EP2614220B1 - Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles - Google Patents

Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles Download PDF

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Publication number
EP2614220B1
EP2614220B1 EP11751877.9A EP11751877A EP2614220B1 EP 2614220 B1 EP2614220 B1 EP 2614220B1 EP 11751877 A EP11751877 A EP 11751877A EP 2614220 B1 EP2614220 B1 EP 2614220B1
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EP
European Patent Office
Prior art keywords
rotor
recesses
region
recess
rotation
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
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EP11751877.9A
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German (de)
French (fr)
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EP2614220A1 (en
Inventor
Thomas Hofbauer
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Siemens AG
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Siemens AG
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Publication of EP2614220A1 publication Critical patent/EP2614220A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F05D2220/31—Application in turbines in steam 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
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a rotor for a turbomachine with a discharge area.
  • Rotors which are used for turbomachines, especially steam turbines, must meet increased requirements. At present, such rotors have to withstand high steam temperatures, which leads to a demand for good materials with good material strength. In addition, steam turbines are required with ever higher turbine power, which means that the torque moments on the rotor are increased. Furthermore, a slender embodiment is required of the rotors for the steam turbines, which in turn leads to an increased polar moment of resistance. In addition, a more flexible driving style is often desired by the customer. Such a flexible driving leads to increased thermal stresses in a fast start, resulting in an increased load on the rotors.
  • a rotor for a steam turbine is essentially cylindrical along an axis of rotation and experiences different thermal and mechanical loads along the axis of rotation. For example, in the inflow region, the rotor is exposed to high thermal loads. Basically, a rotor must meet the following requirements, which, however, have contradictory objectives.
  • a rotor with a constant cross-section or constant resistance moment curve along the turbine axis or rotation axis is desired on the part of the rotor dynamics. This means that, taking account of notch factors, the rotor can withstand the power to be transmitted and the resulting torsional moment at any axial position along the axis of rotation.
  • relief grooves have to be considered for the reduction of thermally induced stresses in the rotor. Such relief grooves lie essentially in the inflow region of the steam turbine and locally reduce the cross section and the polar moment of resistance.
  • EP2264281A2 discloses anti-vortex recesses for a gas turbine engine compressor.
  • the object is achieved by a rotor for a turbomachine with a discharge region, wherein a plurality of recesses arranged in the circumferential direction are arranged.
  • the invention proceeds from the previous design, in which a relief groove is provided with rotationally symmetrical and circular cross sections in the inflow region. Rather, the rotor is provided according to the invention in the relief region with recesses which are arranged in the circumferential direction. These recesses are arranged in the circumferential direction about an axis of rotation and have a non-axisymmetric cross-sectional profile.
  • the cross-sectional profile has including notches and flanks, which run like a thread helically in a helical line.
  • This embodiment of the relief region of the rotor initially ensures that torsional moments are suitably transmitted, since the diameter of the rotor is substantially unchanged. Furthermore, thermally induced stresses in the discharge region can still be reduced, since the recesses derive the thermally induced voltages.
  • the recesses are arranged at equidistant intervals from each other.
  • imbalances and unwanted disturbing rotor dynamics can be prevented.
  • the rotor dynamics can continue to be positively influenced. Imbalance can be effectively avoided.
  • the recesses are formed substantially elongated.
  • the recesses are inclined at an angle ⁇ , which is between 10 ° and 80 °, preferably at 45 °, to the axis of rotation.
  • the recesses have a depth, wherein this depth first increases in the axial direction and then decreases.
  • the recess has a beginning and an end region, wherein the recess terminates flush with the rotor surface in the beginning and end regions.
  • notch influences are almost minimized, which has a positive effect on the rotor dynamics and on the mechanical properties of the rotor.
  • FIG. 1 shows a cross section through a part of a steam turbine 1.
  • the steam turbine 1 has essentially an outer casing 2 and an inner casing 3 arranged inside the outer casing 2.
  • a rotor 5 arranged around a rotation axis 4 is rotatably mounted.
  • the rotor 5 has in the direction of the axis of rotation successively arranged blade rows 6, wherein only the first two rows are provided with the reference numeral 6.
  • a vapor with high temperatures and high pressures usually flows into an inflow region 8 in the steam turbine and relaxes in the flow channel 9 in the direction of the axis of rotation 4 and flows alternately through the blade rows 6 and the guide blade rows 7.
  • the temperature of the vapor decreases, whereby the pressure decreases.
  • the rotor is rotated in this case and rotates in operation generally constant at 3000 rev / min or 3600 rev / min.
  • the high steam temperatures and pressures as well as the comparatively high rotation frequency lead to high thermal and mechanical loads.
  • the requirements for the rotor 5 are particularly high.
  • FIG. 2 is an illustration of a rotor according to the prior art.
  • the inflow region 8 is provided with a relief groove 10.
  • This relief groove 10 is formed according to the prior art substantially rotationally symmetrical or circular. This means that seen in cross section, the relief groove 11 is a circular section.
  • a circular relief groove 10 is not ideal for strength reasons, since the inner diameter 12 is reduced, which could lead to undesirable strength disadvantages.
  • a foot groove 13 is arranged in the rotation axis direction. In this facednut 13, in the FIG. 2 is designed as a hammerheadlutinut, a blade not shown is arranged.
  • FIG. 3 an inventive embodiment of the relief groove 10 is shown.
  • the relief groove surface 14 is formed substantially parallel to the axis of rotation 4.
  • recesses 15 are arranged in the relief region, which are arranged in the circumferential direction 16. These recesses 15 can be milled into the relief groove surface 14 or incorporated by other processing methods.
  • the recesses 15 have a distance 17 to each other, this distance 17 from recess 15 to recess 15 is constant. Therefore, the recesses 15 are arranged at equidistant intervals.
  • the recesses 15 have a width and a length, wherein the length is greater than the width.
  • the recesses 15 are in this case formed in the circumferential direction 16 is substantially identical to each other to avoid unwanted rotor dynamics.
  • the recesses 15 are inclined at an angle ⁇ , which is between 10 ° and 80 °, preferably at 45 °, to the axis of rotation 4. Further advantageous angular ranges are 10 ° to 70 °, 20 ° to 60 °, 30 ° to 50 ° and 10 ° to 70 °, 10 ° to 60 °, 10 ° to 50 ° and 20 ° to 80 °, 30 ° to 80 °, 40 ° to 80 °, 50 ° to 80 °.
  • the course of the recesses 15 is similar to a thread, which means that the recesses 15 extend helically in a helix.
  • the recesses 15 are therefore formed non-axisymmetric.
  • the angle ⁇ is determined between a parallel to the axis of rotation 4 and the elongated configuration of the recess 15.
  • the FIG. 4 shows a cross-sectional view along the line AA from the FIG. 3 , This view thus represents a view in the direction of the axis of rotation 4.
  • the recesses 15 are in this case distributed at equidistant intervals 17 in the circumferential direction 16.
  • the recesses 15 have a core radius 18, which from the bottom 19 of the recess to the axis of rotation 4 out is determined.
  • the recess 15 is determined by the outer radius 20, which is determined by the relief groove surface 14 and the axis of rotation 4.
  • the recesses 15 are seen in cross-section rectangular or trapezoidal, wherein at the transitions 21 for reasons of strength no corners should be formed.
  • the bottom 19 and a side wall 22 are characterized by flowing transitions. This means that the transitions are characterized by a radius that is not shown in detail. At least disturbing notch effects should be avoided in this transition 21.
  • the FIG. 5 shows a side view of the rotor 5.
  • the recesses 15 are in this case formed in the direction of rotation axis out such that the core radius 18 varies in the direction of rotation axis.
  • the core radius 18 in an initial region 23 and an end region 24 is flush with the outer radius 20.
  • the recess 15 in the initial 23 and end region 24 is flush with the relief groove surface 14.
  • the recess 15 has a continuous course in its longitudinal direction.
  • the FIG. 5 shows a section through a relief groove 15. This means that the cut according to FIG. 5 not parallel to the axis of rotation 4, but substantially parallel to a side wall 22 is executed.
  • the core radius 18 is selected such that the course of the bottom 19 of the recess 15 is rotationally symmetrical or circular.
  • the inflow region (8) is designed to flow with live steam.

Description

Die Erfindung betrifft einen Rotor für eine Strömungsmaschine mit einem Entlastungsbereich.The invention relates to a rotor for a turbomachine with a discharge area.

Rotoren, die für Strömungsmaschinen, insbesondere Dampfturbinen, eingesetzt werden, müssen erhöhten Anforderungen gerecht werden. Derzeit müssen solche Rotoren hohen Dampftemperaturen standhalten, was zu einem Bedarf an guten Werkstoffen mit einer guten Werkstofffestigkeit führt. Darüber hinaus werden Dampfturbinen mit immer höheren Turbinenleistungen gefordert, was dazu führt, dass die Widerstandsmomente am Rotor erhöht werden. Des Weiteren wird an die Rotoren für die Dampfturbinen eine schlanke Ausführungsform gefordert, was wiederum zu einem erhöhten polaren Widerstandsmoment führt. Darüber hinaus ist eine flexiblere Fahrweise oftmals kundenseitig gewünscht. Solch eine flexible Fahrweise führt zu erhöhten thermischen Spannungen bei einem schnellen Anfahren, was zu einer erhöhten Belastung der Rotoren führt.Rotors, which are used for turbomachines, especially steam turbines, must meet increased requirements. At present, such rotors have to withstand high steam temperatures, which leads to a demand for good materials with good material strength. In addition, steam turbines are required with ever higher turbine power, which means that the torque moments on the rotor are increased. Furthermore, a slender embodiment is required of the rotors for the steam turbines, which in turn leads to an increased polar moment of resistance. In addition, a more flexible driving style is often desired by the customer. Such a flexible driving leads to increased thermal stresses in a fast start, resulting in an increased load on the rotors.

Ein Rotor für eine Dampfturbine ist im Wesentlichen entlang einer Rotationsachse zylindrisch ausgeführt und erfährt entlang der Rotationsachse unterschiedliche thermische und mechanische Belastungen. So ist beispielsweise im Einströmbereich der Rotor hohen thermischen Belastungen ausgesetzt. Grundsätzlich muss ein Rotor den nachfolgend genannten Anforderungen gerecht werden, die allerdings widersprüchliche Zielsetzungen aufweisen. So ist zum einen seitens der Rotordynamik ein Rotor mit möglichst konstantem Querschnitt bzw. konstantem Widerstandsmomentverlauf entlang der Turbinenachse bzw. Rotationsachse gewünscht. Dies bedeutet, dass unter Berücksichtigung von Kerbfaktoren der Rotor aus der zu übertragenden Leistung und dem daraus entstehenden Torsionsmoment an jeder axialen Position entlang der Rotationsachse standhält. Auf der anderen Seite sind Entlastungsnuten für den Abbau thermisch induzierter Spannungen im Rotor zu berücksichtigen. Solche Entlastungsnuten liegen im Wesentlichen im Einströmbereich der Dampfturbine und reduzieren den Querschnitt sowie das polare Widerstandsmoment lokal.A rotor for a steam turbine is essentially cylindrical along an axis of rotation and experiences different thermal and mechanical loads along the axis of rotation. For example, in the inflow region, the rotor is exposed to high thermal loads. Basically, a rotor must meet the following requirements, which, however, have contradictory objectives. On the one hand, a rotor with a constant cross-section or constant resistance moment curve along the turbine axis or rotation axis is desired on the part of the rotor dynamics. This means that, taking account of notch factors, the rotor can withstand the power to be transmitted and the resulting torsional moment at any axial position along the axis of rotation. On the other hand, relief grooves have to be considered for the reduction of thermally induced stresses in the rotor. Such relief grooves lie essentially in the inflow region of the steam turbine and locally reduce the cross section and the polar moment of resistance.

Um dennoch den gewünschten Anforderungen an die Dampfturbine gerecht zu werden, was die Dampftemperatur, Turbinenleistung, Rotor und die flexible Fahrweise angeht, muss der Rotor weiter optimiert werden.In order nevertheless to meet the desired requirements of the steam turbine, as far as the steam temperature, turbine power, rotor and the flexible driving style are concerned, the rotor must be further optimized.

Bekannte Rotoren für Dampfturbinen werden mit Entlastungsnuten gefertigt, die einen rotationssymmetrischen und kreisförmigen Querschnitt im Einströmbereich aufweisen. Für diese Gestaltung der Entlastungsnut im Allgemeinen und die Wahl des minimalen Rotor-Durchmessers im Speziellen wird ein Kompromiss eingegangen, der den weiter oben aufgeführten widersprüchlichen Anforderungen gerecht wird.Known rotors for steam turbines are manufactured with relief grooves, which have a rotationally symmetrical and circular cross-section in the inflow region. For this design of the relief groove in general and the choice of the minimum rotor diameter in particular, a compromise is made which meets the contradictory requirements listed above.

EP2264281A2 offenbart Antiwirbelausnehmungen für einen Gasturbinenmotorverdichter. EP2264281A2 discloses anti-vortex recesses for a gas turbine engine compressor.

Wünschenswert wäre es einen Rotor zu haben, der den vorgenannten Entwicklungstendenzen gerecht wird. Es ist daher Aufgabe der Erfindung, einen Rotor anzugeben, der den vorgenannten Entwicklungstendenzen gerecht wird.It would be desirable to have a rotor that meets the aforementioned development trends. It is therefore an object of the invention to provide a rotor that meets the above development trends.

Die Aufgabe wird gelöst durch einen Rotor für eine Strömungsmaschine mit einem Entlastungsbereich, wobei mehrere in Umfangsrichtung angeordnete Ausnehmungen angeordnet sind.The object is achieved by a rotor for a turbomachine with a discharge region, wherein a plurality of recesses arranged in the circumferential direction are arranged.

Die Erfindung geht weg von der bisherigen Gestaltung, bei der eine Entlastungsnut mit rotationssymmetrischen und kreisförmigen Querschnitten im Einströmbereich vorgesehen ist. Vielmehr wird der Rotor erfindungsgemäß im Entlastungsbereich mit Ausnehmungen versehen, die in Umfangsrichtung angeordnet sind. Diese Ausnehmungen sind in Umfangsrichtung um eine Rotationsachse angeordnet und weisen ein nicht-achsensymmetrisches Querschnittsprofil auf. Das Querschnittsprofil weist unter anderem Kerben und Flanken auf, die ähnlich einem Gewinde wendelartig in einer Schraubenlinie verlaufen.The invention proceeds from the previous design, in which a relief groove is provided with rotationally symmetrical and circular cross sections in the inflow region. Rather, the rotor is provided according to the invention in the relief region with recesses which are arranged in the circumferential direction. These recesses are arranged in the circumferential direction about an axis of rotation and have a non-axisymmetric cross-sectional profile. The cross-sectional profile has including notches and flanks, which run like a thread helically in a helical line.

Durch diese Ausgestaltung des Entlastungsbereichs des Rotors ist zunächst gewährleistet, dass Torsionsmomente geeignet übertragen werden, da der Durchmesser des Rotors im Wesentlichen unverändert ist. Des Weiteren können dennoch thermisch induzierte Spannungen im Entlastungsbereich abgebaut werden, da die Ausnehmungen die thermisch induzierten Spannungen ableiten.This embodiment of the relief region of the rotor initially ensures that torsional moments are suitably transmitted, since the diameter of the rotor is substantially unchanged. Furthermore, thermally induced stresses in the discharge region can still be reduced, since the recesses derive the thermally induced voltages.

In den Unteransprüchen sind vorteilhafte Weiterbildungen angegeben.In the dependent claims advantageous developments are given.

So ist es vorteilhaft, dass die Ausnehmungen in äquidistanten Abständen zueinander angeordnet sind. Durch eine äquidistante Verteilung der Ausnehmungen in Umfangsrichtung können Unwuchten und unerwünschte störende Rotordynamiken verhindert werden.Thus, it is advantageous that the recesses are arranged at equidistant intervals from each other. By an equidistant distribution of the recesses in the circumferential direction imbalances and unwanted disturbing rotor dynamics can be prevented.

Durch eine vorteilhafte Weiterbildung, bei der die Ausnehmungen identisch zueinander ausgeführt sind, kann weiterhin die Rotordynamik positiv beeinflusst werden. Unwuchten können dadurch wirksam vermieden werden.By an advantageous development in which the recesses are made identical to each other, the rotor dynamics can continue to be positively influenced. Imbalance can be effectively avoided.

Die Ausnehmungen sind im Wesentlichen länglich ausgebildet. In einer weiteren vorteilhaften Weiterbildung sind die Ausnehmungen unter einem Winkel α, der zwischen 10° und 80°, vorzugsweise bei 45° liegt, zur Rotationsachse geneigt. Durch diese Neigung wird eine gewinde-wendelartige Gestaltung möglich, die ähnlich wie eine Schraubenlinie verläuft.The recesses are formed substantially elongated. In a further advantageous development, the recesses are inclined at an angle α, which is between 10 ° and 80 °, preferably at 45 °, to the axis of rotation. By this inclination, a thread-helical design is possible, which runs similar to a helical line.

In einer vorteilhaften Weiterbildung weisen die Ausnehmungen eine Tiefe auf, wobei diese Tiefe in axialer Richtung zunächst zunimmt und anschließend abnimmt. Durch diese Maßnahme ist eine in Umfangsrichtung homogene Entlastungswirkung trotz der nicht-achsensymmetrischen Querschnittsfläche erzielbar.In an advantageous development, the recesses have a depth, wherein this depth first increases in the axial direction and then decreases. By this measure, a homogeneous in the circumferential direction relief effect despite the non-axisymmetric cross-sectional area can be achieved.

Idealerweise wird in einer vorteilhaften Weiterbildung die Ausnehmung einen Anfang- und einen Endbereich aufweisen, wobei die Ausnehmung im Anfangs- und Endbereich bündig mit der Rotoroberfläche abschließt. Durch solch eine Ausgestaltung sind Kerbeinflüsse nahezu minimiert, was sich positiv auf die Rotordynamik und auf die mechanischen Eigenschaften des Rotors auswirkt.Ideally, in an advantageous embodiment, the recess has a beginning and an end region, wherein the recess terminates flush with the rotor surface in the beginning and end regions. By such an embodiment, notch influences are almost minimized, which has a positive effect on the rotor dynamics and on the mechanical properties of the rotor.

Ein Ausführungsbeispiel der Erfindung wird, ohne hierauf beschränkt zu sein, anhand der Figuren 1 bis 5 näher erläutert. Dabei zeigen:

Figur 1
eine Querschnittsansicht einer Dampfturbine,
Figur 2
eine Querschnittsansicht eines Teils eines Rotors gemäß dem Stand der Technik,
Figur 3
eine Draufsicht auf einen Teil eines erfindungsgemäßen Rotors,
Figur 4
eine Querschnittsansicht eines erfindungsgemäßen Rotors,
Figur 5
eine Querschnittsansicht eines erfindungsgemäßen Rotors.
An embodiment of the invention is, but is not limited to, based on the FIGS. 1 to 5 explained in more detail. Showing:
FIG. 1
a cross-sectional view of a steam turbine,
FIG. 2
a cross-sectional view of a part of a rotor according to the prior art,
FIG. 3
a plan view of a part of a rotor according to the invention,
FIG. 4
a cross-sectional view of a rotor according to the invention,
FIG. 5
a cross-sectional view of a rotor according to the invention.

Komponenten mit denselben Bezugszeichen haben im Wesentlichen die gleiche Funktionsweise.Components with the same reference numerals have substantially the same operation.

Die Figur 1 zeigt einen Querschnitt durch einen Teil einer Dampfturbine 1. Die Dampfturbine 1 weist im Wesentlichen ein Außengehäuse 2 und ein innerhalb des Außengehäuses 2 angeordnetes Innengehäuse 3 auf. Innerhalb des Innengehäuses 3 ist ein um eine Rotationsachse 4 angeordneter Rotor 5 drehbar gelagert. Der Rotor 5 weist in Richtung der Rotationsachse nacheinander angeordnete Laufschaufelreihen 6 auf, wobei lediglich die ersten beiden Reihen mit dem Bezugszeichen 6 versehen sind.The FIG. 1 shows a cross section through a part of a steam turbine 1. The steam turbine 1 has essentially an outer casing 2 and an inner casing 3 arranged inside the outer casing 2. Within the inner housing 3, a rotor 5 arranged around a rotation axis 4 is rotatably mounted. The rotor 5 has in the direction of the axis of rotation successively arranged blade rows 6, wherein only the first two rows are provided with the reference numeral 6.

Zwischen den Laufschaufelreihen 6 sind im Innengehäuse 3 angeordnete Leitschaufeln 7 angeordnet, wobei in der Figur 1 lediglich zwei Leitschaufelreihen 7 mit dem Bezugszeichen 7 gekennzeichnet sind.Between the blade rows 6 3 arranged vanes 7 are arranged in the inner housing, wherein in the FIG. 1 only two vane rows 7 are denoted by the reference numeral 7.

Im Betrieb strömt ein Dampf mit hohen Temperaturen und hohen Drücken in der Regel in einen Einströmbereich 8 in die Dampfturbine und entspannt sich im Strömungskanal 9 in Richtung der Rotationsachse 4 und durchströmt dabei abwechselnd die Laufschaufelreihen 6 und die Leitschaufelreihen 7. Die Temperatur des Dampfes sinkt, wobei sich der Druck verringert. Der Rotor wird hierbei in Drehung versetzt und rotiert im Betrieb in der Regel konstant mit 3000 U/min bzw. 3600 U/min. Die hohen Dampftemperaturen und -Drücke sowie die vergleichsweise hohe Rotationsfrequenz führen zu hohen thermischen und mechanischen Belastungen. Besonders im Einströmbereich 8 sind die Anforderungen an den Rotor 5 besonders hoch.In operation, a vapor with high temperatures and high pressures usually flows into an inflow region 8 in the steam turbine and relaxes in the flow channel 9 in the direction of the axis of rotation 4 and flows alternately through the blade rows 6 and the guide blade rows 7. The temperature of the vapor decreases, whereby the pressure decreases. The rotor is rotated in this case and rotates in operation generally constant at 3000 rev / min or 3600 rev / min. The high steam temperatures and pressures as well as the comparatively high rotation frequency lead to high thermal and mechanical loads. Especially in the inflow region 8, the requirements for the rotor 5 are particularly high.

In der Figur 2 ist eine Darstellung eines Rotors gemäß dem Stand der Technik zu sehen. Im Wesentlichen ist der Einströmbereich 8 mit einer Entlastungsnut 10 versehen. Diese Entlastungsnut 10 ist gemäß dem Stand der Technik im Wesentlichen rotationssymmetrisch bzw. kreisförmig ausgebildet. Das bedeutet, dass im Querschnitt gesehen die Entlastungsnutlinie 11 einen Kreisausschnitt darstellt. Allerdings ist eine kreisförmige Entlastungsnut 10 aus Festigkeitsgründen nicht ideal, da der Innendurchmesser 12 verringert wird, was zu unerwünschten Festigkeitsnachteilen führen könnte. Des Weiteren ist in Rotationsachsenrichtung eine Fußnut 13 angeordnet. In diese Fußnut 13, die in der Figur 2 als Hammerkopf-Fußnut ausgebildet ist, wird eine nicht näher dargestellte Laufschaufel angeordnet.In the FIG. 2 is an illustration of a rotor according to the prior art. In essence, the inflow region 8 is provided with a relief groove 10. This relief groove 10 is formed according to the prior art substantially rotationally symmetrical or circular. This means that seen in cross section, the relief groove 11 is a circular section. However, a circular relief groove 10 is not ideal for strength reasons, since the inner diameter 12 is reduced, which could lead to undesirable strength disadvantages. Furthermore, a foot groove 13 is arranged in the rotation axis direction. In this Fußnut 13, in the FIG. 2 is designed as a hammerhead Fußnut, a blade not shown is arranged.

In der Figur 3 ist eine erfindungsgemäße Ausgestaltung der Entlastungsnut 10 dargestellt. Anstatt die Entlastungsnut 10 wie in Figur 2 dargestellt, mit einer rotationssymmetrischen bzw. kreisförmigen Oberfläche auszubilden, wird die Entlastungsnutoberfläche 14 im Wesentlichen parallel zur Rotationsachse 4 ausgebildet. Erfindungsgemäß werden im Entlastungsbereich 10 Ausnehmungen 15 angeordnet, die in Umfangsrichtung 16 angeordnet sind. Diese Ausnehmungen 15 können in die Entlastungsnutoberfläche 14 eingefräst oder durch andere Bearbeitungsmethoden eingearbeitet werden. Die Ausnehmungen 15 weisen einen Abstand 17 zueinander hin, wobei dieser Abstand 17 von Ausnehmung 15 zu Ausnehmung 15 gleichbleibend ist. Daher sind die Ausnehmungen 15 in äquidistanten Abständen zueinander angeordnet.In the FIG. 3 an inventive embodiment of the relief groove 10 is shown. Instead of the relief groove 10th as in FIG. 2 shown formed with a rotationally symmetric or circular surface, the relief groove surface 14 is formed substantially parallel to the axis of rotation 4. According to the invention 10 recesses 15 are arranged in the relief region, which are arranged in the circumferential direction 16. These recesses 15 can be milled into the relief groove surface 14 or incorporated by other processing methods. The recesses 15 have a distance 17 to each other, this distance 17 from recess 15 to recess 15 is constant. Therefore, the recesses 15 are arranged at equidistant intervals.

Die Ausnehmungen 15 weisen eine Breite und eine Länge auf, wobei die Länge größer ist als die Breite.The recesses 15 have a width and a length, wherein the length is greater than the width.

Die Ausnehmungen 15 sind hierbei in Umfangsrichtung 16 im Wesentlichen identisch zueinander ausgebildet, um unerwünschte Rotordynamiken zu vermeiden. Die Ausnehmungen 15 sind unter einem Winkel α, der zwischen 10° und 80°, vorzugsweise bei 45° liegt, zur Rotationsachse 4 geneigt. Weitere vorteilhafte Winkelbereiche sind 10° bis 70°, 20° bis 60°, 30° bis 50° sowie 10° bis 70°, 10° bis 60°, 10° bis 50° sowie 20° bis 80°, 30° bis 80°, 40° bis 80°, 50° bis 80°. Durch diese Neigung der Ausnehmungen 15 ist der Verlauf der Ausnehmungen 15 ähnlich einem Gewinde, das bedeutet, dass die Ausnehmungen 15 wendelartig in einer Schraubenlinie verlaufen. Die Ausnehmungen 15 sind daher nicht-achsensymmetrisch ausgebildet. Der Winkel α wird zwischen einer Parallelen zur Rotationsachse 4 und der länglichen Ausbildung der Ausnehmung 15 ermittelt.The recesses 15 are in this case formed in the circumferential direction 16 is substantially identical to each other to avoid unwanted rotor dynamics. The recesses 15 are inclined at an angle α, which is between 10 ° and 80 °, preferably at 45 °, to the axis of rotation 4. Further advantageous angular ranges are 10 ° to 70 °, 20 ° to 60 °, 30 ° to 50 ° and 10 ° to 70 °, 10 ° to 60 °, 10 ° to 50 ° and 20 ° to 80 °, 30 ° to 80 °, 40 ° to 80 °, 50 ° to 80 °. By this inclination of the recesses 15, the course of the recesses 15 is similar to a thread, which means that the recesses 15 extend helically in a helix. The recesses 15 are therefore formed non-axisymmetric. The angle α is determined between a parallel to the axis of rotation 4 and the elongated configuration of the recess 15.

Die Figur 4 zeigt eine Querschnittsansicht entlang der Linie A-A aus der Figur 3. Diese Ansicht stellt somit einen Blick in Richtung der Rotationsachse 4 dar. Die Ausnehmungen 15 sind hierbei in äquidistanten Abständen 17 in Umfangsrichtung 16 verteilt. Die Ausnehmungen 15 weisen einen Kernradius 18 auf, der vom Boden 19 der Ausnehmung zur Rotationsachse 4 hin ermittelt wird. Des Weiteren wird die Ausnehmung 15 durch den Außenradius 20, der durch die Entlastungsnutoberfläche 14 und der Rotationsachse 4 ermittelt wird. Die Ausnehmungen 15 sind im Querschnitt gesehen rechteckig bzw. trapezförmig ausgebildet, wobei an den Übergängen 21 aus Festigkeitsgründen keine Ecken ausgebildet sein sollten. In den Übergängen 21 ist der Boden 19 und eine Seitenwand 22 durch fließende Übergänge gekennzeichnet. Das bedeutet, dass die Übergänge durch einen Radius, der nicht näher eingezeichnet ist, charakterisiert werden. Zumindest sollten störende Kerbwirkungen in diesem Übergang 21 vermieden werden.The FIG. 4 shows a cross-sectional view along the line AA from the FIG. 3 , This view thus represents a view in the direction of the axis of rotation 4. The recesses 15 are in this case distributed at equidistant intervals 17 in the circumferential direction 16. The recesses 15 have a core radius 18, which from the bottom 19 of the recess to the axis of rotation 4 out is determined. Furthermore, the recess 15 is determined by the outer radius 20, which is determined by the relief groove surface 14 and the axis of rotation 4. The recesses 15 are seen in cross-section rectangular or trapezoidal, wherein at the transitions 21 for reasons of strength no corners should be formed. In the transitions 21, the bottom 19 and a side wall 22 are characterized by flowing transitions. This means that the transitions are characterized by a radius that is not shown in detail. At least disturbing notch effects should be avoided in this transition 21.

Die Figur 5 zeigt eine Seitenansicht des Rotors 5. Die Ausnehmungen 15 sind hierbei in Rotationsachsenrichtung hin derart ausgebildet, dass der Kernradius 18 in Rotationsachsenrichtung hin variiert. Insbesondere ist der Kernradius 18 in einem Anfangsbereich 23 und einem Endbereich 24 bündig mit dem Außenradius 20. Das bedeutet, dass die Ausnehmung 15 im Anfangs- 23 und Endbereich 24 bündig mit der Entlastungsnutoberfläche 14 abschließt. Des Weiteren weist die Ausnehmung 15 einen stetigen Verlauf in ihrer Längsrichtung. Die Figur 5 zeigt einen Schnitt durch eine Entlastungsnut 15 auf. Das bedeutet, dass der Schnitt gemäß Figur 5 nicht parallel zur Rotationsachse 4, sondern im Wesentlichen parallel zu einer Seitenwand 22 ausgeführt ist. Der Kernradius 18 ist derart gewählt, dass der Verlauf des Bodens 19 der Ausnehmung 15 rotationssymmetrisch oder kreisförmig ausgebildet ist. Der Einströmbereich (8) ist zum Beströmen mit Frischdampf ausgebildet.The FIG. 5 shows a side view of the rotor 5. The recesses 15 are in this case formed in the direction of rotation axis out such that the core radius 18 varies in the direction of rotation axis. In particular, the core radius 18 in an initial region 23 and an end region 24 is flush with the outer radius 20. This means that the recess 15 in the initial 23 and end region 24 is flush with the relief groove surface 14. Furthermore, the recess 15 has a continuous course in its longitudinal direction. The FIG. 5 shows a section through a relief groove 15. This means that the cut according to FIG. 5 not parallel to the axis of rotation 4, but substantially parallel to a side wall 22 is executed. The core radius 18 is selected such that the course of the bottom 19 of the recess 15 is rotationally symmetrical or circular. The inflow region (8) is designed to flow with live steam.

Claims (9)

  1. Rotor (5) for a turbomachine (1) with a stress-relieving region,
    wherein the rotor (5) is designed such that it can rotate about an axis of rotation (4),
    characterized by
    multiple recesses (15), which are arranged in the stress-relieving region in the circumferential direction (16) on the surface of the rotor (5), for relieving thermally induced stresses in the rotor (5),
    wherein the recesses (15) are inclined at an angle α of between 10° and 80°,
    preferably 45°,
    to the axis of rotation (4).
  2. Rotor (5) according to Claim 1,
    wherein the recesses (15) are arranged with equal separation (17) with respect to one another.
  3. Rotor (5) according to Claim 1 or 2,
    wherein the recesses (15) are identical to one another.
  4. Rotor (5) according to one of the preceding claims, wherein the recesses (15) have a width and a length,
    wherein the length is greater than the width.
  5. Rotor (5) according to one of the preceding claims,
    wherein the recess (15) first increases in the axial direction and then decreases.
  6. Rotor (5) according to Claim 5,
    wherein the recess (15) has a starting region (23) and an end region (24) and the recess (15) terminates, in the starting region (23) and the end region (24), flush with the stress-relieving groove surface (14).
  7. Rotor (5) according to one of the preceding claims,
    wherein the recess (15) has a constant profile in its longitudinal direction.
  8. Rotor (5) according to one of the preceding claims,
    wherein the recess (15), as seen in cross section, is essentially rectangular or trapezoidal.
  9. Rotor (5) according to one of the preceding claims,
    wherein the stress-relieving region is arranged in the inflow region (8) and the inflow region (8) is designed to accommodate a flow of fresh steam.
EP11751877.9A 2010-09-08 2011-08-29 Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles Not-in-force EP2614220B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11751877.9A EP2614220B1 (en) 2010-09-08 2011-08-29 Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10175762A EP2428642A1 (en) 2010-09-08 2010-09-08 Rotor for a steam turbine with circumferential recesses inclined in respect to the rotor main axis
PCT/EP2011/064824 WO2012031931A1 (en) 2010-09-08 2011-08-29 Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles
EP11751877.9A EP2614220B1 (en) 2010-09-08 2011-08-29 Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles

Publications (2)

Publication Number Publication Date
EP2614220A1 EP2614220A1 (en) 2013-07-17
EP2614220B1 true EP2614220B1 (en) 2015-07-15

Family

ID=43530969

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10175762A Withdrawn EP2428642A1 (en) 2010-09-08 2010-09-08 Rotor for a steam turbine with circumferential recesses inclined in respect to the rotor main axis
EP11751877.9A Not-in-force EP2614220B1 (en) 2010-09-08 2011-08-29 Rotor for a steam turbine, having axially asymmetrical cross-sectional profiles

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10175762A Withdrawn EP2428642A1 (en) 2010-09-08 2010-09-08 Rotor for a steam turbine with circumferential recesses inclined in respect to the rotor main axis

Country Status (3)

Country Link
EP (2) EP2428642A1 (en)
CN (1) CN103097665B (en)
WO (1) WO2012031931A1 (en)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH437923A (en) * 1966-04-14 1967-06-15 Albert Ufenast Friedrich Rotary piston engine
EP0353447A1 (en) * 1988-07-29 1990-02-07 Westinghouse Electric Corporation Side-entry grooves for mounting turbine blades
US5492447A (en) * 1994-10-06 1996-02-20 General Electric Company Laser shock peened rotor components for turbomachinery
US5641275A (en) * 1995-01-26 1997-06-24 Ansimag Inc. Grooved shaft for a magnetic-drive centrifugal pump
GB9825504D0 (en) * 1998-11-21 1999-01-13 Heap Roland G An engine
KR100697471B1 (en) * 1999-05-14 2007-03-20 제너럴 일렉트릭 캄파니 Retention sleeve for a thermal medium carrying tube in a gas turbine
EP1614857A1 (en) * 2004-07-05 2006-01-11 Siemens Aktiengesellschaft Turbomachine with a rotor comprising at least one drilled disc
US8425194B2 (en) * 2007-07-19 2013-04-23 General Electric Company Clamped plate seal
US8453463B2 (en) * 2009-05-27 2013-06-04 Pratt & Whitney Canada Corp. Anti-vortex device for a gas turbine engine compressor

Also Published As

Publication number Publication date
EP2614220A1 (en) 2013-07-17
CN103097665A (en) 2013-05-08
EP2428642A1 (en) 2012-03-14
CN103097665B (en) 2015-04-01
WO2012031931A1 (en) 2012-03-15

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