EP1614857A1 - Turbomachine with a rotor comprising at least one drilled disc - Google Patents

Turbomachine with a rotor comprising at least one drilled disc Download PDF

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Publication number
EP1614857A1
EP1614857A1 EP04015806A EP04015806A EP1614857A1 EP 1614857 A1 EP1614857 A1 EP 1614857A1 EP 04015806 A EP04015806 A EP 04015806A EP 04015806 A EP04015806 A EP 04015806A EP 1614857 A1 EP1614857 A1 EP 1614857A1
Authority
EP
European Patent Office
Prior art keywords
rotor
bore
turbomachine
rotor disk
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.)
Withdrawn
Application number
EP04015806A
Other languages
German (de)
French (fr)
Inventor
Harald Hoell
Reimar Dr. Schaal
Werner Dr. Setz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP04015806A priority Critical patent/EP1614857A1/en
Priority to PCT/EP2005/052698 priority patent/WO2006003074A1/en
Priority to EP05760921A priority patent/EP1763622A1/en
Priority to JP2007518576A priority patent/JP2008505270A/en
Priority to CNA200580029209XA priority patent/CN101040101A/en
Priority to US11/631,768 priority patent/US7819632B2/en
Publication of EP1614857A1 publication Critical patent/EP1614857A1/en
Withdrawn legal-status Critical Current

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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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the invention relates to a turbomachine having a rotor rotatably mounted about a rotation axis, which rotor has at least one rotor disk, in which at least one axially extending bore is arranged. Furthermore, the invention relates to a rotor for a turbomachine and a rotor disk having at least one axially extending bore through the rotor disk.
  • Stationary gas turbines and aircraft turbines with rotors composed of a plurality of rotor disks are generally known.
  • One central or several decentralized tie rods clamp the rotor disks together.
  • the rotor disks have at least one cylindrical bore, through which the tie rods extend.
  • Each rotor disk carries on its outer periphery in a ring arranged blades, which are flowed around for compressing a flow medium or for receiving rotational energy from a flow medium thereof.
  • the blades attached to the rotor disc cause enormous centrifugal forces during operation, so that each rotor disk is exposed to great loads.
  • the rotor disks must be faultless.
  • suitable test methods are known, by means of which the rotor disk are examined before their first use as well as in repeat tests for cracks and defects in order to ensure a minimum service life and thus safe operation of the turbomachine.
  • the object of the invention is therefore to provide a rotor disk for the rotor of a turbomachine, a rotor for a turbomachine and a turbomachine whose life is extended by design measures.
  • the bore of the rotor disk extends in the axial direction at least partially crowned with a larger diameter in the middle region.
  • the solution is based on the inventive idea that increase the Mises's comparative stresses in the bore region by the bore in the axial direction at least partially spherical.
  • the increase in the comparative stress is due to the influence of the axial and tangential stress component by the spherical geometry of the bore, i. their convex cross-sectional shape. Due to the increased reference stresses, centrifuging in the hub area leads to greater plasticization, as a result of which the amount of residual compressive stress increases due to geometry, without an increase in the spin speed. Higher compressive residual stresses mean a delay in crack propagation and reduced risk of brittle fracture in later operation.
  • the turbomachine can be designed as a turbine, as a compressor, as a gas turbine or as a steam turbine. It is independent whether they are single-stage or multi-stage formed or flowed through axially or axially.
  • the bore is central, ie in the center of the rotor disk, and / or decentralized, ie spaced from the center of the rotor disk arranged.
  • the effects achieved by the crowned embodiment are independent of whether the hole is provided centrally or decentrally.
  • the maximum inner diameter of the spherical bore is arranged in the axial direction between the end faces of the rotor disk.
  • Gas turbines and their operations are generally known.
  • 1 shows a turbomachine 1 designed as a turbomachine 1 with a rotatably mounted about a rotation axis rotor 5.
  • a turbomachine 1 designed as a turbomachine 1 with a rotatably mounted about a rotation axis rotor 5.
  • a compressor 7 a combustion chamber 9 with burners 11.
  • the combustion chamber 9, the turbine unit 13 is connected downstream.
  • the rotor 5 has a plurality of adjoining rotor disks 20, in each of which a central bore 16 is provided, through which a tie rod 21 extends.
  • Fig. 2 shows the side view of a rotor disk 14 according to the invention with a centrally disposed bore 15, which extends in the axial direction partially spherical, that is curved outwardly.
  • FIG. 3 shows a section through the rotor disk 14 according to the invention as shown in FIG. 2.
  • the bore 15 initially extends in the axial direction of the rotor 5 in a circular cylindrical manner, then merges into a crowned section and ends with a circular cylindrical section.
  • the diameter 17 of the bore 15 is maximum in the spherical portion in the middle between the two end faces 19 of the rotor disk 14 and decreases in the direction of the end faces 19 and the circular cylindrical sections on both sides evenly.
  • the rotor disk 14 has a convex recess.
  • the material of the rotor disc, which surrounds the recess, thus has a concave contour.
  • FIG. 4 shows a cylindrical bore 16 known from the prior art through a rotor disk 20.
  • FIG. 5 shows the profile of stresses ⁇ of a rotor disk 20 of the prior art in a radius-voltage diagram.
  • the characteristic curve 22 shown in a circle-dash line type shows the course of the tangential stresses at a distance x from the surface of the bore 16 in the radial direction.
  • the curve 24 shown in full line shows the Mises comparison voltages. Both stresses decrease with increasing distance x from the surface of the cylindrical bore 16 of the rotor disk 20. After spinning the rotor disk 20, this pressure compressive stresses, whose course is shown in dashed line type by the characteristic curve 26. The amount of compressive residual stresses decreases with increasing distance x.
  • Fig. 6 shows the rotor disk 14 according to the invention with a along the axial direction completely convex bore 15, the shape is also referred to as spherical.
  • FIG. 7 shows the profile of stresses ⁇ of a rotor disk 14 according to the invention in a radius-voltage diagram.
  • the tangential stresses 28 of the rotor disk 14 according to the invention are shown in a circle-dash line type and the Mises comparison voltages 30 in solid line. Both stresses decrease with increasing distance x from the surface of the spherical bore 15 of the rotor disk 14. After spinning the rotor disk 14, this has a compressive residual stress 32 shown in solid line, the amount of which decreases with increasing distance x.
  • FIG. 8 shows the characteristic curves 22, 24, 26, 28, 30, 32 of the two diagrams FIG. 5 and FIG. 7 in comparison.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The turbomachine has a rotor mounted to rotate around a rotational axis (3) and which has at least one rotor disc (14) with an axially extending bore (15) which in the axial direction is at least partially crowned with the large diameter in the center section. The turbomachine may be a turbine, a compressor, a gas turbine, or a steam turbine. Independent claims are also included for the following: (A) a rotor for a turbomachine; (B) a rotor disc for the rotor of a turbomachine; and (C) a device in which a bore is provided centrally and/or de-centrally.

Description

Die Erfindung betrifft eine Strömungsmaschine mit einem um eine Drehachse drehbar gelagerten Rotor, der zumindest eine Rotorscheibe aufweist, in der zumindest eine sich axial erstreckende Bohrung angeordnet ist. Ferner betrifft die Erfindung einen Rotor für eine Strömungsmaschine und eine Rotorscheibe mit zumindest einer sich durch die Rotorscheibe axial erstreckenden Bohrung.The invention relates to a turbomachine having a rotor rotatably mounted about a rotation axis, which rotor has at least one rotor disk, in which at least one axially extending bore is arranged. Furthermore, the invention relates to a rotor for a turbomachine and a rotor disk having at least one axially extending bore through the rotor disk.

Stationäre Gasturbinen und Flugzeugturbinen mit aus mehreren Rotorscheiben zusammengesetzten Rotoren sind allgemein bekannt. Ein zentraler oder mehrere dezentrale Zuganker verspannen die Rotorscheiben miteinander. Dazu weisen die Rotorscheiben zumindest eine zylindrische Bohrung auf, durch die sich die Zuganker erstrecken.Stationary gas turbines and aircraft turbines with rotors composed of a plurality of rotor disks are generally known. One central or several decentralized tie rods clamp the rotor disks together. For this purpose, the rotor disks have at least one cylindrical bore, through which the tie rods extend.

Jede Rotorscheibe trägt an ihrem Außenumfang in einem Kranz angeordnete Laufschaufeln, die zum Verdichten eines Strömungsmediums oder zur Aufnahme von Rotationsenergie aus einem Strömungsmedium von diesem umströmbar sind. Die an der Rotorscheibe befestigten Laufschaufeln rufen beim Betrieb enorme Fliehkräfte hervor, so dass jede Rotorscheibe großen Belastungen ausgesetzt ist.Each rotor disk carries on its outer periphery in a ring arranged blades, which are flowed around for compressing a flow medium or for receiving rotational energy from a flow medium thereof. The blades attached to the rotor disc cause enormous centrifugal forces during operation, so that each rotor disk is exposed to great loads.

Um diesen Belastungen widerstehen zu können, müssen die Rotorscheiben fehlerfrei sein. Hierzu sind geeignete Prüfverfahren bekannt, mittels derer die Rotorscheibe vor deren ersten Verwendung als auch bei Wiederholungsprüfungen auf Risse und Fehlstellen untersucht werden, um eine Mindestlebensdauer und somit einen sicheren Betrieb der Strömungsmaschine zu gewährleisten.To be able to withstand these loads, the rotor disks must be faultless. For this purpose, suitable test methods are known, by means of which the rotor disk are examined before their first use as well as in repeat tests for cracks and defects in order to ensure a minimum service life and thus safe operation of the turbomachine.

Durch eine zunehmende Scheibengröße von gebohrten Rotorscheiben oder bei Verwendung grobkörniger Werkstoffe ist die Fehlererkennbarkeit von Rissen bei den Prüfungen in zunehmendem Maße eingeschränkt.Increased disk size of drilled rotor disks or use of coarse-grained materials increasingly limits the fault detectability of cracks in the tests.

Eine Möglichkeit zur Sicherstellung der geforderten Lebensdauer ist das gezielte Einbringen von Druckeigenspannungen in das Material der Rotorscheiben, die das Wachstum von Fehlstellen, d.h. Rissen, im späteren Betrieb verzögern. Hierzu wird während der Herstellung der gebohrten Rotorscheibe diese gezielt überlastet, d.h. sie wird bei einer Schleuderdrehzahl geschleudert, die höher als die Nenndrehzahl des Rotors ist. Dies ruft im Bereich der Bohrung eine plastische Verformung hervor, die zu den Druckeigenspannungen führt. Die Höhe der Druckeigenspannungen im Scheibenmaterial ist jedoch durch die maximale Schleuderdrehzahl des Schleuderprüfstands und durch die Temperatur beim Schleudern begrenzt, so dass weniger Druckeigenspannungen erzeugt werden können als gewünscht.One way to ensure the required service life is the targeted introduction of compressive residual stresses in the material of the rotor disks, which prevents the growth of defects, i. Cracks, delay in later operation. For this purpose, during the manufacture of the drilled rotor disk, it is purposefully overloaded, i. it is spun at a spin speed higher than the rated speed of the rotor. This causes a plastic deformation in the area of the bore, which leads to the residual compressive stresses. However, the amount of residual compressive stress in the disc material is limited by the maximum spin speed of the spin test stand and by the spinning temperature, so that less compressive residual stresses can be generated than desired.

Die in der Rotorscheibe nicht erkannten bzw. tolerierten Fehlstellen können aufgrund der hohen Belastungen und lediglich begrenzt großen Druckeigenspannungen weiterhin Risse erzeugen und wachsen lassen, welche die Lebensdauer der Rotorscheibe und somit der Strömungsmaschine verringern.The imperfections not recognized or tolerated in the rotor disk can, due to the high loads and only limited compressive residual stresses, continue to generate and grow cracks which reduce the service life of the rotor disk and thus of the turbomachine.

Die Aufgabe der Erfindung ist es daher, eine Rotorscheibe für den Rotor einer Strömungsmaschine, einen Rotor für eine Strömungsmaschine und eine Strömungsmaschine anzugeben, deren Lebensdauer durch konstruktive Maßnahmen verlängert ist.The object of the invention is therefore to provide a rotor disk for the rotor of a turbomachine, a rotor for a turbomachine and a turbomachine whose life is extended by design measures.

Die auf die Strömungsmaschine gerichtete Aufgabe wird durch die Merkmale des Anspruchs 1, die auf den Rotor gerichtete Aufgabe durch die Merkmale des Anspruchs 3 und die auf die Rotorscheibe gerichtet Aufgabe durch die Merkmale des Anspruchs 4 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angeben.The problem addressed to the turbomachine is solved by the features of claim 1, the rotor-directed object by the features of claim 3 and the problem addressed to the rotor disc by the features of claim 4. Advantageous embodiments are specified in the subclaims.

Erfindungsgemäß ist vorgesehen, dass die Bohrung der Rotorscheibe in Axialrichtung zumindest teilweise ballig mit im mittleren Bereich größerem Durchmesser verläuft.According to the invention, it is provided that the bore of the rotor disk extends in the axial direction at least partially crowned with a larger diameter in the middle region.

Der Lösung liegt die erfinderische Idee zu Grunde, dass durch die in Axialrichtung zumindest teilweise ballig verlaufende Bohrung sich die Mises'schen Vergleichsspannungen im Bohrungsbereich erhöhen. Die Erhöhung der Vergleichsspannung beruht auf der Beeinflussung der axialen und tangentialen Spannungskomponente durch die ballige Geometrie der Bohrung, d.h. deren konvexe Querschnittsform. Durch die erhöhten Vergleichsspannungen kommt es beim Schleudern im Nabenbereich zu einer stärkeren Plastifizierung, wodurch der Betrag der Druckeigenspannungen geometriebedingt ohne eine Erhöhung der Schleuderdrehzahl zunimmt. Höhere Druckeigenspannungen bedeuten eine Verzögerung des Rissfortschritts und reduzierte Sprödbruchgefahr im späteren Betrieb.The solution is based on the inventive idea that increase the Mises's comparative stresses in the bore region by the bore in the axial direction at least partially spherical. The increase in the comparative stress is due to the influence of the axial and tangential stress component by the spherical geometry of the bore, i. their convex cross-sectional shape. Due to the increased reference stresses, centrifuging in the hub area leads to greater plasticization, as a result of which the amount of residual compressive stress increases due to geometry, without an increase in the spin speed. Higher compressive residual stresses mean a delay in crack propagation and reduced risk of brittle fracture in later operation.

Durch die in Axialrichtung ballig verlaufende Bohrung nehmen darüber hinaus die Tangentialspannungen ab. Weil diese beim Betrieb der Strömungsmaschine ebenfalls Rissentstehung und Risswachstum begünstigen, wird durch den balligen Verlauf dem entgegengewirkt und das Risswachstum maßgeblich verzögert.In addition, the tangential stresses decrease as a result of the bore extending in the axial direction. Because these also favor the formation of cracks and crack growth during operation of the turbomachine, this is counteracted by the convex course and the crack growth is significantly delayed.

Zweckmäßigerweise kann die Strömungsmaschine als Turbine, als Verdichter, als Gasturbine oder als Dampfturbine ausgebildet sein. Dabei ist es unabhängig, ob diese einstufig oder mehrstufig ausgebildet bzw. axial oder radial durchströmt sind.Expediently, the turbomachine can be designed as a turbine, as a compressor, as a gas turbine or as a steam turbine. It is independent whether they are single-stage or multi-stage formed or flowed through axially or axially.

In einer vorteilhaften Ausgestaltung ist die Bohrung zentral, d.h. im Mittelpunkt der Rotorscheibe, und/oder dezentral, d.h. zum Mittelpunkt der Rotorscheibe beabstandet, angeordnet. Die durch die ballige Ausführungsform erzielten Wirkungen sind dabei unabhängig davon, ob die Bohrung zentral oder dezentral vorgesehen ist.In an advantageous embodiment, the bore is central, ie in the center of the rotor disk, and / or decentralized, ie spaced from the center of the rotor disk arranged. The effects achieved by the crowned embodiment are independent of whether the hole is provided centrally or decentrally.

In einer vorteilhaften Ausgestaltung ist der maximale Innendurchmesser der balligen Bohrung in Axialrichtung gesehen mittig zwischen den Stirnseiten der Rotorscheibe angeordnet. Hierdurch wird eine symmetrische Verteilung der erhöhten Druckeigenspannung erzielt.In an advantageous embodiment, the maximum inner diameter of the spherical bore is arranged in the axial direction between the end faces of the rotor disk. As a result, a symmetrical distribution of the increased compressive residual stress is achieved.

Die Erfindung wird anhand einer Zeichnung erläutert.
Es zeigt:

Fig. 1
eine schematische Darstellung einer Strömungsmaschine aus dem Stand der Technik,
Fig. 2
eine Seitenansicht einer erfindungsgemäßen Rotorscheibe mit einer ballig verlaufenden Bohrung,
Fig. 3
eine Schnittansicht durch die Rotorscheibe gemäß Fig. 2 ,
Fig. 4
eine Schnittansicht durch eine Rotorscheibe aus dem Stand der Technik,
Fig. 5
ein Radius-Spannungs-Diagramm für die Rotorscheibe aus dem Stand der Technik,
Fig. 6
eine Schnittansicht durch die erfindungsgemäße Rotorscheibe,
Fig. 7
ein Radius-Spannungs-Diagramm für die erfindungsgemäße Rotorscheibe und
Fig. 8
einen Vergleich der Kennlinien der Diagramme aus Fig.5 und Fig. 7.
The invention will be explained with reference to a drawing.
It shows:
Fig. 1
a schematic representation of a turbomachine from the prior art,
Fig. 2
a side view of a rotor disk according to the invention with a convex bore,
Fig. 3
a sectional view through the rotor disk of FIG. 2,
Fig. 4
a sectional view through a rotor disk of the prior art,
Fig. 5
a radius-voltage diagram for the rotor disk of the prior art,
Fig. 6
a sectional view through the rotor disk according to the invention,
Fig. 7
a radius-voltage diagram for the rotor disk according to the invention and
Fig. 8
a comparison of the characteristics of the diagrams of Figure 5 and Fig. 7.

Gasturbinen und deren Arbeitsweisen sind im allgemeinen bekannt. Hierzu zeigt Fig. 1 eine als Gasturbine 1 ausgebildete Strömungsmaschine mit einem um eine Drehachse 3 drehbar gelagerten Rotor 5. Entlang dessen Längserstreckung folgt einem Verdichter 7 eine Brennkammer 9 mit Brennern 11. Der Brennkammer 9 ist die Turbineneinheit 13 nachgeschaltet. Sowohl im Verdichter 7 als auch in der Turbineneinheit 13 weist der Rotor 5 mehrere aneinanderliegende Rotorscheiben 20 auf, in denen jeweils eine zentrale Bohrung 16 vorgesehen ist, durch die ein Zuganker 21 sich erstreckt.Gas turbines and their operations are generally known. 1 shows a turbomachine 1 designed as a turbomachine 1 with a rotatably mounted about a rotation axis rotor 5. Along the longitudinal extent follows a compressor 7, a combustion chamber 9 with burners 11. The combustion chamber 9, the turbine unit 13 is connected downstream. Both in the compressor 7 and in the turbine unit 13, the rotor 5 has a plurality of adjoining rotor disks 20, in each of which a central bore 16 is provided, through which a tie rod 21 extends.

Fig. 2 zeigt die Seitenansicht einer erfindungsgemäßen Rotorscheibe 14 mit einer zentral angeordneten Bohrung 15, welche in Axialrichtung teilweise ballig verläuft, also nach außen gewölbt verläuft.Fig. 2 shows the side view of a rotor disk 14 according to the invention with a centrally disposed bore 15, which extends in the axial direction partially spherical, that is curved outwardly.

Fig. 3 zeigt einen Schnitt durch die erfindungsgemäße Rotorscheibe 14 gemäß Fig. 2. Die Bohrung 15 erstreckt sich in Axialrichtung des Rotors 5 anfänglich kreiszylindrisch, geht anschließend in einen balligen Abschnitt über und endet mit einem kreiszylindrischen Abschnitt. Der Durchmesser 17 der Bohrung 15 ist im balligen Abschnitt in der Mitte zwischen den beiden Stirnflächen 19 der Rotorscheibe 14 maximal und nimmt in Richtung der Stirnflächen 19 bzw. der kreiszylindrischen Abschnitte beiderseits gleichmäßig ab. Durch den in Axialrichtung teilweise balligen Verlauf der Bohrung 15 weist die Rotorscheibe 14 eine konvexe Ausnehmung auf. Das Material der Rotorscheibe, welches die Ausnehmung umgibt, weist somit eine konkave Kontur auf.FIG. 3 shows a section through the rotor disk 14 according to the invention as shown in FIG. 2. The bore 15 initially extends in the axial direction of the rotor 5 in a circular cylindrical manner, then merges into a crowned section and ends with a circular cylindrical section. The diameter 17 of the bore 15 is maximum in the spherical portion in the middle between the two end faces 19 of the rotor disk 14 and decreases in the direction of the end faces 19 and the circular cylindrical sections on both sides evenly. As a result of the axial, partially convex course of the bore 15, the rotor disk 14 has a convex recess. The material of the rotor disc, which surrounds the recess, thus has a concave contour.

Fig. 4 zeigt eine aus dem Stand der Technik bekannte zylindrische Bohrung 16 durch eine Rotorscheibe 20.4 shows a cylindrical bore 16 known from the prior art through a rotor disk 20.

Fig. 5 zeigt den Verlauf von Spannungen σ einer Rotorscheibe 20 aus dem Stand der Technik in einem Radius-Spannungs-Diagramm. Die in einer Kreis-Strich-Linienart dargestellte Kennlinie 22 zeigt den Verlauf der Tangentialspannungen im Abstand x von der Oberfläche der Bohrung 16 in Radialrichtung. Ebenso zeigt die in Volllinie dargestellte Kennlinie 24 die Mises'schen Vergleichsspannungen. Beide Spannungen nehmen mit steigendem Abstand x von der Oberfläche der zylindrischen Bohrung 16 der Rotorscheibe 20 ab. Nach dem Schleudern der Rotorscheibe 20 weist diese Druckeigenspannungen auf, deren Verlauf in gestrichelter Linienart durch die Kennlinie 26 dargestellt ist. Der Betrag der Druckeigenspannungen verringert sich mit zunehmendem Abstand x.FIG. 5 shows the profile of stresses σ of a rotor disk 20 of the prior art in a radius-voltage diagram. The characteristic curve 22 shown in a circle-dash line type shows the course of the tangential stresses at a distance x from the surface of the bore 16 in the radial direction. Likewise, the curve 24 shown in full line shows the Mises comparison voltages. Both stresses decrease with increasing distance x from the surface of the cylindrical bore 16 of the rotor disk 20. After spinning the rotor disk 20, this pressure compressive stresses, whose course is shown in dashed line type by the characteristic curve 26. The amount of compressive residual stresses decreases with increasing distance x.

Fig. 6 zeigt die erfindungsgemäße Rotorscheibe 14 mit einer entlang der Axialrichtung vollständig konvex ausgebildeten Bohrung 15, deren Form auch als ballig bezeichnet wird.Fig. 6 shows the rotor disk 14 according to the invention with a along the axial direction completely convex bore 15, the shape is also referred to as spherical.

Fig. 7 zeigt den Verlauf von Spannungen σ einer erfindungsgemäßen Rotorscheibe 14 in einem Radius-Spannungs-Diagramm. Die Tangentialspannungen 28 der erfindungsgemäßen Rotorscheibe 14 sind in einer Kreis-Strich-Linienart und die Mises'schen Vergleichsspannungen 30 in Volllinie dargestellt. Beide Spannungen nehmen mit zunehmendem Abstand x von der Oberfläche der balligen Bohrung 15 der Rotorscheibe 14 ab. Nach dem Schleudern der Rotorscheibe 14 weist diese eine in Volllinie dargestellte Druckeigenspannung 32 auf, deren Betrag sich mit zunehmendem Abstand x verringert.FIG. 7 shows the profile of stresses σ of a rotor disk 14 according to the invention in a radius-voltage diagram. The tangential stresses 28 of the rotor disk 14 according to the invention are shown in a circle-dash line type and the Mises comparison voltages 30 in solid line. Both stresses decrease with increasing distance x from the surface of the spherical bore 15 of the rotor disk 14. After spinning the rotor disk 14, this has a compressive residual stress 32 shown in solid line, the amount of which decreases with increasing distance x.

Fig. 8 zeigt die Kennlinien 22, 24, 26, 28, 30, 32 der beiden Diagramme Fig. 5 und Fig. 7 im Vergleich.FIG. 8 shows the characteristic curves 22, 24, 26, 28, 30, 32 of the two diagrams FIG. 5 and FIG. 7 in comparison.

Durch die konvexe Bohrung 14 sind die aus dem Stand der Technik ermittelten Tangentialspannungen 22 gemäß den Pfeilen 34 auf die Tangentialspannungen 28 vermindert worden. Die Mises'schen Vergleichsspannungen 24, 30 wurden durch den balligen Verlauf der Bohrung 15 dagegen gemäß der Pfeile 36 vergrößert, was nach dem Schleudern mit gleichgroßer Schleuderdrehzahl zumindest im radial innen liegenden Bereich der balligen Bohrung 15 eine betragsmäßig vergrößerte Druckeigenspannung gemäß der Pfeile 38 bewirkt.Due to the convex bore 14, the tangential stresses 22 determined from the prior art have been reduced to the tangential stresses 28 according to the arrows 34. By contrast, the Mises comparison stresses 24, 30 were increased by the convex course of the bore 15 according to the arrows 36, which after spinning with the same spin speed at least in the radially inner region of the spherical bore 15 causes an inherent compressive stress according to the arrows 38.

Der um jede Bohrung liegende Bereich, insbesondere bei zentralen Bohrungen der nabennahe Bereich, ist beim Betrieb der Strömungsmaschine den vergleichsweise höchsten Beanspruchungen ausgesetzt, wodurch die Erhöhung der Druckspannungen und die Verminderung der Tangentialspannungen das Risswachstum an dieser Stelle verzögert und somit die Lebensdauer der Rotorscheibe, des Rotors und der Strömungsmaschine verlängert wird.The area lying around each hole, especially in central bores near the nabennahe area is exposed during operation of the turbomachine, the comparatively highest stresses, whereby the increase of the compressive stresses and the reduction of Tangentialspannungen delays the crack growth at this point and thus the life of the rotor disc, the Rotor and the turbomachine is extended.

Claims (7)

Strömungsmaschine (2)
mit einem um eine Drehachse (3) drehbar gelagerten Rotor (5) ,
der zumindest eine Rotorscheibe (14) mit jeweils einer sich durch die Rotorscheibe (14) axial erstreckende Bohrung (15) aufweist,
dadurch gekennzeichnet, dass
die Bohrung (15) in Axialrichtung zumindest teilweise ballig mit im mittleren Bereich größerem Durchmesser verläuft.Turbomachine (2)
with a rotor (5) rotatably mounted about an axis of rotation (3),
the at least one rotor disk (14) each having a bore (15) axially extending through the rotor disk (14),
characterized in that
the bore (15) extends in the axial direction at least partially crowned with in the central region of larger diameter. Strömungsmaschine (2) nach Anspruch 1,
dadurch gekennzeichnet, dass
die Strömungsmaschine (2) eine Turbine, ein Verdichter, eine Gasturbine (1) oder eine Dampfturbine ist.Turbomachine (2) according to claim 1,
characterized in that
the turbomachine (2) is a turbine, a compressor, a gas turbine (1) or a steam turbine. Rotor (5) für eine Strömungsmaschine (2),
der zumindest eine Rotorscheibe (14) mit zumindest einer sich durch die Rotorscheibe (14) axial erstreckende Bohrung (15) aufweist,
dadurch gekennzeichnet, dass
die Bohrung (15) in Axialrichtung zumindest teilweise ballig mit im mittleren Bereich größerem Durchmesser verläuft.Rotor (5) for a turbomachine (2),
the at least one rotor disk (14) having at least one bore (15) extending axially through the rotor disk (14),
characterized in that
the bore (15) extends in the axial direction at least partially crowned with in the central region of larger diameter. Rotorscheibe (14) für den Rotor (5) einer Strömungsmaschine (2),
mit zumindest einer sich durch die Rotorscheibe (14) axial erstreckenden Bohrung (15),
dadurch gekennzeichnet, dass
die Bohrung (15) in Axialrichtung zumindest teilweise ballig mit im mittleren Bereich größerem Durchmesser verläuft.Rotor disk (14) for the rotor (5) of a turbomachine (2),
with at least one bore (15) extending axially through the rotor disk (14),
characterized in that
the bore (15) extends in the axial direction at least partially crowned with in the central region of larger diameter. Rotorscheibe (14) nach Anspruch 4,
dadurch gekennzeichnet, dass
die Rotorscheibe (14) als Verdichterscheibe eines Verdichters oder als Turbinenscheibe einer Turbine ausgebildet ist.Rotor disc (14) according to claim 4,
characterized in that
the rotor disk (14) is designed as a compressor disk of a compressor or as a turbine disk of a turbine. Vorrichtung nach Anspruch 1, 3 oder 4,
dadurch gekennzeichnet, dass
die Bohrung (15) zentral und/oder dezentral vorgesehen ist.Apparatus according to claim 1, 3 or 4,
characterized in that
the bore (15) is provided centrally and / or decentralized. Vorrichtung nach Anspruch 1, 3, 4 oder 6,
dadurch gekennzeichnet, dass
die der maximale Innendurchmesser (17) der balligen Bohrung (15) in Axialrichtung gesehen mittig angeordnet ist.Apparatus according to claim 1, 3, 4 or 6,
characterized in that
the maximum inner diameter (17) of the spherical bore (15) is arranged centrally in the axial direction.
EP04015806A 2004-07-05 2004-07-05 Turbomachine with a rotor comprising at least one drilled disc Withdrawn EP1614857A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04015806A EP1614857A1 (en) 2004-07-05 2004-07-05 Turbomachine with a rotor comprising at least one drilled disc
PCT/EP2005/052698 WO2006003074A1 (en) 2004-07-05 2005-06-10 Non-positive-displacement machine with a rotor having at least one bored rotor disk
EP05760921A EP1763622A1 (en) 2004-07-05 2005-06-10 Turbomachine with a rotor comprising at least one drilled disc
JP2007518576A JP2008505270A (en) 2004-07-05 2005-06-10 Rotating disc of rotor in fluid machinery
CNA200580029209XA CN101040101A (en) 2004-07-05 2005-06-10 Non-positive-displacement machine with a rotor having at least one bored rotor disk
US11/631,768 US7819632B2 (en) 2004-07-05 2005-06-10 Turbo machine with a rotor which has at least one rotor disk with a bore

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04015806A EP1614857A1 (en) 2004-07-05 2004-07-05 Turbomachine with a rotor comprising at least one drilled disc

Publications (1)

Publication Number Publication Date
EP1614857A1 true EP1614857A1 (en) 2006-01-11

Family

ID=34925627

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Application Number Title Priority Date Filing Date
EP04015806A Withdrawn EP1614857A1 (en) 2004-07-05 2004-07-05 Turbomachine with a rotor comprising at least one drilled disc
EP05760921A Withdrawn EP1763622A1 (en) 2004-07-05 2005-06-10 Turbomachine with a rotor comprising at least one drilled disc

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05760921A Withdrawn EP1763622A1 (en) 2004-07-05 2005-06-10 Turbomachine with a rotor comprising at least one drilled disc

Country Status (5)

Country Link
US (1) US7819632B2 (en)
EP (2) EP1614857A1 (en)
JP (1) JP2008505270A (en)
CN (1) CN101040101A (en)
WO (1) WO2006003074A1 (en)

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GB0614972D0 (en) * 2006-07-28 2006-09-06 Rolls Royce Plc A mounting disc
EP2428642A1 (en) * 2010-09-08 2012-03-14 Siemens Aktiengesellschaft Rotor for a steam turbine with circumferential recesses inclined in respect to the rotor main axis
US10119400B2 (en) 2012-09-28 2018-11-06 United Technologies Corporation High pressure rotor disk
US8959767B2 (en) * 2012-11-21 2015-02-24 United Technologies Corporation Method of extending life of rotating parts
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Also Published As

Publication number Publication date
US7819632B2 (en) 2010-10-26
WO2006003074A1 (en) 2006-01-12
US20080031724A1 (en) 2008-02-07
JP2008505270A (en) 2008-02-21
EP1763622A1 (en) 2007-03-21
CN101040101A (en) 2007-09-19

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