of the blade is avoided. Additional fastening components omitted.

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.Previously, in the prior art, each bevel was made in a separate milling operation. The annular groove, however, can be made during the turning process, with which the contour of the front side is made. Thus, in only one manufacturing process below each retaining groove, the receiving area is created in the material of the blade root is displaceable. 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 Kerbspannungen 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 bottom and two flanks, in which each flank the annular groove passes over a curve in the Ringnutgrund. As a result, notch stresses are avoided in the shaft collar, which would be generated at an acute transition from flank to Ringnutgrund.

An der vom Nutgrund der Haltenut und der von der Innenfläche der Ringnut gebildeten Schnittkante schließen diese einen Tangentenwinkel ein, der in einer Ebene liegt, die vom Radius des Rotors und der Drehachse des Rotors aufgespannt wird. Dabei 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 Aufnahmebereichs der Form des Vorsprungs geometrisch sehr nahe kommt. Somit kann durch den Anstemmvorgang 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 groove bottom of the retaining groove and formed by the inner surface of the annular groove cutting edge include this a tangent angle, which lies in a plane which is spanned by the radius of the rotor and the axis of rotation of the rotor. In this case, the groove bottom of the retaining groove can cut the radially inner curve of the annular groove. Due to the rounding, the tangent angle may be on the order of between 50 ° and 90 °, so that the shape of the receiving region is geometrically very close to the shape of the projection. Thus, by the Anstemmvorgang a projection can be formed which has an angle of 50 ° to 90 ° to the groove bottom of the retaining groove. The most effective portion of the projection is that which is formed at an angle of 90 ° to the groove bottom of the retaining groove.

Zweckmäßigerweise ist der Wellenbund durch eine Scheibe, insbesondere durch eine Verdichterscheibe gebildet. Die Ringnut kann beim Drehen der Verdichterscheibe hergestellt werden, so dass das einzelne Fräsen jeder Fase entfällt.Conveniently, the shaft collar is formed by a disk, in particular by a compressor disk. The annular groove can be produced when turning the compressor disk, so that the individual milling of each chamfer is eliminated.

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 Laufschaufel 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 retaining foot for complementarily formed blade root in the respective retaining groove, wherein material of the blade root projects into the annular groove. After the introduction of the blade in the retaining material of the blade root is deformed by prying into the annular groove and thus produces a mechanical protection against axial displacement. The retaining groove may be dovetail-shaped 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.Thus, the blade is secured against axial displacement in both directions, each face has a Disc an annular groove. Thus, each side of the end face facing blade root is deformed by a Anstemmvorgang and secured the two-sided blade 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 task directed to the turbomachine is achieved by providing it with a rotor according to one of claims 1 to 7. The advantages listed for the rotor apply mutatis mutandis to the turbomachine, especially if this is a compressor.

Die Erfindung wird anhand einer Zeichnung erläutert. Es zeigt:

Figur 1
eine erfindungsgemäße Verdichterscheibe in einer perspektivischen Ansicht,
Figur 2
einen Schnitt durch eine Verdichterscheibe gemäß Figur 1,
Figur 3
einen Schnitt durch eine Verdichterscheibe gemäß Figur 1 mit einem plastisch verformten Schaufelfuß einer Laufschaufel,
Figur 4
eine Ausschnittsweise Seitenansicht der Verdich- terscheibe gemäß Figur 3,
Figur 5, 6
Detail durch den Schnitt einer Verdichterscheibe mit einer Ringnut,
Figur 7
eine perspektivisch dargestellte Verdichterscheibe mit Haltenuten nach dem Stand der Technik und
Figur 8
einen Schnitt durch die Verdichterscheibe gemäß Figur 7.
The invention will be explained with reference to a drawing. It shows:
FIG. 1
a compressor disk according to the invention in a perspective view,
FIG. 2
a section through a compressor disk according to FIG. 1 .
FIG. 3
a section through a compressor disk according to FIG. 1 with a plastically deformed blade root of a blade,
FIG. 4
a partial side view of the compressor disk according to FIG. 3 .
FIG. 5, 6
Detail by cutting a compressor disk with an annular groove,
FIG. 7
a perspective view of the compressor disk with retaining grooves according to the prior art and
FIG. 8
a section through the compressor disk according to FIG. 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.Gas turbines and their ways of working are well known. The gas turbine has a compressor, a combustion chamber and a turbine unit substantially along a rotor. The sucked and compressed by the compressor air is mixed with a fuel and burned in the combustion chamber to a hot gas, which then relaxes work in the turbine unit on the rotor of the gas turbine. The rotor of the gas turbine thereby 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 rotierbarer Kranz aus Laufschaufeln einem feststehenden Kranz von Leitschaufeln folgt. Gleichfalls bilden jeweils zwei Schaufelkränze eine Turbinenstufe, wobei in Strömungsrichtung gesehen jeweils ein feststehender Leitschaufelkranz ein am Rotor befestigter rotierbarer Kranz aus Laufschaufeln 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 flow direction, in each case a rotatable ring of rotor blades fastened to the rotor follows a stationary ring of stator blades. Likewise, in each case two blade rings form a turbine stage, wherein in the flow direction, in each case a stationary vane ring follows a rotatable ring of rotor blades fastened to the rotor.
The rotor of the gas turbine has for each blade ring on a disc or a shaft collar on which the blades of the respective ring are attached.

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 Haltenut 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. FIG. 1 shows a segment of such a disk as the compressor disk 19 according to the invention. The compressor disk forms a shaft collar 22 which has on its outer circumference 23 transversely extending retaining grooves 21 for receiving rotor blades 16. In the region of the groove bottom 27 of the retaining groove 21, a coaxial with the pivot point of the rotor and arranged in the axial direction A extending annular groove 31 is provided. The annular groove 31 can be produced during the production of the compressor disk 19 during rotation of the front side 25 and thus within the previous working step. The annular groove 31 intersects each retaining groove 21 in the region of the groove bottom 27. Thus, a receiving region 34 is available into which the material of the blade root 33 can be plastically displaced, for example by chucking.

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. 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, on each end face 25, the annular groove 31 which is U-shaped in cross-section. With a depth T, each annular groove 31 extends in the axial direction, so that the axial length of the groove bottom 27 of the retaining groove 21 with respect to a disk thickness D (see FIG. 1 ) is shortened.

Die Ringnut 31 weist im Querschnitt als Seitenwand jeweils eine Flanke 37 auf, die über eine Rundung 41, welche als Radius, Ellipse, konkave Form oder vergleichbarem ausgebildet sein kann, in den Ringnutgrund 39 übergeht.The annular groove 31 has in cross section as a side wall in each case a flank 37 which merges into the annular groove bottom 39 via a rounding 41, which may be designed as a radius, ellipse, concave shape or the like.

Die Ringnut 31 ist an beiden Stirnseiten 25 der Verdichterscheibe 19 vorgesehen, so dass jede Laufschaufel 16 durch zwei Anstemmvorgänge axial gesichert werden kann.The annular groove 31 is provided on both end faces 25 of the compressor disk 19, so that each blade 16 can be axially secured by two Anstemmvorgänge.

Figur 3 zeigt den Schnitt durch eine Verdichterscheibe 19 mit einer Laufschaufel 16, deren Schaufelfuß 33 bereits plastisch deformiert ist. Das Material des Schaufelfußes 33 ragt als 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. FIG. 3 shows the section through a compressor disk 19 with a blade 16, the blade root 33 is already plastically deformed. The material of the blade root 33 projects as a projection 35 radially inwardly into the annular groove 31. The annular groove bottom 39 serves as an abutment for the projection 35, which thus secures the 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 Schaufelfußes 33.In FIG. 4 is a section of the side view of the compressor disk 19 according to FIG. 3 shown. The blade root 33 of the blade 16 is deformed by the Anstemmvorgang. An Anstemmung 36 is arranged in the lower region of the blade root 33 and covers about one third of the width of the blade root 33rd

Fig. 5 und 6 zeigen den Schnitt durch die Verdichterscheibe 19 mit der koaxialen Ringnut 31 im Detail. FIGS. 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 von Ringnut 31 zum Nutgrund 27 liegt eine Tangente an, welche mit dem Nutgrund 27 der Haltenut 21 einen Tangentenwinkel α einschließt. 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 Tangentenwinkel α eine Größe von 50° bis 90° auf. 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.At the curvature of the annular groove 31 in the region of the transition from the annular groove 31 to the groove bottom 27 is located at a tangent, which α with the groove bottom 27 of the retaining groove 21 includes a tangent. This lies in an imaginary plane, which is spanned by the axis of rotation of the rotor and by the radial direction of the rotor, which extends through a retaining 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 °. If the annular groove bottom 39 intersects the groove base 27 of the retaining groove 21, a tangent angle α of 90 ° is present. 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 retaining groove 21, then the tangent angle α decreases corresponding to the selected rounding 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 blade 16 against axial displacement, since this is supported on the annular groove bottom 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 Laufschaufel 16 erzielt werden.Compared with the prior art FIG. 7 in which a tangential angle of 45 ° formed by the chamfer 30 is present, a more effective axial securing of the rotor blade 16 can be achieved with the embodiment according to the invention.

Claims (8)

  1. Rotor for a turbo-engine, especially a rotor for a compressor of a gas turbine,
    upon which is installed at least one shaft collar (22) with an outer periphery (23) and with two radially extending end faces (25),
    with a plurality of retaining slots (21) for rotor blades (16) provided in the outer periphery (23), extending transversely to the circumferential direction, in which is installed in each case a rotor blade (16) with a blade root (33) formed corresponding to the retaining slot (21),
    characterized
    in that the rotor blades are each locked by an end face deformation in the axial direction, an annular groove (31) extending in the axial direction coaxial to the rotational axis of the rotor is provided at least in one end face (25) of the shaft collar (22), which intersects the slot base (27) of each retaining slot (21) and as deformation material of the blade root (33) of the rotor blade (16) is plastically displaced into the annular groove (31).
  2. Rotor according to Claim 1,
    characterized
    in that the annular groove (31) has an annular groove base (39) and two flanks (37), wherein each flank (37) of the annular groove (31) merges into the annular groove base (39) by a rounding (41).
  3. Rotor according to Claim 1 or 2,
    characterized
    in that the shaft collar (22) is formed by a disk, especially by means of a compressor disk (19).
  4. Rotor according to one of Claims 1 to 3,
    characterized
    in that each retaining slot (21) is dovetail-shaped in cross section.
  5. Rotor according to one of Claims 1 to 4,
    characterized
    in that each retaining slot (21) is fir-tree-shaped in cross section.
  6. Rotor according to one of Claims 3 to 5,
    characterized
    in that each end face (25) of a disk has an annular groove (31).
  7. Turbo-engine with a rotor according to one of Claims 1 to 6.
  8. Turbo-engine according to Claim 7,
    characterized
    in that the turbo-engine is constructed as a compressor, especially 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
PCT/EP2005/002710 WO2005100751A1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine
EP05716050A EP1733124B1 (en) 2004-04-07 2005-03-14 Non-positive-displacement machine and rotor for a non-positive-displacement machine

Publications (2)

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

Family

ID=34896011

Family Applications (2)

Application Number Title Priority Date Filing Date
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

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04008485A Withdrawn EP1584791A1 (en) 2004-04-07 2004-04-07 Turbo-machine and rotor therefor

Country Status (5)

Country Link
US (1) US7628589B2 (en)
EP (2) EP1584791A1 (en)
CN (1) CN100404795C (en)
DE (1) DE502005011334D1 (en)
WO (1) WO2005100751A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE112020004634T5 (en) * 2019-09-27 2022-06-15 Honda Motor Co., Ltd. metal coating process
CN114837748A (en) * 2021-02-02 2022-08-02 中国航发商用航空发动机有限责任公司 Aircraft engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3157385A (en) * 1961-10-17 1964-11-17 Ass Elect Ind Blade locking means for turbines or compressors
CH489698A (en) * 1968-09-02 1970-04-30 Bbc Brown Boveri & Cie Device for securing rotor blades of turbo machines, in particular for turbines, which are held in a form-fitting manner in axial grooves of a shaft
SE389163B (en) * 1975-03-12 1976-10-25 Stal Laval Turbin Ab AXIAL TURBINE FLOP WHEEL
US4439107A (en) * 1982-09-16 1984-03-27 United Technologies Corporation Rotor blade cooling air chamber
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
US6190131B1 (en) * 1999-08-31 2001-02-20 General Electric Co. Non-integral balanced coverplate and coverplate centering slot for a turbine
FR2824870B1 (en) * 2001-05-16 2003-08-15 Alstom Power Nv LOW PRESSURE STEAM TURBINE ROTOR DISC EQUIPPED WITH FINS EACH MOUNTED ON THE DISC WITH A NOTCHED FIXATION SAID ON THE TREE FOOT
US6533550B1 (en) * 2001-10-23 2003-03-18 Pratt & Whitney Canada Corp. Blade retention

Also Published As

Publication number Publication date
EP1584791A1 (en) 2005-10-12
EP1733124A1 (en) 2006-12-20
US7628589B2 (en) 2009-12-08
DE502005011334D1 (en) 2011-06-16
CN100404795C (en) 2008-07-23
CN1950590A (en) 2007-04-18
US20080267781A1 (en) 2008-10-30
WO2005100751A1 (en) 2005-10-27

Similar Documents

Publication Publication Date Title
EP1733124B1 (en) Non-positive-displacement machine and rotor for a non-positive-displacement machine
EP2604792B1 (en) Method for repairing a component of a gas turbine engine and associated repaired component
EP2733311B1 (en) Nozzle ring
EP1656493A1 (en) Labyrinth seal in a stationary gas turbine
EP1944472A1 (en) Axial rotor section for a rotor in a turbine, sealing element for a turbine rotor equipped with rotor blades and rotor for a turbine
EP3273001B1 (en) Methods of manufacturing a tandem guide vane segment
EP1747349B1 (en) Blade for turbomachinery comprising a shroud and a weight-optimised sealing strip
EP1694943B1 (en) Turbomachine
DE102014114555A1 (en) Locking spacer assembly
EP1215367B1 (en) Locking device for turbomachine blades
EP2818724B1 (en) Fluid flow engine and method
CH708768A2 (en) Interlocking spacer assembly for insertion into a peripheral attachment slot between platforms of adjacent blades.
EP1910647A1 (en) Securing element for fastening moving blades
EP2994615B1 (en) Rotor for a thermal turbomachine
EP3236011A1 (en) Rotor with overhang on rotor blades for a securing element
EP2762684B1 (en) Seal mount made from titanium aluminide for a flow machine
DE102008048261B4 (en) Axial turbomachinery rotor with a paddle lock and method of making the same
EP3309359A1 (en) Blade assembly for a gas turbine engine
EP1548232A1 (en) Turbomachine comprising a stator vane support and method of mounting stator vanes to the stator vane support
DE102012215413A1 (en) Assembly for axial flow turbomachine in two-phase jet engine, has guide vanes and diffuser connected with each other through connecting portions, where guide vanes are provided with radially inner stator hub and radially outer housing ring
DE10333815B4 (en) Welding process for tubular element and gear pump, which is manufactured by the welding process
EP1698759B1 (en) Rotor end piece
DE102021200787B4 (en) TURBINE WHEEL AND WIRE RETAINING PIN MOUNTING METHOD FOR TURBINE WHEEL
EP3159483A1 (en) Blade support for fixing rotor blades of a thermal fluid flow engine
EP3514333A1 (en) Rotor blade tip shroud for a turbo machine, rotor blade, method for producing a rotor blade cover strip and a rotor blade

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: 20060921

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE GB IT LI SE

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): CH DE GB IT LI SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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): CH DE GB IT LI SE

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

REF Corresponds to:

Ref document number: 502005011334

Country of ref document: DE

Date of ref document: 20110616

Kind code of ref document: P

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502005011334

Country of ref document: DE

Effective date: 20110616

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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: 20120207

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502005011334

Country of ref document: DE

Effective date: 20120207

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

Ref country code: DE

Payment date: 20150513

Year of fee payment: 11

Ref country code: CH

Payment date: 20150602

Year of fee payment: 11

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

Ref country code: GB

Payment date: 20160310

Year of fee payment: 12

Ref country code: SE

Payment date: 20160307

Year of fee payment: 12

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

Ref country code: IT

Payment date: 20160329

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502005011334

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: DE

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

Effective date: 20161001

Ref country code: CH

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

Effective date: 20160331

Ref country code: LI

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

Effective date: 20160331

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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

Effective date: 20170314

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

Ref country code: SE

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

Effective date: 20170315

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

Ref country code: IT

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

Effective date: 20170314

Ref country code: GB

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

Effective date: 20170314