EP2098687A1 - Rotor for a turbo engine - Google Patents
Rotor for a turbo engine Download PDFInfo
- Publication number
- EP2098687A1 EP2098687A1 EP08004272A EP08004272A EP2098687A1 EP 2098687 A1 EP2098687 A1 EP 2098687A1 EP 08004272 A EP08004272 A EP 08004272A EP 08004272 A EP08004272 A EP 08004272A EP 2098687 A1 EP2098687 A1 EP 2098687A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- damping element
- blade
- blades
- projection
- 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.)
- Withdrawn
Links
- 238000013016 damping Methods 0.000 claims abstract description 74
- 239000012858 resilient material Substances 0.000 claims abstract description 7
- 238000005452 bending Methods 0.000 abstract description 9
- 238000011161 development Methods 0.000 description 5
- 230000018109 developmental process Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 230000006378 damage Effects 0.000 description 3
- 238000003825 pressing Methods 0.000 description 2
- 229910000639 Spring steel Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- 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
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F05D2220/70—Application in combination with
- F05D2220/72—Application in combination with a steam turbine
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/12—Two-dimensional rectangular
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/13—Two-dimensional trapezoidal
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/182—Two-dimensional patterned crenellated, notched
-
- 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
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Definitions
- the invention relates to a rotor for a turbomachine, wherein the rotor has circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor.
- a steam turbine as an embodiment of a turbomachine, essentially two components are responsible for the conversion of the thermal energy of the steam into rotational energy.
- this would be the rotatably mounted rotor and a housing arranged around the rotor.
- the rotor has so-called. Blades, wherein guide vanes are arranged on the housing.
- the operating frequencies are 50 Hz and 60 Hz, respectively, for steam turbines used in the municipal power supply area.
- the rotational frequencies occurring during operation lead to unwanted vibrations of the blades in connection with the thermodynamic conditions of the steam. As a rule, cracks occur in the rotor blades, in the airfoil and / or in the blade roots.
- the blade feet can be designed as so-called double-T, hammer or pine-tree feet. All these feet have in common that they are placed in a corresponding groove in the rotor. Furthermore, turbine blade feet are known which are bent. The bend results in a distribution of the transfer area between the rotor and the turbine blades. The transmitted forces can be better distributed, resulting in an extension of the life.
- the turbine blades are arranged adjacent to each other on the circumference.
- the turbine blades have blade plates disposed between the blade roots and the airfoil.
- the rotor is formed according to the prior art such that between each two blade plates, a projection of the rotor is arranged.
- the invention begins, the object of which is to provide a rotor which has blades arranged in such a way that vibrations of the blades during operation are effectively reduced.
- a rotor for a turbomachine having circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor, wherein a damping element is arranged between the blades.
- the invention thus goes the way to enable a power transmission not only between the blades and the rotor, but also to realize a power transmission between adjacent blades.
- the power transmission takes place via the damping element, which is arranged between the blades.
- the damping element is arranged such that a counterforce from the damping element leads to the blade to a damping of the vibration.
- the damping element between the blade roots is caulked, with the applied clamping force leads to a pressing apart of the blades.
- the damping element is arranged between two adjacent blade plates.
- the blade plates are shaped in the blades so as to form a base that covers the blade root opposite the blade.
- An arranged between the blade plates damping element can dampen vibration between two blades optimally.
- the damping element is formed from a resilient material.
- a resilient material has the advantage that a bending force is required in a bending of the damping element. If a damping element made of a resilient material is arranged between two blade plates and thereby inevitably has to be bent, a force is created on the blade plates after installation of the damping element. This force leads to a pressing apart of adjacent blades. A vibration of adjacent blades is thereby reduced.
- the damping element essentially has the shape of a rod.
- the damping element has a rectangular cross-section. As a result, the damping element is comparatively easy to manufacture.
- the damping element has a trapezoidal or conical cross section. This leads to the advantage that during operation, a centrifugal force acting on the damping element due to the trapezoidal or conical sides arranged obliquely to the centrifugal force direction a force arises in the direction of the blade plates. This force caused by centrifugal force is a lateral force that further supports a pushing apart of the blades. As a result, a vibration during operation is further reduced.
- the damping element has a projection which is arranged in a recess in the blade plate.
- the protrusion of the damping element arranged in the protrusion constitutes an axial securing which is intended to prevent the damping element from becoming detached in an axial direction.
- the damping element has a kink, which is arranged in a recess in the blade plate. Since the damping element is made of a resilient material, a kink in the damping element, which has a substantially triangular shape, can be used to serve as an axial securing element.
- a trained as a simple kink securing element has the advantage that engages in the projection as a result of the elastic material of the damping element of the kink. Damage to the damping element is therefore almost impossible. In addition, an excellent axial securing of the damping element is ensured.
- the FIG. 1 discloses a part of a rotor 1.
- the rotor 1 is in the FIG. 1 shown in a plan view. To see several grooves 2, which are designed to receive a blade, not shown.
- the rotor 1 is formed along an axial direction 3.
- the groove 2 is designed so bent to the axial direction 3 that a curved curve 4 is formed.
- a likewise bent blade root 5 of a blade is arranged.
- FIG. 7 is a cross-sectional view of a portion of the rotor 1 according to the prior art shown.
- the axial direction 3 points to the normal of the plane of the drawing.
- the Blade feet 5, which may have a fir tree root, a double T-shape or the like, have a blade plate 6.
- the blade plate 6 adjoins an end face 7 of a rotor projection 8 of the rotor 1.
- the blade plate 6 and the rotor projection 8 are in this case designed such that a force between the blade plate 6 and the rotor projection 8 is formed.
- FIG. 3 is also shown a cross-sectional view of the rotor 1 according to the prior art.
- the circular section A is in the FIG. 7 magnified reproduced.
- FIG. 2 is an inventive design of the rotor 1 can be seen.
- the rotor 1 is initially developed in such a way that the rotor projection 8 is removed.
- a damping element 9 is arranged between the blade plates 6.
- FIG. 9 a cross-sectional view of the damping element 9 can be seen.
- the damping element 9 may have a rectangular cross-section in a first embodiment. Accordingly, the blade plates 6 corresponding recesses 10 for receiving the damping element 9.
- the damping element 9 is made of a resilient material that can be bent along the curved curve 4. However, due to the bending of the damping element 9 along the curved curve 4, a bending force is generated which generates a force between the blade plates 6. This results in each case a bending force 11 in the direction of the blade plates 6.
- the in the FIG. 9 Arrows shown symbolically show the direction of the bending force 11, which are caused by the elastic properties of the damping element 9.
- the damping element 9 is trapezoidal or conical in cross-section, which in the FIG. 8 is shown.
- the recesses 10 have for this purpose also a complementary shape to the damping element 9.
- the damping element 9 and the recess 10 are formed such that the smallest possible gap forms therebetween.
- damping element 9 is shown in the non-installed state. When installed, the damping element 9 would be shown bent. This in FIG. 4 shown damping element 9 has a rectangular cross-section. In addition, the damping element 9 is formed as a rod. This has the advantage that the damping element 9 can be made comparatively quickly.
- the damping element 9 has a trapezoidal or conical cross section 12.
- the damping element 9 comprises two support flanks 13, wherein in the FIGS. 4 to 6 only a support edge 13 can be seen.
- the support flanks 13 are in accordance with the embodiment FIG. 4 formed parallel to each other, whereas in the embodiment according to FIG. 5 the support flanks 13 are formed at an angle ⁇ against each other.
- a centrifugal force 14 acts on the damping element 9.
- the centrifugal force 14 causes a force in the direction of the blade plates 6, which points in the direction of the bending force 11. This means that the bending force 11 is supported by the trapezoidal design of the damping element 9 with the centrifugal force. Dampings are thereby further increased, resulting in a reduction of the vibrations.
- FIG. 6 shows a damping element 9 with a trapezoidal cross-section 12, wherein the damping element 9 has a kink 15.
- the bend 15 leads to a formation of a projection 16.
- This projection 16 relative to the support flank 13 is in a corresponding recess 17 in the Blade plate 6 adapted. As a result, slipping of the damping element 9 in a longitudinal direction 18 is avoided.
- the projection 16 is achieved essentially by three bends 19 of the damping element 9. For this purpose, first the damping element 9 is bent along a first bend 19 '. Subsequently, the damping element 9 is bent back in an opposite direction along the second bend 19 'and then bent along the third bend 19' '' again such that the damping element 9 is substantially aligned again in a straight longitudinal direction 18.
- damping element 9 As a material for the damping element 9, for example spring steel can be used. In alternative embodiments, well-known blade steels, such as e.g. X20Cr13 can be used.
- the use of the damping elements 9 offers, inter alia, the advantage that the main flow is not disturbed. Another advantage is that the damping element 9 can be dismantled without destruction from the rotor 1. It is also an advantage that no additional grooves in the rotor 1 must be incorporated.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Die Erfindung betrifft einen Rotor (1) für eine Strömungsmaschine, wobei der Rotor (1) mehrere Schaufeln aufweist, die mittels Dämpfungselement (9) gegeneinander versteift sind, wobei das Dämpfungselement (9) aus einem federelastischen Material ausgebildet ist und den bogenförmigen Verlauf der Schaufelfüße folgt, um dadurch eine Biegekraft in Richtung der Schaufeln zu erzeugen. The invention relates to a rotor (1) for a turbomachine, wherein the rotor (1) has a plurality of blades which are stiffened against each other by means of damping element (9), wherein the damping element (9) is formed from a resilient material and the arcuate course of the blade roots follows to thereby generate a bending force in the direction of the blades.
Description
Die Erfindung betrifft einen Rotor für eine Strömungsmaschine, wobei der Rotor in Umfangsrichtung benachbart angeordnete Schaufeln aufweist, wobei der Rotor entlang einer axialen Richtung ausgebildet ist, wobei die Schaufeln einen gebogenen Schaufelfuß aufweisen, wobei der Schaufelfuß in einer Schaufelnut im Rotor angeordnet ist.The invention relates to a rotor for a turbomachine, wherein the rotor has circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor.
Unter einer Strömungsmaschine wird beispielsweise eine Dampfturbine verstanden.Under a turbomachine, for example, a steam turbine is understood.
In einer Dampfturbine als Ausführungsform einer Strömungsmaschine sind im Wesentlichen zwei Komponenten für die Umsetzung der thermischen Energie des Dampfes in Rotationsenergie verantwortlich. Zum einen wären dies der drehbar gelagerte Rotor und ein um den Rotor angeordnetes Gehäuse. Der Rotor weist sog. Laufschaufeln auf, wobei am Gehäuse Leitschaufeln angeordnet sind. Die Frequenzen im Betrieb betragen für Dampfturbinen, die im kommunalen Energieversorgungsbereich eingesetzt werden, 50 Hz bzw. 60 Hz. Die im Betrieb auftretenden Rotationsfrequenzen führen im Zusammenhang mit den thermodynamischen Verhältnissen des Dampfes zu unerwünschten Schwingungen der Laufschaufeln. In der Regel treten Risse in den Laufschaufeln, im Schaufelblatt und/oder in den Schaufelfüßen auf. Die Schaufelfüße können als sog. Doppel-T-, Hammer- oder als Tannenbaumfüße ausgebildet sein. Allen diesen Füßen ist gemeinsam, dass sie in eine entsprechende Nut im Rotor angeordnet werden. Des Weiteren sind Turbinenschaufelfüße bekannt, die gebogen sind. Die Biegung führt zu einer Verteilung der Übertragungsfläche zwischen dem Rotor und den Turbinenschaufeln. Die übertragenen Kräfte können dadurch besser verteilt werden, was zu einer Verlängerung der Lebensdauer führt.In a steam turbine as an embodiment of a turbomachine, essentially two components are responsible for the conversion of the thermal energy of the steam into rotational energy. On the one hand, this would be the rotatably mounted rotor and a housing arranged around the rotor. The rotor has so-called. Blades, wherein guide vanes are arranged on the housing. The operating frequencies are 50 Hz and 60 Hz, respectively, for steam turbines used in the municipal power supply area. The rotational frequencies occurring during operation lead to unwanted vibrations of the blades in connection with the thermodynamic conditions of the steam. As a rule, cracks occur in the rotor blades, in the airfoil and / or in the blade roots. The blade feet can be designed as so-called double-T, hammer or pine-tree feet. All these feet have in common that they are placed in a corresponding groove in the rotor. Furthermore, turbine blade feet are known which are bent. The bend results in a distribution of the transfer area between the rotor and the turbine blades. The transmitted forces can be better distributed, resulting in an extension of the life.
Die Turbinenschaufeln sind hierbei auf dem Umfang benachbart nebeneinander angeordnet. Die Turbinenschaufeln weisen Schaufelplatten auf, die zwischen den Schaufelfüßen und dem Schaufelblatt angeordnet sind. Der Rotor wird gemäß dem Stand der Technik derart ausgebildet, dass zwischen jeweils zwei Schaufelplatten ein Vorsprung des Rotors angeordnet ist.The turbine blades are arranged adjacent to each other on the circumference. The turbine blades have blade plates disposed between the blade roots and the airfoil. The rotor is formed according to the prior art such that between each two blade plates, a projection of the rotor is arranged.
Obwohl die Laufschaufeln in die entsprechenden Nuten eingestemmt werden, treten im Betrieb vergleichsweise hohe, unerwünschte Schwingungen auf. Diese Schwingungen führen zu einer Verkürzung der Lebensdauer, wobei es auch vorkommen kann, dass Risse auftreten und somit zu einer Beschädigung führen. Wünschenswert wäre es eine Möglichkeit zu haben, mit der die Schwingungen der Laufschaufeln wirksam verhindert werden. An dieser Stelle setzt die Erfindung an, deren Aufgabe es ist, einen Rotor anzugeben, der Schaufeln aufweist, die derart angeordnet sind, dass Schwingungen der Schaufeln im Betrieb wirksam verringert werden.Although the blades are caulked into the respective grooves, comparatively high, undesirable vibrations occur during operation. These vibrations lead to a shortening of the lifetime, whereby it can also happen that cracks occur and thus lead to damage. It would be desirable to have a possibility with which the vibrations of the blades are effectively prevented. At this point, the invention begins, the object of which is to provide a rotor which has blades arranged in such a way that vibrations of the blades during operation are effectively reduced.
Gelöst wird diese Aufgabe durch einen Rotor für eine Strömungsmaschine, wobei der Rotor in Umfangsrichtung benachbart angeordnete Schaufeln aufweist, wobei der Rotor entlang einer axialen Richtung ausgebildet ist, wobei die Schaufeln einen gebogenen Schaufelfuß aufweisen, wobei der Schaufelfuß in einer Schaufelnut im Rotor angeordnet ist, wobei zwischen den Schaufeln ein Dämpfungselement angeordnet ist.This object is achieved by a rotor for a turbomachine, the rotor having circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a blade groove in the rotor, wherein a damping element is arranged between the blades.
Die Erfindung geht damit den Weg, eine Kraftübertragung nicht nur zwischen den Schaufeln und dem Rotor zu ermöglichen, sondern auch eine Kraftübertragung zwischen benachbarten Schaufeln zu realisieren. Die Kraftübertragung erfolgt über das Dämpfungselement, das zwischen den Schaufeln angeordnet ist. Sobald eine Schaufel schwingt, wird diese Schwingung über das Dämpfungselement an die benachbarte Schaufel übertragen, allerdings ist das Dämpfungselement derart angeordnet, dass eine Gegenkraft von dem Dämpfungselement auf die Schaufel zu einer Dämpfung der Schwingung führt. Dazu ist das Dämpfungselement zwischen den Schaufelfüßen eingestemmt, wobei die dafür aufzubringende Stemmkraft zu einem Auseinanderdrücken der Schaufeln führt.The invention thus goes the way to enable a power transmission not only between the blades and the rotor, but also to realize a power transmission between adjacent blades. The power transmission takes place via the damping element, which is arranged between the blades. As soon as one blade vibrates, this vibration is transmitted via the damping element to the adjacent blade, however, the damping element is arranged such that a counterforce from the damping element leads to the blade to a damping of the vibration. For this purpose, the damping element between the blade roots is caulked, with the applied clamping force leads to a pressing apart of the blades.
In den Unteransprüchen sind vorteilhafte Weiterbildungen angegeben.In the dependent claims advantageous developments are given.
So ist es vorteilhaft, wenn das Dämpfungselement zwischen zwei benachbarten Schaufelplatten angeordnet ist. Die Schaufelplatten sind bei den Laufschaufeln derart geformt, dass sie eine Grundfläche bilden, die den Schaufelfuß gegenüber dem Schaufelblatt abdeckt. Ein zwischen den Schaufelplatten angeordnetes Dämpfungselement kann eine Schwingung zwischen zwei Schaufeln optimal dämpfen.Thus, it is advantageous if the damping element is arranged between two adjacent blade plates. The blade plates are shaped in the blades so as to form a base that covers the blade root opposite the blade. An arranged between the blade plates damping element can dampen vibration between two blades optimally.
In einer vorteilhaften Weiterbildung ist das Dämpfungselement aus einem federelastischen Material ausgebildet.In an advantageous development, the damping element is formed from a resilient material.
Ein federelastisches Material hat den Vorteil, dass bei einer Biegung des Dämpfungselementes eine Biegekraft erforderlich ist. Wenn ein Dämpfungselement aus einem federelastischen Material zwischen zwei Schaufelplatten angeordnet wird und dabei zwangsläufig gebogen werden muss, entsteht nach dem Einbau des Dämpfungselementes eine Kraft auf die Schaufelplatten. Diese Kraft führt zu einem Auseinanderdrücken von benachbarten Schaufeln. Eine Schwingung von benachbarten Schaufeln wird dadurch verringert.A resilient material has the advantage that a bending force is required in a bending of the damping element. If a damping element made of a resilient material is arranged between two blade plates and thereby inevitably has to be bent, a force is created on the blade plates after installation of the damping element. This force leads to a pressing apart of adjacent blades. A vibration of adjacent blades is thereby reduced.
In einer vorteilhaften Weiterbildung weist das Dämpfungselement im Wesentlichen die Form eines Stabes auf. Vorteilhafterweise weist das Dämpfungselement einen rechteckigen Querschnitt auf. Dadurch ist das Dämpfungselement vergleichweise leicht herzustellen.In an advantageous development, the damping element essentially has the shape of a rod. Advantageously, the damping element has a rectangular cross-section. As a result, the damping element is comparatively easy to manufacture.
In einer vorteilhaften Weiterbildung weist das Dämpfungselement einen trapezförmigen oder konischen Querschnitt auf. Dies führt zu dem Vorteil, dass im Betrieb eine auf das Dämpfungselement wirkende Fliehkraft wegen der schief zur Fliehkraftrichtung angeordneten trapezförmigen oder konischen Seiten eine Kraft in Richtung der Schaufelplatten entsteht. Diese durch Fliehkraft hervorgerufene Kraft ist eine Querkraft, die ein Auseinanderdrücken der Schaufeln weiter unterstützt. Dadurch ist eine Schwingung während des Betriebs weiterhin verringert.In an advantageous development, the damping element has a trapezoidal or conical cross section. This leads to the advantage that during operation, a centrifugal force acting on the damping element due to the trapezoidal or conical sides arranged obliquely to the centrifugal force direction a force arises in the direction of the blade plates. This force caused by centrifugal force is a lateral force that further supports a pushing apart of the blades. As a result, a vibration during operation is further reduced.
In einer vorteilhaften Weiterbildung weist das Dämpfungselement einen Vorsprung auf, der in einer Ausbuchtung in der Schaufelplatte angeordnet ist. Der in der Ausbuchtung angeordnete Vorsprung des Dämpfungselementes stellt eine axiale Sicherung dar, die verhindern soll, dass das Dämpfungselement in einer axialen Richtung sich löst.In an advantageous development, the damping element has a projection which is arranged in a recess in the blade plate. The protrusion of the damping element arranged in the protrusion constitutes an axial securing which is intended to prevent the damping element from becoming detached in an axial direction.
Vorteilhafterweise weist das Dämpfungselement einen Knick auf, der in einer Ausbuchtung in der Schaufelplatte angeordnet ist. Da das Dämpfungselement aus einem federelastischen Material ist, kann ein Knick im Dämpfungselement, der im Wesentlichen eine dreieckige Form aufweist, dazu genutzt werden, um als axiales Sicherungselement zu dienen. Ein als einfacher Knick ausgebildetes Sicherungselement hat den Vorteil, dass in Folge des elastischen Materials des Dämpfungselementes der Knick in den Vorsprung eingreift. Eine Beschädigung des Dämpfungselementes ist daher nahezu ausgeschlossen. Zudem ist eine hervorragende axiale Sicherung des Dämpfungselementes gewährleistet.Advantageously, the damping element has a kink, which is arranged in a recess in the blade plate. Since the damping element is made of a resilient material, a kink in the damping element, which has a substantially triangular shape, can be used to serve as an axial securing element. A trained as a simple kink securing element has the advantage that engages in the projection as a result of the elastic material of the damping element of the kink. Damage to the damping element is therefore almost impossible. In addition, an excellent axial securing of the damping element is ensured.
Ausführungsbeispiele der Erfindung werden nachfolgend anhand der Zeichnungen beschrieben. Diese sollen das Ausführungsbeispiel nicht maßstäblich darstellen, vielmehr sind die Zeichnungen, wozu Erläuterungen dienen, in schematischer und/oder leicht versetzter Form ausgeführt. Im Hinblick auf Ergänzungen der aus den Zeichnungen unmittelbar erkennbaren Lehren wird auf den einschlägigen Stand der Technik verwiesen.Embodiments of the invention will be described below with reference to the drawings. These are not intended to represent the embodiment to scale, but the drawings, to which explanations serve, executed in a schematic and / or slightly offset form. With regard to additions to the teachings directly recognizable from the drawings reference is made to the relevant prior art.
Es zeigen:
Figur 1- eine Draufsicht auf einen Ausschnitt eines Rotors gemäß dem Stand der Technik,
Figur 2- einen Ausschnitt eines Rotors gemäß der Erfindung,
Figur 3- eine Querschnittsansicht in axialer Richtung gesehen einen Teils des Rotors gemäß dem Stand der Technik,
Figur 4- ein Dämpfungselement,
Figur 5- ein Dämpfungselement in alternativer Ausführungsform,
Figur 6- ein Dämpfungselement in alternativer Ausführungsform,
Figur 7- eine Querschnittsansicht eines Teils des Rotors gemäß dem Stand der Technik,
Figur 8- eine Querschnittsansicht eines Teils des Rotors mit einem Dämpfungselement,
Figur 9- eine Querschnittsansicht eines Teils eines Rotors mit einer alternativen Ausführungsform des Dämpfungselementes.
- FIG. 1
- a top view of a section of a rotor according to the prior art,
- FIG. 2
- a section of a rotor according to the invention,
- FIG. 3
- a cross-sectional view in the axial direction seen a part of the rotor according to the prior art,
- FIG. 4
- a damping element,
- FIG. 5
- a damping element in an alternative embodiment,
- FIG. 6
- a damping element in an alternative embodiment,
- FIG. 7
- a cross-sectional view of a part of the rotor according to the prior art,
- FIG. 8
- a cross-sectional view of a portion of the rotor with a damping element,
- FIG. 9
- a cross-sectional view of a portion of a rotor with an alternative embodiment of the damping element.
Die
In der
Die Schaufelplatte 6 und der Rotorvorsprung 8 sind hierbei derart ausgebildet, dass eine Kraft zwischen der Schaufelplatte 6 und dem Rotorvorsprung 8 entsteht.The
In der
In der
In einer alternativen Ausführungsform ist das Dämpfungselement 9 trapezförmig oder konisch im Querschnitt ausgebildet, was in der
In der
In der
Die
Der Vorsprung 16 wird im Wesentlichen durch drei Biegungen 19 des Dämpfungselementes 9 erreicht. Dazu wird zunächst das Dämpfungselement 9 entlang einer ersten Biegung 19' gebogen. Anschließend wird in einer entgegengesetzten Richtung das Dämpfungselement 9 entlang der zweiten Biegung 19' zurückgebogen und anschließend entlang der dritten Biegung 19''' wieder derart gebogen, dass das Dämpfungselement 9 im Wesentlichen wieder in einer geradlinigen Längsrichtung 18 ausgerichtet ist.The projection 16 is achieved essentially by three
Als Material für das Dämpfungselement 9 kann beispielsweise Federstahl verwendet werden. In alternativen Ausführungsformen können ebenso bekannte Schaufelstähle, wie z.B. X20Cr13 verwendet werden. Die Verwendung der Dämpfungselemente 9 bietet unter anderem den Vorteil, dass die Hauptströmung nicht gestört wird. Ein weiterer Vorteil ist, dass das Dämpfungselement 9 zerstörungsfrei aus dem Rotor 1 demontiert werden kann. Ebenso ist es ein Vorteil, dass keine zusätzlichen Nuten im Rotor 1 eingearbeitet werden müssen.As a material for the damping
Claims (10)
wobei der Rotor (1) in Umfangsrichtung benachbart angeordnete Schaufeln aufweist,
wobei der Rotor (1) entlang einer axialen Richtung (3) ausgebildet ist,
wobei die Schaufeln einen gebogenen Schaufelfuß (5) aufweisen,
wobei der Schaufelfuß (5) in einer Nut (2) im Rotor (1) angeordnet ist,
dadurch gekennzeichnet, dass
zwischen den Schaufeln ein Dämpfungselement (9) angeordnet ist.Rotor (1) for a turbomachine,
the rotor (1) having circumferentially adjacent vanes,
wherein the rotor (1) is formed along an axial direction (3),
the blades having a curved blade root (5),
wherein the blade root (5) is arranged in a groove (2) in the rotor (1),
characterized in that
a damping element (9) is arranged between the blades.
wobei der Schaufelfuß (5) gegen die axiale Richtung (3) gebogen ist.Rotor (1) according to claim 1,
wherein the blade root (5) is bent against the axial direction (3).
wobei der Schaufelfuß (5) eine Schaufelplatte (6) aufweist und das Dämpfungselement (9) zwischen zwei benachbarten Schaufelplatten (6) angeordnet ist.Rotor (1) according to claim 1 or 2,
wherein the blade root (5) has a blade plate (6) and the damping element (9) is arranged between two adjacent blade plates (6).
wobei die Schaufelplatte (6) als Vorsprung ausgebildet ist.Rotor (1) according to claim 3,
wherein the blade plate (6) is formed as a projection.
wobei das Dämpfungselement (9) aus einem federelastischen Material besteht.Rotor (1) according to one of the preceding claims,
wherein the damping element (9) consists of a resilient material.
wobei das Dämpfungselement (9) im Wesentlichen die Form eines Stabes aufweist.Rotor (1) according to one of the preceding claims,
wherein the damping element (9) has substantially the shape of a rod.
wobei das Dämpfungselement (9) einen rechteckigen Querschnitt aufweist.Rotor (1) according to claim 6,
wherein the damping element (9) has a rectangular cross-section.
wobei das Dämpfungselement (9) einen trapezförmigen oder konischen Querschnitt aufweist.Rotor (1) according to claim 6,
wherein the damping element (9) has a trapezoidal or conical cross section.
wobei das Dämpfungselement (9) einen Vorsprung aufweist, der in einer Ausbuchtung in der Schaufelplatte (6) angeordnet ist.Rotor (1) according to one of the preceding claims,
wherein the damping element (9) has a projection which is arranged in a recess in the blade plate (6).
wobei das Dämpfungselement (9) einen Knick (15) aufweist, der in einer Ausnehmung (17) in der Schaufelplatte (6) angeordnet ist.Rotor (1) according to one of claims 1 to 8,
wherein the damping element (9) has a kink (15) which is arranged in a recess (17) in the blade plate (6).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08004272A EP2098687A1 (en) | 2008-03-07 | 2008-03-07 | Rotor for a turbo engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08004272A EP2098687A1 (en) | 2008-03-07 | 2008-03-07 | Rotor for a turbo engine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2098687A1 true EP2098687A1 (en) | 2009-09-09 |
Family
ID=39495232
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08004272A Withdrawn EP2098687A1 (en) | 2008-03-07 | 2008-03-07 | Rotor for a turbo engine |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2098687A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3342983A1 (en) * | 2017-01-03 | 2018-07-04 | United Technologies Corporation | Blade, corresponding gas turbine engine and method of damping vibration between adjoining blades |
US10662784B2 (en) | 2016-11-28 | 2020-05-26 | Raytheon Technologies Corporation | Damper with varying thickness for a blade |
US10677073B2 (en) | 2017-01-03 | 2020-06-09 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
CN115030916A (en) * | 2021-03-04 | 2022-09-09 | 中国航发商用航空发动机有限责任公司 | Compressor rotor and aero-engine |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2235272A1 (en) * | 1973-06-26 | 1975-01-24 | Rolls Royce | |
DE19940556A1 (en) * | 1999-08-26 | 2001-03-01 | Asea Brown Boveri | Device for cooling guide vanes or rotor blades in a gas turbine |
EP1124038A1 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blading |
US6371727B1 (en) * | 2000-06-05 | 2002-04-16 | The Boeing Company | Turbine blade tip shroud enclosed friction damper |
-
2008
- 2008-03-07 EP EP08004272A patent/EP2098687A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2235272A1 (en) * | 1973-06-26 | 1975-01-24 | Rolls Royce | |
DE19940556A1 (en) * | 1999-08-26 | 2001-03-01 | Asea Brown Boveri | Device for cooling guide vanes or rotor blades in a gas turbine |
EP1124038A1 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blading |
US6371727B1 (en) * | 2000-06-05 | 2002-04-16 | The Boeing Company | Turbine blade tip shroud enclosed friction damper |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10662784B2 (en) | 2016-11-28 | 2020-05-26 | Raytheon Technologies Corporation | Damper with varying thickness for a blade |
EP3342983A1 (en) * | 2017-01-03 | 2018-07-04 | United Technologies Corporation | Blade, corresponding gas turbine engine and method of damping vibration between adjoining blades |
US10677073B2 (en) | 2017-01-03 | 2020-06-09 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10731479B2 (en) | 2017-01-03 | 2020-08-04 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
CN115030916A (en) * | 2021-03-04 | 2022-09-09 | 中国航发商用航空发动机有限责任公司 | Compressor rotor and aero-engine |
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