US20110299989A1 - Blade union of a turbo machine - Google Patents

Blade union of a turbo machine Download PDF

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Publication number
US20110299989A1
US20110299989A1 US13/201,893 US201013201893A US2011299989A1 US 20110299989 A1 US20110299989 A1 US 20110299989A1 US 201013201893 A US201013201893 A US 201013201893A US 2011299989 A1 US2011299989 A1 US 2011299989A1
Authority
US
United States
Prior art keywords
blade
coupling element
shroud
arrangement
width
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.)
Abandoned
Application number
US13/201,893
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English (en)
Inventor
Christoph Hermann Richter
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: RICHTER, CHRISTOPH HERMANN
Publication of US20110299989A1 publication Critical patent/US20110299989A1/en
Abandoned 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the invention refers to an arrangement comprising a first blade and a second blade which is arranged adjacent to the first blade.
  • turbomachines Compressors, gas turbines or steam turbines, for example, are to be understood by turbomachines in the sense of this application.
  • the aforesaid turbomachines have in common the fact that they comprise a casing and a rotor which is rotatably mounted in the casing, wherein a flow passage, through which flows a flow medium, is formed between the rotor and the casing.
  • the flow medium is steam in steam turbines.
  • a further problem of vibration excitations is that the rotor blades execute vibrations as a consequence of the vibration excitations, which vibrations lead to material fatigue both of the turbine blade and of the rotor steeple in which the turbine blade is arranged. It would be desirable to achieve a reduction of the vibration amplitudes, which leads to a reduction of the material stress.
  • nodal diameter vibrations develop. These nodal diameter vibrations are characterized in that the amplitudes of the vibrations have a sinusoidal shape over the circumference of the blades.
  • adjacent blades are modified in such a way that a sub-quantity of the blades is provided with a coupling element which is fixedly connected to the blade.
  • This coupling element is designed in such a way that it extends as far as the next neighboring blade, or even as far as the next but one neighboring blade, but is not fixedly connected to the adjacent blade.
  • a blade in the arrangement executes a vibration
  • the blade moves together with the fixedly connected bar.
  • the adjacent blade which is not fixedly connected to the coupling element, presses this—as a result of the centrifugal force which occurs during operation—against the blade, as a result of which a frictional contact is carried out, wherein energy dissipation is carried out as a result of friction, and consequently vibration energy disappears, as a result of which the disturbing vibration is damped.
  • the first blade has a first blade tip and the second blade has a second blade tip, wherein the coupling element is arranged in the region of the first and second blade tips.
  • the damping device is arranged in the blade tip.
  • the coupling element is therefore advantageously arranged in the region of the first and second blade tips. The amplitudes of the disturbing vibrations are greatest there and are therefore damped the most effectively.
  • the first blade tip has a first shroud, wherein the coupling element is fixedly arranged in the first shroud.
  • a coupling element which is basically an external element
  • the shrouds are arranged at the blade tips and have a construction which is comparatively large in relation to the overall blade.
  • the coupling element is fixedly arranged in this shroud.
  • the second blade tip which is associated with the adjacent blade, has a second shroud, wherein the coupling element is arranged in the second shroud.
  • the coupling element is arranged loosely in the second shroud, i.e. not fixedly connected to the second shroud.
  • the second shroud in this case is arranged in such a way that a centrifugal force which occurs during operation leads to the coupling element being pressed against the second shroud. This means that the coupling element rubs in the second shroud in the event of an occurring vibration. Consequently, energy dissipation takes place, as a result of which the vibration is damped.
  • the first shroud and the second shroud have in each case a slot in which the coupling element is arranged.
  • a slot a comparatively simple solution which is favorable to production engineering can be made available in order to effectively arrange the coupling element in the shroud.
  • the slot is arranged at the side in the first shroud and in the second shroud. As a result of the side arrangement, it is possible to easily remove the coupling element during maintenance operations.
  • the coupling element is of a longish and narrow design.
  • the effective damping of the blade vibrations depends essentially upon the shape and the material of the coupling element. The longer the coupling element is, the greater are also the vibration amplitudes of the tip of the coupling element. The longer the coupling element is, the greater are therefore the vibration amplitudes at the tip.
  • the material should be selected in such a way that it can be connected to the blade as rigidly and fixedly as possible, wherein the strength values of the coupling element should be such that the coupling element itself is hardly able to execute separate vibrations.
  • the coupling element is constructed as a plate.
  • the plate advantageously has a rectangular shape, as seen in cross section, with a width L and a height H, wherein it is necessary that L is greater than H and that the coupling element is arranged in the shroud in such a way that the surface with the width L butts against the shroud during operation.
  • the coupling element therefore has the shape of a flat knife blade.
  • the coupling element is comparatively easily bendable in a radial direction, i.e. in the direction in which the centrifugal forces prevail, which leads to the coupling element being able to be easily pressed against the other shroud.
  • bending in the axial direction i.e. perpendicularly to the centrifugal force direction is hardly possible. This means that vibration of the blade, on which the coupling element is fixedly arranged, entrains sufficiently well. As a result, effective damping is possible.
  • FIG. 1 shows a detail of an arrangement as seen in the radial direction, looking onto the shrouds
  • FIG. 2 shows a detail of two adjacent shrouds
  • FIG. 3 shows a perspective view of a shroud.
  • FIG. 1 shows a detail of an arrangement in the radial direction, i.e. the radial direction perpendicular to the plane of the drawing.
  • the arrangement comprises a first blade 1 and a second blade 2 which is arranged adjacent to the first blade 1 .
  • the first blade 1 and the second blade 2 are fixedly arranged via rotor steeples on a rotor, which is not shown in more detail.
  • the rotor rotates around a rotational axis 3 .
  • the first blade 1 and the second blade 2 are of a longish design in the radial direction and are exposed to inflow during operation by a flow medium, which is not shown in more detail, wherein the first blade 1 and the second blade 2 execute a rotation in a rotational direction 4 .
  • the first blade 1 is arranged adjacent to the second blade 2 .
  • the first blade 1 comprises a coupling element 5 which is fixedly connected to the first blade 1 in a way which is not shown in more detail.
  • the coupling element 5 can be fixedly connected to the first blade 1 by means of screw-fastening, riveting or soldering, for example.
  • a vibration 6 of the first blade 1 leads to a vibration of the tip 7 of the coupling element. This also leads to a harmonic vibration 8 of the tip 7 of the coupling element. It is necessary to minimize this harmonic vibration 8 , which is carried out by the coupling element 5 butting against the second blade 2 .
  • the coupling element 5 is arranged in a blade tip of the first blade 1 and in a blade tip of the second blade 2 , which is not shown in more detail in FIG. 1 .
  • FIG. 3 shows a shroud 10 of the first or second blade 1 or 2 .
  • the shroud 10 in this case is arranged at the blade tip of the first blade 1 and of the second blade 2 .
  • the shroud 10 has slots 11 in which the coupling element 5 is arranged.
  • the coupling element 5 In the case of the first blade 1 , the coupling element 5 is fixedly arranged in the slot 11 .
  • the coupling element 5 In the case of the second blade 2 , the coupling element 5 is only loosely arranged in the slot 11 .
  • a centrifugal force which occurs during operation acts in the centrifugal force direction 12 which is identical to the radial direction.
  • FIG. 2 shows an alternative representation of a part of an arrangement.
  • the first blade 1 has a first shroud 13 and the blade 2 has a second shroud 14 .
  • the shrouds are arranged at the blade tip of the first blade 1 and of the second blade 2 .
  • the coupling element 5 is arranged at the side in the first shroud 13 and also in the second shroud 14 .
  • the coupling element 5 is of a longish and narrow design and constructed as a plate.
  • the coupling element 5 has a rectangular shape, as seen in cross section, with a width L and a height H.
  • the height H is essentially identical to the height H of the slot 11 .
  • At least the height H of the plate 5 should be slightly smaller than the height H of the slot 11 .
  • the coupling element 5 is fixedly connected to the first shroud 13 , which can be carried out by means of a screw fastening, for example.
  • screws which fixedly connect the coupling element 5 to the first blade 1 are used.
  • Screwed connections 15 , 16 result from this.
  • the screwed connection 15 , 16 may be oriented in the axial direction 17 , for example.
  • the screwed connection 15 , 16 can naturally also be carried out in the radial direction 18 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/201,893 2009-02-17 2010-01-27 Blade union of a turbo machine Abandoned US20110299989A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09002224A EP2218875A1 (de) 2009-02-17 2009-02-17 Schaufelverband einer Strömungsmaschine
EP09002224.5 2009-02-17
PCT/EP2010/050936 WO2010094540A1 (de) 2009-02-17 2010-01-27 Schaufelverband einer strömungsmaschine

Publications (1)

Publication Number Publication Date
US20110299989A1 true US20110299989A1 (en) 2011-12-08

Family

ID=40874982

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/201,893 Abandoned US20110299989A1 (en) 2009-02-17 2010-01-27 Blade union of a turbo machine

Country Status (4)

Country Link
US (1) US20110299989A1 (de)
EP (2) EP2218875A1 (de)
CN (1) CN102317578A (de)
WO (1) WO2010094540A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130108448A1 (en) * 2011-10-26 2013-05-02 General Electric Company Turbine bucket platform shaping for gas temperature control and related method
US11719440B2 (en) * 2018-12-19 2023-08-08 Doosan Enerbility Co., Ltd. Pre-swirler having dimples

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8951013B2 (en) * 2011-10-24 2015-02-10 United Technologies Corporation Turbine blade rail damper
CN109057870B (zh) * 2018-08-07 2020-12-01 中国航发湖南动力机械研究所 涡轮叶片组

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US2772856A (en) * 1950-08-01 1956-12-04 Rolls Royce Structural elements for turbo-machines such as compressors or turbines of gasturbineengines
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
US3377050A (en) * 1966-06-21 1968-04-09 Bristol Siddeley Engines Ltd Shrouded rotor blades
US3986792A (en) * 1975-03-03 1976-10-19 Westinghouse Electric Corporation Vibration dampening device disposed on a shroud member for a twisted turbine blade
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US4840539A (en) * 1987-03-12 1989-06-20 Alsthom Moving blading for steam turbines
US5645402A (en) * 1996-04-10 1997-07-08 Solar Turbines Incorporated Turbine blade vibration dampening
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1618285A (en) * 1927-02-22 Blade lashing
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
CH272378A (de) * 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
JPS5395406A (en) * 1977-02-02 1978-08-21 Hitachi Ltd Connection structure for vane
US4784571A (en) * 1987-02-09 1988-11-15 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
JPH08303205A (ja) * 1995-05-11 1996-11-19 Hitachi Ltd タービン動翼
GB9609721D0 (en) 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
DE10256778A1 (de) 2001-12-11 2004-01-08 Alstom (Switzerland) Ltd. Schwingungsdämpfer
JP2008045419A (ja) * 2006-08-11 2008-02-28 Mitsubishi Heavy Ind Ltd インテグラルシュラウド翼のせん断応力低減構造
EP2019188A1 (de) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Laufschaufelstufe mit Dämpfungselement

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US2772856A (en) * 1950-08-01 1956-12-04 Rolls Royce Structural elements for turbo-machines such as compressors or turbines of gasturbineengines
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
US3377050A (en) * 1966-06-21 1968-04-09 Bristol Siddeley Engines Ltd Shrouded rotor blades
US3986792A (en) * 1975-03-03 1976-10-19 Westinghouse Electric Corporation Vibration dampening device disposed on a shroud member for a twisted turbine blade
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US4840539A (en) * 1987-03-12 1989-06-20 Alsthom Moving blading for steam turbines
US5645402A (en) * 1996-04-10 1997-07-08 Solar Turbines Incorporated Turbine blade vibration dampening
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130108448A1 (en) * 2011-10-26 2013-05-02 General Electric Company Turbine bucket platform shaping for gas temperature control and related method
US8967973B2 (en) * 2011-10-26 2015-03-03 General Electric Company Turbine bucket platform shaping for gas temperature control and related method
US11719440B2 (en) * 2018-12-19 2023-08-08 Doosan Enerbility Co., Ltd. Pre-swirler having dimples

Also Published As

Publication number Publication date
CN102317578A (zh) 2012-01-11
EP2399005B1 (de) 2012-11-21
EP2218875A1 (de) 2010-08-18
WO2010094540A1 (de) 2010-08-26
EP2399005A1 (de) 2011-12-28

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AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:RICHTER, CHRISTOPH HERMANN;REEL/FRAME:026762/0983

Effective date: 20110708

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION