EP3564489A1 - Rotor with for centrifugal forces optimized contact surfaces - Google Patents
Rotor with for centrifugal forces optimized contact surfaces Download PDFInfo
- Publication number
- EP3564489A1 EP3564489A1 EP18170613.6A EP18170613A EP3564489A1 EP 3564489 A1 EP3564489 A1 EP 3564489A1 EP 18170613 A EP18170613 A EP 18170613A EP 3564489 A1 EP3564489 A1 EP 3564489A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- holding
- radius
- shoulder
- disk
- 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.)
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Classifications
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
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- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
-
- 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
- F05D2250/27—Three-dimensional hyperboloid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/711—Shape curved convex
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
Definitions
- the invention relates to a rotor having a rotor disk and a plurality of rotor components fastened circumferentially to the rotor disk, wherein the rotor disk has a support surface facing the rotor axis and the respective rotor component has a support surface complementary to the support surface.
- the rotor disk has a circumferential projection extending axially in front of the end face, against which a fastening shoulder extending on the sealing element to the rotor disk is respectively supported.
- a supporting surface facing the rotor axis is almost compulsorily formed on the projection of the rotor disk by a rotating surface rotating about the rotor axis.
- the voltage applied to the support surface holding surface of the attachment paragraph is basically complementary to the support surface with matching radius.
- Object of the present invention is therefore to realize an attachment of rotor components to a rotor disk at large centrifugal forces occurring.
- the generic rotor is used in particular for use in a gas turbine. However, the embodiment can also be used in other types of rotors, for example in steam turbines. At least the rotor has at least one rotor disk on which a plurality of rotor components are distributed in the circumference.
- the rotor disk in a first embodiment has a circumferential, axially extending fastening shoulder.
- the rotor disk has a plurality of circumferentially distributed fastening heels, which each extend axially.
- the encircling attachment paragraph or in this case the individual distributed in the circumference arranged mounting heels on the side facing the rotor axis side forms a support surface.
- the support surface is a rotation surface revolving around the rotor axis or a portion of a corresponding rotation surface.
- the support surface in turn has a mean support radius.
- the rotor components each have a circumferentially extending and the rotor disk axially extending retaining shoulder, which is arranged on the side facing the rotor axis below the mounting paragraph of.
- the holding shoulder on a support surface complementary to the support surface.
- the holding surface is likewise a section of a rotation surface and has a middle holding radius.
- the centrifugal forces occurring in the rotor component can thus be transmitted to the fastening shoulder at least proportionally via the retaining shoulder in the bearing of the retaining surface on the support surface.
- the axial overlap between the holding surface and support surface can be used and an integral mean value of the respective radius or an average value at the geometric center in the axial direction can be determined here.
- the holding surface and the support surface are formed by a matching surface of rotation and thus match the holding radius and the support radius according to the invention now the holding radius is smaller than the support radius. It has been shown in terms of achieving maximum load capacity that a holding radius with at least 0.99 times the support radius and at the same time with a maximum of 0.999 support radius according to the invention is of particular advantage over the known embodiments of the prior art.
- the embodiment according to the invention is particularly advantageously suitable for a rotor disk on which a plurality of rotor blades distributed in the circumference can be attached.
- the rotor disk distributed in the circumference has a plurality of blade disk axially penetrating the rotor disk.
- the blade retaining grooves are hereby covered on one end side of the rotor disk by the rotor components distributed in the circumference at least in sections.
- the particular advantage of the high load capacity of the connection according to the invention between the holding shoulder and the attachment paragraph is especially useful if the rotor component has an aperture penetrating the rotor component axially, which is arranged approximately in the center of the rotor component in the circumferential direction.
- the breakthrough is located radially outside the position of the holding surface.
- the opening extends in the circumferential direction over at least 0.25 times the width of the rotor component in the circumferential direction. It is particularly advantageous if the breakthrough extends over at least 0.4 times the width. In contrast, the breakthrough should not be greater than the 0.75 times the width of the rotor component in the circumferential direction. Again, it is particularly advantageous if the opening extends over a maximum of 0.6 times the width of the rotor component.
- the rotor component may have different shapes, wherein the type of attachment to the rotor is advantageously suitable when the rotor component has a substantially flat in the circumferential direction and radially extending shape.
- the tensile stresses in this case are at least twice as large as the bending stresses.
- the rotor component can be supported on the rotor opposite to the holding shoulder with an inner edge portion facing the rotor axis.
- the rotor disk on a circumferential, axially spaced from an end face of the rotor disk or from the fastening shoulder annular projection.
- the corresponding annular projection is arranged on a second rotor disk adjacent to the rotor disk. At least the corresponding annular projection on the rotor disk or the second rotor disk forms a contact surface facing the fastening shoulder, against which the inner edge portion of the rotor components comes to rest.
- FIG. 1 is schematically sketched in a longitudinal section through the rotor axis through the rotor disk 01 and the rotor member 11 in the region of the connection between the rotor member 11 and the rotor disk 01.
- the rotor disk 01 can be seen with a blade holding groove 02 located on the radially outer circumference. This disk 02 is intended to accommodate moving blades (not shown here).
- the rotor disk 01 in this case has a fastening shoulder 04, which extends in the circumferential direction and in the axial direction and has a support surface 05 on the side facing the rotor axis.
- the support surface 05 is shown by way of example only slightly inclined and slightly convex executed sketched.
- the rotor component 11, which is fastened to the rotor disk 01, can also be seen.
- the rotor component 11 has a holding shoulder 14, which 14 likewise extends in the circumferential direction and axially.
- the holding shoulder 14 forms a holding surface 15, which 15 is arranged on the radially outwardly facing side.
- the holding surface 15 and the support surface 05 are listed complementary to each other.
- the retaining shoulder 14 is arranged near the end of the rotor component 11 facing the rotor axis, an inner edge section 17 being located at the end on the side facing the rotor axis. This 17 is in this case axially against the annular projection 07 of the rotor disk 01.
- the support surface 05 as well as the support surface 15, which, viewed in the axial direction, abut one another over a support width 10.
- the support surface 05 as a rotation surface about the rotor axis to a central support radius 06.
- the holding surface 15 of the rotor component 11 is likewise designed as a section of a rotation surface and can also be designed with a middle holding radius 16 to be discribed.
- the holding radius 16 is in this case determined at the same axial position as the support radius 06.
Abstract
Die Erfindung betrifft einen Rotor einer Gasturbine mit einer Rotorscheibe (01) und einer Mehrzahl über den Umfang der Rotorscheibe (01) verteilten Rotorbauteilen (11). Hierzu weist die Rotorscheibe (11) einen sich axial erstreckenden Befestigungsabsatz (04) mit einer Stützfläche (05) auf. Weiterhin umfasst jedes der Rotorbauteile (11) einen sich axial erstreckenden Halteabsatz (14) mit einer Haltefläche (15), sodass jeweils die Halteflächen (16) der Halteabsätze (14) zur Anlage mit der Stützfläche (05) des Befestigungsabsatzes (04) der Rotorscheibe (01) kommen. Zur Optimierung der Auflagespannungen zwischen dem Halteabsatz (15) und dem Befestigungsabsatz (05) ist vorgesehen, dass die Haltefläche (15) einen kleineren mittleren Haltradius (16) aufweist als der mittlere Stützradius (06) der Stützfläche (05). Dadurch wird die Erzielung höchster Belastungsfähigkeit der Haltverbindung ermöglicht. Dies gilt insbesondere dann, wenn das Rotorbauteil (11) einen sich über den Umfang erstreckenden Durchbruch (12) aufweist.The invention relates to a rotor of a gas turbine with a rotor disk (01) and a plurality of rotor components (11) distributed over the circumference of the rotor disk (01). For this purpose, the rotor disk (11) has an axially extending fastening shoulder (04) with a support surface (05). Furthermore, each of the rotor components (11) comprises an axially extending holding shoulder (14) with a holding surface (15), so that in each case the holding surfaces (16) of the holding heels (14) for engagement with the support surface (05) of the attachment paragraph (04) of the rotor disk (01) come. In order to optimize the contact stresses between the retaining shoulder (15) and the fastening shoulder (05), it is provided that the retaining surface (15) has a smaller central holding radius (16) than the central supporting radius (06) of the supporting surface (05). This makes it possible to achieve the highest load capacity of the holding connection. This applies in particular when the rotor component (11) has an opening (12) extending over the circumference.
Description
Die Erfindung betrifft einen Rotor mit einer Rotorscheibe und einer Mehrzahl im Umfang an der Rotorscheibe befestigten Rotorbauteilen, wobei die Rotorscheibe eine zur Rotorachse weisende Stützfläche und das jeweilige Rotorbauteil eine zur Stützfläche komplementäre Haltefläche aufweist.The invention relates to a rotor having a rotor disk and a plurality of rotor components fastened circumferentially to the rotor disk, wherein the rotor disk has a support surface facing the rotor axis and the respective rotor component has a support surface complementary to the support surface.
Aus dem Stand der Technik sind verschiedenste Möglichkeiten zur Anbringung von Rotorbauteilen an Rotorscheiben bekannt. So zeigt beispielsweise die
Weitere analoge Ausführungen sind auch aus der
Wenngleich sich die Befestigung der Dichtelemente an der Rotorscheibe über die Anlage des Befestigungsabsatz es der Dichtelemente am Haltevorsprung an den Rotorscheiben bewährt hat, so treten bei Strömungsmaschinen mit hohen Leistungen Belastungen an dem Haltevorsprung und dem Befestigungsabsatz nahe den zulässigen Materialkennwerten auf.Although the attachment of the sealing elements on the rotor disk on the attachment of the mounting paragraph it has proven the sealing elements on the retaining projection on the rotor discs, so occur in high-performance turbomachinery loads on the retaining projection and the mounting paragraph close to the permissible material properties.
Aufgabe der vorliegenden Erfindung ist es daher, eine Befestigung von Rotorbauteilen an einer Rotorscheibe bei großen auftretenden Fliehkräften zu realisieren.Object of the present invention is therefore to realize an attachment of rotor components to a rotor disk at large centrifugal forces occurring.
Die gestellte Aufgabe wird durch eine erfindungsgemäße Ausführungsform nach der Lehre des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der Unteransprüche.The stated object is achieved by an embodiment according to the invention according to the teaching of claim 1. Advantageous embodiments are the subject of the dependent claims.
Der gattungsgemäße Rotor dient insbesondere zur Verwendung bei einer Gasturbine. Die Ausführungsform kann jedoch ebenso bei anderen Arten von Rotoren, beispielsweise bei Dampfturbinen zum Einsatz kommen. Zumindest weist der Rotor zumindest eine Rotorscheibe auf, an der im Umfang verteilt eine Mehrzahl Rotorbauteile angeordnet sind.The generic rotor is used in particular for use in a gas turbine. However, the embodiment can also be used in other types of rotors, for example in steam turbines. At least the rotor has at least one rotor disk on which a plurality of rotor components are distributed in the circumference.
Hierzu weist die Rotorscheibe in einer ersten Ausführungsform einen umlaufenden sich axial erstreckenden Befestigungsabsatz auf. In einer zweiten Ausführungsform weist die Rotorscheibe eine Mehrzahl im Umfang verteilt angeordnete Befestigungsabsätze auf, welche sich jeweils axial erstrecken. Dabei bildet der umlaufende Befestigungsabsatz bzw. dabei bilden die einzelnen im Umfang verteilt angeordneten Befestigungsabsätze auf der zur Rotorachse weisenden Seite eine Stützfläche. Bei der Stützfläche handelt es sich um eine um die Rotorachse umlaufende Rotationsfläche oder um einen Abschnitt einer entsprechenden Rotationsfläche. Die Stützfläche wiederum weist hierbei einen mittleren Stützradius auf.For this purpose, the rotor disk in a first embodiment has a circumferential, axially extending fastening shoulder. In a second embodiment, the rotor disk has a plurality of circumferentially distributed fastening heels, which each extend axially. In this case, the encircling attachment paragraph or in this case the individual distributed in the circumference arranged mounting heels on the side facing the rotor axis side forms a support surface. The support surface is a rotation surface revolving around the rotor axis or a portion of a corresponding rotation surface. The support surface in turn has a mean support radius.
Demgegenüber besitzen die Rotorbauteile jeweils einen sich in Umfangsrichtung und zur Rotorscheibe axial erstreckenden Halteabsatz, welcher auf der zur Rotorachse weisenden Seite unterhalb des Befestigungsabsatz des angeordnet ist. Dabei weist der Halteabsatz eine zur Stützfläche komplementäre Haltefläche auf. Analog zur Stützfläche stellt sich ebenso die Haltefläche als Abschnitt einer Rotationsfläche dar und weist einen mittleren Halteradius auf.In contrast, the rotor components each have a circumferentially extending and the rotor disk axially extending retaining shoulder, which is arranged on the side facing the rotor axis below the mounting paragraph of. In this case, the holding shoulder on a support surface complementary to the support surface. Analogous to the support surface, the holding surface is likewise a section of a rotation surface and has a middle holding radius.
Bestimmungsgemäß können somit die im Rotorbauteil auftretenden Fliehkräfte zumindest anteilig über den Halteabsatz in der Anlage der Haltefläche an der Stützfläche auf den Befestigungsabsatz übertragen werden.As a result, the centrifugal forces occurring in the rotor component can thus be transmitted to the fastening shoulder at least proportionally via the retaining shoulder in the bearing of the retaining surface on the support surface.
Zur Bestimmung des Stützradius sowie des Halteradius kann die axiale Überdeckung zwischen Haltefläche und Stützfläche herangezogen werden und hier ein integraler Mittelwert des jeweiligen Radius oder ein Mittelwert an der in axialer Richtung geometrischen Mitte bestimmt werden.To determine the support radius and the holding radius, the axial overlap between the holding surface and support surface can be used and an integral mean value of the respective radius or an average value at the geometric center in the axial direction can be determined here.
Während hingegen im Stand der Technik grundsätzlich die Haltefläche und die Stützfläche von einer übereinstimmenden Rotationsfläche gebildet werden und insofern der Halteradius und der Stützradius übereinstimmen wird erfindungsgemäß nunmehr der Halteradius kleiner als der Stützradius ausgeführt. Dabei hat es sich hinsichtlich der Erzielung höchster Belastungsfähigkeit gezeigt, dass ein Halteradius mit mindestens dem 0,99-fachen Stützradius und zugleich mit maximal dem 0,999-fachen Stützradius erfindungsgemäß von besonderem Vorteil gegenüber den bekannten Ausführungen aus dem Stand der Technik ist.Whereas in the prior art, in principle, the holding surface and the support surface are formed by a matching surface of rotation and thus match the holding radius and the support radius according to the invention now the holding radius is smaller than the support radius. It has been shown in terms of achieving maximum load capacity that a holding radius with at least 0.99 times the support radius and at the same time with a maximum of 0.999 support radius according to the invention is of particular advantage over the known embodiments of the prior art.
Die erfindungsgemäße Ausführungsform eignet sich in besonders vorteilhafter Weise bei einer Rotorscheibe, an der eine Mehrzahl im Umfang verteilt angeordnete Laufschaufeln angebracht werden können. Hierzu weist die Rotorscheibe im Umfang verteilt eine Mehrzahl die Rotorscheibe axial durchdringende Schaufelhaltenuten auf. Die Schaufelhaltenuten werden hierbei auf einer Stirnseite der Rotorscheibe durch die im Umfang verteilt angeordneten Rotorbauteile zumindest abschnittsweise abgedeckt.The embodiment according to the invention is particularly advantageously suitable for a rotor disk on which a plurality of rotor blades distributed in the circumference can be attached. For this purpose, the rotor disk distributed in the circumference has a plurality of blade disk axially penetrating the rotor disk. The blade retaining grooves are hereby covered on one end side of the rotor disk by the rotor components distributed in the circumference at least in sections.
Der besondere Vorteil der hohen Belastungsfähigkeit der erfindungsgemäßen Verbindung zwischen dem Halteabsatz und dem Befestigungsabsatz kommt besonders zum Tragen, wenn das Rotorbauteil einen das Rotorbauteil axial durchdringenden Durchbruch aufweist, welcher hierbei ungefähr in Umfangsrichtung betrachtet in der Mitte des Rotorbauteils angeordnet ist. Dabei befindet sich der Durchbruch radial außerhalb der Lage der Haltefläche. Insbesondere bei einer derartigen Ausführungsform treten ungleichmäßige Verformungen in der Rotorscheibe und den Rotorbauteilen auf, denen durch die erfindungsgemäße Lösung entgegengewirkt wird.The particular advantage of the high load capacity of the connection according to the invention between the holding shoulder and the attachment paragraph is especially useful if the rotor component has an aperture penetrating the rotor component axially, which is arranged approximately in the center of the rotor component in the circumferential direction. In this case, the breakthrough is located radially outside the position of the holding surface. In particular, in such an embodiment occur uneven deformations in the rotor disk and the rotor components, which is counteracted by the inventive solution.
Dabei ist es von Vorteil, wenn sich der Durchbruch in Umfangsrichtung über zumindest dem 0,25-fachen der Breite des Rotorbauteils in Umfangsrichtung erstreckt. Besonders vorteilhaft ist es hierbei, wenn sich der Durchbruch über zumindest der 0,4-fachen Breite erstreckt. Demgegenüber sollte der Durchbruch nicht größer sein als die 0,75-fache Breite des Rotorbauteils in Umfangsrichtung. Besonders vorteilhaft ist es hierbei wieder, wenn sich der Durchbruch über maximal die 0,6-fache Breite des Rotorbauteils erstreckt.It is advantageous if the opening extends in the circumferential direction over at least 0.25 times the width of the rotor component in the circumferential direction. It is particularly advantageous if the breakthrough extends over at least 0.4 times the width. In contrast, the breakthrough should not be greater than the 0.75 times the width of the rotor component in the circumferential direction. Again, it is particularly advantageous if the opening extends over a maximum of 0.6 times the width of the rotor component.
Das Rotorbauteil kann unterschiedliche Gestalten aufweisen, wobei die Befestigungsart am Rotor vorteilhaft geeignet ist, wenn das Rotorbauteil eine im Wesentlichen flache sich in Umfangsrichtung und radial erstreckende Gestalt aufweist. Insofern treten im Rotorbauteil bei einwirkender Fliehkraft innerhalb des Rotorbauteils vorwiegend Zugspannungen und nur untergeordnete Biegespannungen auf. Beispielsweise sind die Zugspannungen in diesem Fall zumindest doppelt so groß wie die Biegespannungen.The rotor component may have different shapes, wherein the type of attachment to the rotor is advantageously suitable when the rotor component has a substantially flat in the circumferential direction and radially extending shape. In this respect occur in the rotor component with acting centrifugal force within the rotor component mainly tensile stresses and only minor bending stresses. For example, the tensile stresses in this case are at least twice as large as the bending stresses.
Zur Befestigung des Rotorbauteils am Rotor über Abstützung der Fliehkräfte vom Halteabsatz auf den Befestigungsabsatz ist es weiterhin von Vorteil, wenn sich das Rotorbauteil gegenüberliegend zum Halteabsatz mit einem inneren, zur Rotorachse weisenden Randabschnitt am Rotor abstützen kann. Hierzu weist wahlweise die Rotorscheibe einen umlaufenden, von einer Stirnseite der Rotorscheibe bzw. vom Befestigungsabsatz axial beabstandeten Ringvorsprung auf. Jedoch kann auch vorgesehen sein, dass der entsprechende Ringvorsprung an einer zur Rotorscheibe benachbarten zweiten Rotorscheibe angeordnet ist. Zumindest bildet der entsprechende Ringvorsprung an der Rotorscheibe bzw. der zweiten Rotorscheibe eine zum Befestigungsabsatz weisende Anlagefläche auf, an der der innere Randabschnitt der Rotorbauteile zur Anlage kommt.To fasten the rotor component to the rotor by supporting the centrifugal forces from the holding shoulder onto the fastening shoulder It is furthermore advantageous if the rotor component can be supported on the rotor opposite to the holding shoulder with an inner edge portion facing the rotor axis. For this purpose, optionally, the rotor disk on a circumferential, axially spaced from an end face of the rotor disk or from the fastening shoulder annular projection. However, it can also be provided that the corresponding annular projection is arranged on a second rotor disk adjacent to the rotor disk. At least the corresponding annular projection on the rotor disk or the second rotor disk forms a contact surface facing the fastening shoulder, against which the inner edge portion of the rotor components comes to rest.
In den nachfolgenden Figuren wird eine beispielhafte Ausführungsform für einen Rotor im Bereich der Verbindung zwischen Rotorbauteil und Rotorscheibe skizziert. Es zeigen:
- Fig. 1
- In der
Fig. 1 wird im Längsschnitt abschnittsweise die Rotorscheibe sowie das daran befestigte Rotorbauteil skizziert; - Fig. 2
- die
Fig. 2 zeigt die Anordnung mit der Rotorscheibe und dem Rotorbauteil in einem Schnitt quer zur Rotorachse.
- Fig. 1
- In the
Fig. 1 in sections, the rotor disk and the rotor component attached thereto are sketched in sections; - Fig. 2
- the
Fig. 2 shows the arrangement with the rotor disk and the rotor component in a section transverse to the rotor axis.
In der
Weiter zu erkennen ist das Rotorbauteil 11, welches 11 an der Rotorscheibe 01 befestigt ist. Hierzu weist das Rotorbauteil 11 einen Halteabsatz 14 auf, welcher 14 sich ebenso in Umfangsrichtung und axial erstreckt. Analog bildet der Halteabsatz 14 eine Haltefläche 15, welche 15 auf der radial auswärts weisenden Seite angeordnet ist. Hierbei ist sind die Haltefläche 15 sowie die Stützfläche 05 komplementär zueinander aufgeführt. Der Halteabsatz 14 ist nahe dem zur Rotorachse weisenden Ende des Rotorbauteils 11 angeordnet, wobei sich am Ende auf der zur Rotorachse weisenden Seite ein innerer Randabschnitt 17 befindet. Dieser 17 liegt hierbei axial an dem Ringvorsprung 07 der Rotorscheibe 01 an. Bei entsprechenden Fliehkräften aufgrund der Rotation des Rotors führte die Abstützung des Rotorbauteils 11 über den Halteabsatz 14 mit der Haltefläche 15 auf die Stützfläche 05 des Befestigungsabsatzes 04 zu einem Moment im Rotorbauteil 11, welches über die Anlage des inneren Randabschnitts 17 am Ringvorsprung 07 abgestützt wird. Weiterhin weist das Rotorbauteil 11 einen in axialer Richtung das Rotorbauteil 11 durchdringenden Durchbruch 12 auf.The
Von wesentlicher Bedeutung sind die Geometrien der Stützfläche 05 sowie der Haltefläche 15, wobei diese in axialer Richtung betrachtet über eine Auflagebreite 10 aneinander anliegen. Hierbei weist die Stützfläche 05 als Rotationsfläche um die Rotorachse einen mittleren Stützradius 06 auf. Dieser 06 ist hierbei angenommen als Radius in der Mitte der axialen Auflagebreite 10. Demgegenüber wird die Haltefläche 15 des Rotorbauteils 11 ebenso als Abschnitt einer Rotationsfläche ausgeführt und kann ebenso mit einem mittleren Halteradius 16 beschrieben werden. Der Halteradius 16 ist hierbei an gleicher axialer Position wie der Stützradius 06 bestimmt.Of essential importance are the geometries of the
Hierzu skizziert die
Wesentlich für die Erfindung ist nunmehr die Betrachtung der auf der zur Rotorachse weisenden Seite an dem Befestigungsabsatz 04 angeordneten Stützfläche 05 mit dem hier dargestellten mittleren Stützradius 06 in Verbindung mit dem Halteabsatz 14, welcher 14 radial auswärts weisend die Haltefläche 15 mit dem mittleren Halteradius 16 aufweist. Zu erkennen ist, dass hier vorgesehen ist, dass der Halteradius 16 einen geringeren Wert aufweist als es dem gegenüberliegenden entsprechenden Stützradius 06 entspricht.Essential for the invention now is the consideration of the side facing the rotor axis on the
Diese Gestalt mit der zunächst in Umfangsrichtung betrachtet nicht vollflächigen Anlage der Haltefläche 15 an der Stützfläche 05 führt bei hohen Fliehkräften aufgrund einer entsprechenden Rotation des Rotors zu einer Vergleichmäßigung der Auflagespannungen zwischen den beiden Flächen 05, 15.Due to a corresponding rotation of the rotor, this shape with the system of the holding
Claims (6)
dadurch gekennzeichnet,
dass der Halteradius (16) mindestens dem 0,99-fachen und maximal dem 0,999-fachen Stützradius (06) entspricht.Rotor, in particular a gas turbine, with a rotor disk (01), which (01) has a circumferential axially extending mounting shoulder (04) with a support surface facing the rotor axis (05), or which has a plurality of circumferentially distributed axially extending Befestigungsabätze with each having a support surface facing the rotor axis, the support surface (05) being a rotation surface rotating about the rotor axis or a portion of a rotation surface having a center support radius (06) and having a plurality of rotor components (11) distributed circumferentially (11) each having a holding shoulder (14) extending in the axial direction with a holding face (15) complementary to the supporting face (05), which (15) is a section of a rotating face with a middle holding radius (16),
characterized,
that the holding radius (16) corresponds to at least 0.99 times and at most 0.999 times the support radius (06).
dadurch gekennzeichnet,
dass die Rotorscheibe (01) eine Mehrzahl im Umfang verteilt angeordnete axial durchdringende Schaufelhaltenuten (02) aufweist und die Rotorbauteile (11) die Schaufelhaltenuten (02) auf einer Stirnseite der Rotorscheibe zumindest abschnittsweise abdecken.Rotor according to claim 1,
characterized,
that the rotor disc (01) distributes a plurality of circumferentially arranged axially penetrating Schaufelhaltenuten (02) and cover the rotor components (11), the Schaufelhaltenuten (02) on one end face of the rotor disc at least in sections.
dadurch gekennzeichnet,
dass das Rotorbauteil (11) radial außerhalb der Haltefläche (15) einen sich in axialer Richtung erstreckenden Durchbruch (12) aufweist.Rotor according to claim 1 or 2,
characterized,
that the rotor member (11) outside the support surface (15) has a portion extending in the axial direction aperture (12) radially.
dadurch gekennzeichnet,
dass sich der Durchbruch (12) in Umfangsrichtung über zumindest dem 0,25-fachen, insbesondere über zumindest dem 0,4-fachen, und/oder über maximal dem 0,75-fachen, insbesondere über maximal dem 0,6-fachen, der Breite des Rotorbauteils (11) in Umfangsrichtung erstreckt.Rotor according to claim 3,
characterized,
that the opening (12) in circumferential direction over at least the times 0.25, in particular at least 0.4 times, and / or a maximum of about 0.75 times the-, in particular a maximum of the times 0.6, the width of the rotor member (11) extends in the circumferential direction.
dadurch gekennzeichnet,
dass das Rotorbauteil (11) eine sich im Wesentlichen in Umfangsrichtung und radial erstreckende flache Gestalt aufweist, wobei sich der Halteabsatz (14) in axialer Richtung ausgehend von der flachen Gestalt erstreckt und im zur Rotorachse weisenden Drittel der radialen Erstreckung des Rotorbauteils (11) angeordnet ist.Rotor according to one of claims 1 to 4,
characterized,
in that the rotor component (11) has a substantially circumferentially and radially extending flat shape, wherein the retaining shoulder (14) extends in the axial direction starting from the flat shape and arranged in the rotor axis facing third of the radial extent of the rotor component (11) is.
dadurch gekennzeichnet,
dass die Rotorscheibe (01) und/oder eine zur Rotorscheibe (01) benachbarte zweite Rotorscheibe einen von der Stirnseite der Rotorscheibe (01) beabstandeten umlaufenden Ringvorsprung aufweist und dass das Rotorbauteil (11) auf der von der Haltefläche (15) zur Rotorachse weisenden Seite einen inneren Randabschnitt (17) aufweist, wobei sich der innere Randabschnitt (17) am Ringvorsprung (07) axial abstützt.Rotor according to one of claims 1 to 5,
characterized,
in that the rotor disk (01) and / or a second rotor disk adjacent to the rotor disk (01) has a circumferential annular projection spaced from the end face of the rotor disk (01), and in that the rotor component (11) is on the side facing the rotor axis from the holding surface (15) an inner edge portion (17), wherein the inner edge portion (17) on the annular projection (07) is axially supported.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18170613.6A EP3564489A1 (en) | 2018-05-03 | 2018-05-03 | Rotor with for centrifugal forces optimized contact surfaces |
US17/044,828 US11319824B2 (en) | 2018-05-03 | 2019-04-16 | Rotor with centrifugally optimized contact faces |
KR1020207034393A KR102498006B1 (en) | 2018-05-03 | 2019-04-16 | Rotor with contact surface optimized for centrifugal force |
EP19720467.0A EP3724456B1 (en) | 2018-05-03 | 2019-04-16 | Rotor with for centrifugal forces optimized contact surfaces |
JP2020549678A JP6995217B2 (en) | 2018-05-03 | 2019-04-16 | Rotor with contact surface optimized for centrifugal force |
CN201980029755.5A CN112119205B (en) | 2018-05-03 | 2019-04-16 | Rotor with centrifugal force optimized contact surfaces |
PCT/EP2019/059727 WO2019211091A1 (en) | 2018-05-03 | 2019-04-16 | Rotor with centrifugally optimized contact faces |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18170613.6A EP3564489A1 (en) | 2018-05-03 | 2018-05-03 | Rotor with for centrifugal forces optimized contact surfaces |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3564489A1 true EP3564489A1 (en) | 2019-11-06 |
Family
ID=62116260
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18170613.6A Withdrawn EP3564489A1 (en) | 2018-05-03 | 2018-05-03 | Rotor with for centrifugal forces optimized contact surfaces |
EP19720467.0A Active EP3724456B1 (en) | 2018-05-03 | 2019-04-16 | Rotor with for centrifugal forces optimized contact surfaces |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
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EP19720467.0A Active EP3724456B1 (en) | 2018-05-03 | 2019-04-16 | Rotor with for centrifugal forces optimized contact surfaces |
Country Status (6)
Country | Link |
---|---|
US (1) | US11319824B2 (en) |
EP (2) | EP3564489A1 (en) |
JP (1) | JP6995217B2 (en) |
KR (1) | KR102498006B1 (en) |
CN (1) | CN112119205B (en) |
WO (1) | WO2019211091A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US11415016B2 (en) * | 2019-11-11 | 2022-08-16 | Rolls-Royce Plc | Turbine section assembly with ceramic matrix composite components and interstage sealing features |
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Also Published As
Publication number | Publication date |
---|---|
US11319824B2 (en) | 2022-05-03 |
EP3724456B1 (en) | 2023-03-01 |
JP6995217B2 (en) | 2022-01-14 |
CN112119205A (en) | 2020-12-22 |
CN112119205B (en) | 2022-11-11 |
JP2021517616A (en) | 2021-07-26 |
KR20210002683A (en) | 2021-01-08 |
EP3724456A1 (en) | 2020-10-21 |
US20210095568A1 (en) | 2021-04-01 |
WO2019211091A1 (en) | 2019-11-07 |
KR102498006B1 (en) | 2023-02-10 |
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