EP2428642A1 - Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen - Google Patents

Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen Download PDF

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Publication number
EP2428642A1
EP2428642A1 EP10175762A EP10175762A EP2428642A1 EP 2428642 A1 EP2428642 A1 EP 2428642A1 EP 10175762 A EP10175762 A EP 10175762A EP 10175762 A EP10175762 A EP 10175762A EP 2428642 A1 EP2428642 A1 EP 2428642A1
Authority
EP
European Patent Office
Prior art keywords
rotor
recesses
recess
axis
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.)
Withdrawn
Application number
EP10175762A
Other languages
German (de)
English (en)
French (fr)
Inventor
Thomas Hofbauer
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 EP10175762A priority Critical patent/EP2428642A1/de
Priority to CN201180043522.4A priority patent/CN103097665B/zh
Priority to EP11751877.9A priority patent/EP2614220B1/de
Priority to PCT/EP2011/064824 priority patent/WO2012031931A1/de
Publication of EP2428642A1 publication Critical patent/EP2428642A1/de
Withdrawn legal-status Critical Current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
    • F01D5/08—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 torque curve along the turbine axis or rotation axis is desired on the one hand by 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.
  • the invention is achieved by a rotor for a turbomachine with a discharge region, wherein a plurality of circumferentially arranged recesses 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, among other things, 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 in the beginning and end portion flush with the Rotor surface completes.
  • 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 becomes substantially parallel to the axis of rotation 4 formed.
  • 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 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 is determined from the bottom 19 of the recess to the axis of rotation 4 out.
  • 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 transitions 21 is the Bottom 19 and a side wall 22 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10175762A 2010-09-08 2010-09-08 Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen Withdrawn EP2428642A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP10175762A EP2428642A1 (de) 2010-09-08 2010-09-08 Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen
CN201180043522.4A CN103097665B (zh) 2010-09-08 2011-08-29 具有卸载区域的用于蒸汽轮机的转子
EP11751877.9A EP2614220B1 (de) 2010-09-08 2011-08-29 Rotor für eine dampfturbine mit einem entlastungsbereich
PCT/EP2011/064824 WO2012031931A1 (de) 2010-09-08 2011-08-29 Rotor für eine dampfturbine mit einem entlastungsbereich

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10175762A EP2428642A1 (de) 2010-09-08 2010-09-08 Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen

Publications (1)

Publication Number Publication Date
EP2428642A1 true EP2428642A1 (de) 2012-03-14

Family

ID=43530969

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10175762A Withdrawn EP2428642A1 (de) 2010-09-08 2010-09-08 Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen
EP11751877.9A Not-in-force EP2614220B1 (de) 2010-09-08 2011-08-29 Rotor für eine dampfturbine mit einem entlastungsbereich

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11751877.9A Not-in-force EP2614220B1 (de) 2010-09-08 2011-08-29 Rotor für eine dampfturbine mit einem entlastungsbereich

Country Status (3)

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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH437923A (de) * 1966-04-14 1967-06-15 Albert Ufenast Friedrich Drehkolbenmotor
US5492447A (en) * 1994-10-06 1996-02-20 General Electric Company Laser shock peened rotor components for turbomachinery
US5997264A (en) * 1995-01-26 1999-12-07 Ansimag Incorporated Shaft for a magnetic-drive centrifugal pump using a plurality of grooves
WO2000031394A2 (en) * 1998-11-21 2000-06-02 Roland Grant Heap An engine
EP1052371A2 (en) * 1999-05-14 2000-11-15 General Electric Company Retention sleeve for a transfer tube of a thermal medium in a gas turbine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0353447A1 (en) * 1988-07-29 1990-02-07 Westinghouse Electric Corporation Side-entry grooves for mounting turbine blades
EP1614857A1 (de) * 2004-07-05 2006-01-11 Siemens Aktiengesellschaft Strömungsmaschine mit einem Rotor der zumindest eine gebohrene Rotorscheibe aufweist
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH437923A (de) * 1966-04-14 1967-06-15 Albert Ufenast Friedrich Drehkolbenmotor
US5492447A (en) * 1994-10-06 1996-02-20 General Electric Company Laser shock peened rotor components for turbomachinery
US5997264A (en) * 1995-01-26 1999-12-07 Ansimag Incorporated Shaft for a magnetic-drive centrifugal pump using a plurality of grooves
WO2000031394A2 (en) * 1998-11-21 2000-06-02 Roland Grant Heap An engine
EP1052371A2 (en) * 1999-05-14 2000-11-15 General Electric Company Retention sleeve for a transfer tube of a thermal medium in a gas turbine

Also Published As

Publication number Publication date
EP2614220B1 (de) 2015-07-15
CN103097665B (zh) 2015-04-01
WO2012031931A1 (de) 2012-03-15
CN103097665A (zh) 2013-05-08
EP2614220A1 (de) 2013-07-17

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