EP1574666A1 - Rangée d'aubes de turbine - Google Patents

Rangée d'aubes de turbine Download PDF

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Publication number
EP1574666A1
EP1574666A1 EP04005463A EP04005463A EP1574666A1 EP 1574666 A1 EP1574666 A1 EP 1574666A1 EP 04005463 A EP04005463 A EP 04005463A EP 04005463 A EP04005463 A EP 04005463A EP 1574666 A1 EP1574666 A1 EP 1574666A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blades
turbine blade
blade row
blade
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Withdrawn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
EP04005463A
Other languages
German (de)
English (en)
Inventor
Heinrich Dr. Stüer
Frank Truckenmüller
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 EP04005463A priority Critical patent/EP1574666A1/fr
Publication of EP1574666A1 publication Critical patent/EP1574666A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/10—Anti- vibration 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a turbine blade row with a Number of turbine blades and a turbomachine, having such a turbine blade row.
  • a turbomachine in particular a steam turbine, has substantially moving parts and stationary parts.
  • the moving parts include a rotatably mounted about a rotation axis rotor.
  • the rotor is usually housed in an inner housing.
  • the inner housing is attached within some outer embodiments of a steam turbine in some embodiments.
  • the rotor has a rotor shell surface, are mounted on the symmetrical to the axis of rotation in the radial direction extending blades.
  • a blade row consists of blades which are mounted in a common plane perpendicular to the axis of rotation on the rotor.
  • vanes Guide vane rows attached on the inner housing are several consisting of vanes Guide vane rows attached.
  • the vane rows differ among other things by the length of the individual vanes.
  • the inner housing and the rotor are formed in such a way that between the rows of vanes, the blade rows protrude.
  • a guide or blade is also called Turbine blade called.
  • Turbine blade also called.
  • a Leit- Blade row also known as turbine blade row.
  • a flow medium in particular water vapor, flows over an entrance to the steam turbine and is through the deflected individual runners and vanes. The temperature the flow medium drops here. It finds one Energy conversion of initially thermal energy in kinetic energy instead. As a result of this energy conversion the rotor is set in a rotary motion. These Rotational motion can generate electrical energy used by means of a generator connected to the rotor become.
  • the and blades In high-pressure and medium-pressure steam turbines, the and blades usually solid. Steam turbines are usually for speeds of 50 or 60 Hz. Constructed. Converted at these speeds 3000 revolutions / min or 3600 revolutions / min occur enormous Centrifugal forces in the blades.
  • the blades of a Low-pressure steam turbine are therefore made hollow to the Weight of the blades to a minimum.
  • a hollow running blade cheaper than a solid running blade.
  • the vanes In addition to the blades are also the vanes usually hollow at least in low-pressure steam turbines executed.
  • the hollow guide and blades are made a sheet metal or two deep-drawn Sheet metal halves welded together. Disadvantageous in operation a steam turbine are vibrations of the leading and Blades. The natural frequencies of hollow formed Guides and blades are compared to massive ones Lower vanes.
  • the object of the present invention is to provide a To introduce turbine blade row, the small invalid Has vibrations.
  • the task is performed by a turbine blade row with a Number of turbine blades solved, the Turbine blades are divided into at least two groups, which is in a mechanical natural frequency of them different turbine blades.
  • the inventors have recognized that in addition to the suggestion for Flutter of individual guide or blade, another Fluttering phenomenon occurs when adjacent Leit- Blades similar or same natural frequencies exhibit. This leads to resonance-like amplified Vibrations, which also cause a failure of the whole Steam turbine could lead.
  • the turbine blade row is not according to the invention formed throughout with identical turbine blades. Rather, at least two groups of consciously become aware Turbine blades formed.
  • the mechanical natural frequency a turbine blade in a group is different from the mechanical natural frequency of a turbine blade one other group.
  • a forced oscillation of a Turbine blade from a group has a lower Influence on the vibration of a turbine blade from a other group than the vibration of a turbine blade from the same group.
  • a mutual suggestion of Turbine blades from different groups is thereby minimized as far as possible.
  • the turbine blade row in a Turbomachine used.
  • FIG 1 is a sectional view through a steam turbine 1 as Embodiment of a turbomachine shown.
  • the Steam turbine 1 has a rotor 2 with a rotor surface on, in a manner not shown to a Rotation axis 3 is rotatably mounted.
  • the steam turbine 1 has an inner housing 4, which is rotationally symmetrical to Rotation axis 3 is arranged.
  • the rotor 2 has radial extending blades 5, which in a circumferential direction rotationally symmetrical to the axis of rotation 3 on the Rotor surface to a blade row (17) mounted one behind the other.
  • steam turbine 1 is shown by the sectional view only one blade 5 per row of blades (17) detect.
  • vanes 6th On an inner surface of the inner housing 4 are guide vanes 6th appropriate. Multiple vanes 6 are rotationally symmetrical to the axis of rotation 3 on the inner housing. 4 appropriate.
  • a flow medium in particular steam, flows over one Inflow 8 in the steam turbine.
  • the Flow medium flows alternately along the axis of rotation through a guide or blade row.
  • the thermal Energy of the flow medium is here in kinetic Energy converted.
  • the rotor 3 is thereby in rotation added.
  • the flow medium then flows out of a Outflow region 9 from the steam turbine.
  • FIG. 2 is a plan view of a blade row 17 to see.
  • the blades 5 are in a direction of rotation 11 arranged at equidistant intervals on the rotor 2.
  • a blade 5 can be seen.
  • the blade 5 becomes from a direction 12 of a flow medium incident flow.
  • the blade 5 is hollow and has a pressure side 13 and a suction side 14.
  • the Flow medium first flows to a leading edge 15 and then flows to a trailing edge 16.
  • the blade 5 moves in operation about the axis of rotation. 3
  • FIG. 4 shows a developed turbine blade row 17 shown.
  • the turbine blade row 17 may consist of Leit- or Blades exist.
  • the turbine blade row 17 has a first one Natural frequency having first turbine blade 19. to first turbine blade 19 directly adjacent is a second natural frequency having second turbine blade 20th arranged.
  • the first and second natural frequency is differently.
  • the first turbine blade 19 is here hollow executed and from a sheet with a certain first sheet thickness formed.
  • the second turbine blade 20 is also made hollow and from a second sheet formed with a second sheet thickness. By choosing the Sheet thickness can be formed arbitrary natural frequencies become.
  • a third natural frequency third turbine blade 25 arranged.
  • the third turbine blade 25 is as well as the first 19 and second turbine blade 20 made hollow.
  • the third turbine blade 25 is another one Natural frequency having further turbine blade 26th arranged.
  • the turbine blades 19, 20, 25, 26 also alternately solid and hollow or only massive be executed.
  • a first block 28 formed from a predetermined number of by their natural frequency distinguishable turbine blades 19, 20, 25, 26, 27 is trained.
  • the first block 28 five Turbine blades 19, 20, 25, 26, 27 on.
  • the turbine blades 19, 20, 25, 26, 27 are in this Embodiment divided into five groups, where the groups in a mechanical natural frequency of them associated turbine blades 19, 20, 25, 26, 27 differ.
  • a block can also have fewer turbine blades 19, 20, 25, 26, 27.
  • a second block 29 arranged in addition to the first block 28, a second block 29 arranged.
  • the second block 29 has the same number Turbine blades 19, 20, 25, 26, 27, as the first block 28.
  • the order and natural frequencies of the turbine blades 19, 20, 25, 26, 27 of the first block 28 and the second Block 29 are identical here.
  • a further block 30 is arranged at the second block 29 .
  • the further block 30 has as many turbine blades as the first Block 28 and the second block 29 and is what the order the turbine blades 19, 20, 25, 26, 27 and the Natural frequencies are identical to these.
  • a Turbine blade row 17 is finally formed, the a predetermined number of blocks 28, 29, 30 has.
  • the Number of blocks 28, 29, 30 depends on the size of the Turbine blades 19, 20, 25, 26, 27 and of the diameter of the rotor 2 from.
  • the blocks 28, 29, 30 are formed such that the Turbine blades 19, 20, 25, 26, 27 of each block 28, 29, 30th come from different groups.
  • the embodiment of a turbine blade row 17 in Figure 5 has a first natural frequency having first Turbine blade 19 'and a second natural frequency having second turbine blade 20 'on.
  • the first Turbine blade 19 'and the second turbine blade 20' together form a first block 28 '.
  • a second block 29 ' is right next to the first block 28.
  • Next to the second Block 29 ' is in turn a further block 30' attached, the a first turbine blade 19 'and a second one Turbine blade 20 'has.
  • the number at blocks 28 ', 29', 30 ' depends on the size of the Turbine blades 19 ', 20' and the diameter of the rotor 2 off.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04005463A 2004-03-08 2004-03-08 Rangée d'aubes de turbine Withdrawn EP1574666A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04005463A EP1574666A1 (fr) 2004-03-08 2004-03-08 Rangée d'aubes de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04005463A EP1574666A1 (fr) 2004-03-08 2004-03-08 Rangée d'aubes de turbine

Publications (1)

Publication Number Publication Date
EP1574666A1 true EP1574666A1 (fr) 2005-09-14

Family

ID=34814262

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04005463A Withdrawn EP1574666A1 (fr) 2004-03-08 2004-03-08 Rangée d'aubes de turbine

Country Status (1)

Country Link
EP (1) EP1574666A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2548221C1 (ru) * 2014-02-13 2015-04-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Способ доводки рабочего колеса газотурбинного двигателя (гтд)
US12025024B2 (en) 2020-09-10 2024-07-02 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine wheel, turbine, and turbocharger

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
JPS59150903A (ja) * 1983-02-09 1984-08-29 Toshiba Corp 回転機械の翼配列構造
JPH06248902A (ja) * 1993-03-01 1994-09-06 Toshiba Corp タービン動翼の配列方法
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
US6379112B1 (en) * 2000-11-04 2002-04-30 United Technologies Corporation Quadrant rotor mistuning for decreasing vibration

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916258A (en) * 1956-10-19 1959-12-08 Gen Electric Vibration damping
JPS59150903A (ja) * 1983-02-09 1984-08-29 Toshiba Corp 回転機械の翼配列構造
JPH06248902A (ja) * 1993-03-01 1994-09-06 Toshiba Corp タービン動翼の配列方法
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
US6379112B1 (en) * 2000-11-04 2002-04-30 United Technologies Corporation Quadrant rotor mistuning for decreasing vibration

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 008, no. 284 (M - 348) 26 December 1984 (1984-12-26) *
PATENT ABSTRACTS OF JAPAN vol. 018, no. 640 (M - 1717) 6 December 1994 (1994-12-06) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2548221C1 (ru) * 2014-02-13 2015-04-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Способ доводки рабочего колеса газотурбинного двигателя (гтд)
US12025024B2 (en) 2020-09-10 2024-07-02 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine wheel, turbine, and turbocharger

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