EP1752611A1 - Turbine für eine Wärmekraftanlage mit Haltevorrichtung - Google Patents

Turbine für eine Wärmekraftanlage mit Haltevorrichtung Download PDF

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Publication number
EP1752611A1
EP1752611A1 EP05017643A EP05017643A EP1752611A1 EP 1752611 A1 EP1752611 A1 EP 1752611A1 EP 05017643 A EP05017643 A EP 05017643A EP 05017643 A EP05017643 A EP 05017643A EP 1752611 A1 EP1752611 A1 EP 1752611A1
Authority
EP
European Patent Office
Prior art keywords
disc
cam
rotor
blade root
recess
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.)
Granted
Application number
EP05017643A
Other languages
English (en)
French (fr)
Other versions
EP1752611B1 (de
Inventor
Derek Hopkinson
Christoph Dr. 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
Priority to EP20050017643 priority Critical patent/EP1752611B1/de
Priority to DE200560005988 priority patent/DE602005005988T2/de
Publication of EP1752611A1 publication Critical patent/EP1752611A1/de
Application granted granted Critical
Publication of EP1752611B1 publication Critical patent/EP1752611B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • the invention relates to a turbine for a thermal power plant comprising a rotor, at least one blade having a blade root engaged to the rotor via a groove/bar-connection and a locking device being arranged between the blade root and the rotor for blocking a relative movement in at least one direction between the blade root and the rotor.
  • Turbines currently known in the state of the art comprise axially assembled blades.
  • low pressure steam turbine blades comprise blade feet, which are secured in axial and radial direction in order to keep the blade in the rotor groove and to prevent it from rocking motion.
  • rocking motion would eventually damage the surfaces of the blade feet and/or rotor grooves leading to early retirement of the parts involved.
  • a caulking piece is inserted in respective rotor grooves for radial locking.
  • Axial locking is achieved by inserting locking strips in tangential rotor grooves.
  • a turbine for a thermal power plant according to the above type is provided, which is characterized in that the locking device comprises a rotatable cam-disc having at least one lobe.
  • the cam-disc of the locking device By rotating the cam-disc of the locking device from a position, in which the blade root and the rotor abut to the cam-disc at locations away from the lobe to a position, in which the lobe contacts the blade root or the rotor, the blade root and the rotor are pushed apart.
  • the resulting locking of the respective blade root to the rotor can therefore be achieved in a simple assembly operation, namely by merely rotating the cam-disc. This results in a cost efficient assembly process.
  • the locking device can be manufactured of only one single part, which further reduces the cost of the device.
  • the locking of the respective blade root to the rotor can easily be resolved by rotating the cam-disc back into its original position.
  • the blade root can therefore be easily disassembled according to the inventive solution.
  • a new turbine blade can subsequently be installed using the same locking device by rotating the same into its locking position.
  • no grooves in highly loaded zones of the rotor and the blade have to be provided. This increases the durability of the rotor and the respective blades and therefore of the overall turbine.
  • the cam-disc is arranged to create a radial force between the rotor and the blade root in the area of the groove/bar-connection by rotating the cam-disc.
  • the cam-disc is arranged such that its rotational axis is substantially parallel to the longitudinal axis of the rotor.
  • the rotational axis of the cam-disk is arranged with respect to the longitudinal axis of the rotor at an angle in the range from 0° to 40°, preferably in the range from 20° to 30°. This allows a locking of the respective turbine blade in at least a radial direction.
  • the locking device further comprises a preferably bendable cam-shaft connected to the cam-disc and arranged in parallel or substantially in parallel to the longitudinal axis of the rotor, in particular at an angle in the range from 0° to 40°, preferably in the range from 20° to 30° with respect to the longitudinal axis of the rotor.
  • the cam-shaft allows the rotatable cam-disc to be easily operated from the outside of the turbine.
  • the locking device is therefore accessible from one side, preferably from the outlet side of the turbine.
  • the cam-shaft has a turn-key insert, preferably an Inbuskey insert. This way, the locking device can be operated using standard tools.
  • the operation of the inventive turbine is designed service friendly due to the cam-shaft.
  • the cam-shaft further improves the positional stability of the cam-disc, as due to the cam-shaft being arranged between the blade root and the rotor the cam-disc attached thereto is stabilized in a position in which its face sides are perpendicular to the longitudinal axis of the rotor.
  • an "elastic" force can be created between the blade root and the rotor by turning the cam-disc to a position in which the cam-shaft is bent due to the interaction of the lobe on the cam-disc with the blade root.
  • the "elastic" force created therewith keeps a sufficient value over a wide range of rotor operation. This also allows an intentional radial motion of the blade relative to the rotor.
  • the blade root and/or the rotor each have a respective disc recess adapted to accommodate a respective portion of the cam-disc when oriented with its rotation axis being parallel or substantially parallel to the longitudinal axis of the rotor, in particular at an angle in the range from 0° to 40°, preferably in the range from 20° to 30° with respect to the longitudinal axis of the rotor. That means, the cam-disc extends perpendicular to the longitudinal axis of the rotor.
  • the respective disc recesses in the blade root and the rotor allow for axial locking of the turbine blade to the rotor.
  • the cam-disc In order to move the turbine blade relative to the rotor in longitudinal direction, the cam-disc would have to be sheared off the cam-shaft. Hence, a positive fit is achieved.
  • only one locking device is required for blocking both radial and axial movement of a respective blade root relative to the rotor.
  • the rotor has a shaft recess adjoining the disc recess in the rotor and extending along a portion of the cam-shaft, the radial depth of the shaft recess being smaller than the radial depth of the disc recess in the rotor.
  • a correspondingly configured shaft recess allows for the cam-shaft to be bent when rotating the cam-disc to a locked position.
  • the cam-disc comprises at least two lobes, one of which preferably has a larger peak radius than the other one.
  • the respective minimum radii of the angular ranges between the at least two lobes have at least two different values. That allows the cam-disc to be arranged in a first rotational position, in which the angular range between the at least two lobes having the smaller value faces towards the blade root. In this rotation position the blade root can be engaged with the rotor by sliding the same along the rotor in a longitudinal direction of the rotor, such that the bar and the groove of the groove/bar connection slide into each other. In this sliding operation the blade root can slide over the cam-disc.
  • the cam-disc can be rotated to an orientation, in which the angular range between the at least two lobes having the larger radius faces towards the blade root and therewith protrudes into the disc recess of the blade root.
  • the cam-disc can be oriented in a so-called equilibrium range, which means the cam-disc is in a stable locking position between the at least two lobes.
  • An undesired unlocking of the blade root by a rotation of the cam-disc induced by vibration movement during the operation of the turbine is prevented by the at least two lobes delimiting the possible movement of the cam-disc with respect to the blade root to the angular range between the two lobes.
  • the at least one lobe contains a blocking lobe, which has a peak radius being adapted, such that the respective portion of the cam-disc exceeds the depth of the disc recess in the blade root and/or the rotor in a way that it blocks and/or resists a full revolution of the cam-disc.
  • the peak radius of the blocking lobe can be made larger than the peak radius of the safeguard lobe, but can also be made equal to that radius. This feature improves the locking reliability of the blade root to the rotor, as it helps prevent an undesired unlocking of the connection.
  • the connection between the blade root and the rotor can only easily be unlocked by rotating the cam-disc reversely to the rotation direction employed for locking the connection.
  • Rotating the cam-disc in the same direction is not or not easily possible due to the presence of the locking lobe. This effect also increases the user friendliness of the locking device, as the operator is prevented by the blocking lobe of rotating the cam-disc too far during the locking operation.
  • the at least one lobe contains a safeguard lobe, which has a peak radius being adapted, such that the respective portion of the cam-disc exceeds the depth of the recess in the blade root in a way that the cam-disc can only be rotated beyond by simultaneously bending the cam-shaft. That means, in order to unlock the groove/bar-connection the cam-disc has to be rotated against a "resistance" generated by the safeguard lobe, which can only be overcome by causing the cam-shaft to bend. This feature further prevents an unintentional unlocking of the groove/bar-connection caused for example by vibrations generated during the operation of the turbine.
  • the groove/bar-connection comprises an undercut groove and a correspondingly bulged bar, preferably a groove and a bar each having a fir-tree profile.
  • the groove and the bar can have a dove tail profile. This way the engagement between the blade root and the rotor is particularly robust. A radial force generated by the locking device, pushing the rotor and the blade root apart causes the engagement between the undercut groove and the correspondingly bulged bar to be locked.
  • Fig. 1 depicts a sectional view of a connection portion between a turbine rotor 10 of a thermal power plant having a rotor axis 11 and a blade root 12 of a turbine blade.
  • the blade root 12 can have a straight bottom, as shown in Fig. 1, or a curved bottom.
  • the turbine blade is a substantially axially assembled blade that means for assembly the blade root 12 is slid in a linear or curved path oriented at a small angle towards the direction of the rotor axis 11, which is the horizontal direction in Fig. 1, into a rotor groove 13 shown in Fig. 2.
  • the rotor groove 13 has a fir-tree profile and is adapted to the profile of the correspondingly shaped blade root 12.
  • the rotor groove 13 and the blade root 12 can have a dove tail profile.
  • the blade root 12 and the rotor groove 13 engage in a radial direction of the turbine rotor 10, which corresponds to the vertical direction in Fig. 1 and 2. That means, the engagement between the blade root 12 and the rotor groove 13 prevents the blade root 12 from slipping out of the rotor groove 13 in a radial direction.
  • the locking device 14 comprises a cam-shaft 18 arranged parallel to the rotor axis 11 and a cam-disc 16 arranged at one end of the cam-shaft 18.
  • the cam-disc 16 protrudes both into a disc recess 22 of the rotor 10 and a disc recess 24 of the blade root 12.
  • Adjoining the disc recess 22 of the rotor 10 a shaft recess 20 of smaller radial depth in comparison to the disc recess 22 is provided in the rotor 10. As illustrated in Figs.
  • the shaft recess 20 allows a bending of the cam-shaft 18 if a radial force F is applied to the cam-disc 16 arranged at the front end of the cam-shaft 18.
  • Fig. 3 shows a perspective view of the locking device 14.
  • the profile of the cam-disc 16 in the plane of the face of the cam-disc 16 is shown in detail in Figs. 4a and 4b.
  • Fig. 4a shows the profile of the cam-disc 16 in Cartesian and polar coordinates
  • Fig. 4b shows this profile in polar coordinates.
  • the radius r is plotted developed against the angle ⁇ .
  • the locking device 14 is arranged in a rotation position, as shown in Fig. 2, in which the portion with the minimum radius 32 faces radially outwards with respect to the rotor axis 11.
  • the blade root 12 can be slid in and out of rotor groove 13 without interference with the cam-disc 16, that means the blade root 12 can slide over the cam-disc 16.
  • the cam-disc 16 is rotated via a turn-key insert 34 at the opposite face of the cam-shaft 18 and/or at the face of the cam disc 16 (not shown in the figures).
  • the turn-key insert 34 can be operated via an Inbuskey or a similar tool.
  • By rotating the cam-disc 16 its outer perimeter is extended into the disc recess 24 of the blade root 12.
  • the safeguard lobe 26 hits against the bottom portion of the disc recess 24. This creates a force acting on the blade root 12 and reacting on the cam-disc 16.
  • the cam-shaft 18 bends as shown in Fig 5b.
  • the locking device 14 In order to unlock the blade root 12 the locking device 14 has to be rotated reversely to the rotation direction employed for locking the blade root 12. That means, using an Inbuskey the locking device 14 is rotated via the safeguard lobe 26 back to a position with the minimum radius 32 facing towards the disc recess 24 of the blade root 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20050017643 2005-08-12 2005-08-12 Turbine für eine Wärmekraftanlage mit Haltevorrichtung Not-in-force EP1752611B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20050017643 EP1752611B1 (de) 2005-08-12 2005-08-12 Turbine für eine Wärmekraftanlage mit Haltevorrichtung
DE200560005988 DE602005005988T2 (de) 2005-08-12 2005-08-12 Turbine für eine Wärmekraftanlage mit Haltevorrichtung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20050017643 EP1752611B1 (de) 2005-08-12 2005-08-12 Turbine für eine Wärmekraftanlage mit Haltevorrichtung

Publications (2)

Publication Number Publication Date
EP1752611A1 true EP1752611A1 (de) 2007-02-14
EP1752611B1 EP1752611B1 (de) 2008-04-09

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EP20050017643 Not-in-force EP1752611B1 (de) 2005-08-12 2005-08-12 Turbine für eine Wärmekraftanlage mit Haltevorrichtung

Country Status (2)

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EP (1) EP1752611B1 (de)
DE (1) DE602005005988T2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008037661A1 (de) * 2006-09-27 2008-04-03 Siemens Aktiengesellschaft Sicherungsvorrichtung einer turbinenschaufel
EP2808490A1 (de) * 2013-05-29 2014-12-03 Alstom Technology Ltd Turbinenschaufel mit Verriegelungsstift
CN105525950A (zh) * 2011-06-09 2016-04-27 通用电气公司 涡轮机叶片锁定系统
CN110836130A (zh) * 2018-08-17 2020-02-25 斗山重工业建设有限公司 涡轮机、燃气涡轮机及涡轮叶片分离方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986779A (en) * 1974-05-27 1976-10-19 Brown Boveri-Sulzer Turbomaschinen Aktiengesellschaft Locking device for releasably fastening parts to rotors of fluid flow machines
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
DE4231339A1 (de) * 1992-09-18 1994-03-24 Hans Kuehl Vorrichtung zum Paßzentrieren und zum Paßverbinden
DE10141113A1 (de) * 2001-08-22 2003-03-06 Ina Schaeffler Kg Sicherung von axial aufeinander schiebbaren Bauteilen

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986779A (en) * 1974-05-27 1976-10-19 Brown Boveri-Sulzer Turbomaschinen Aktiengesellschaft Locking device for releasably fastening parts to rotors of fluid flow machines
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
DE4231339A1 (de) * 1992-09-18 1994-03-24 Hans Kuehl Vorrichtung zum Paßzentrieren und zum Paßverbinden
DE10141113A1 (de) * 2001-08-22 2003-03-06 Ina Schaeffler Kg Sicherung von axial aufeinander schiebbaren Bauteilen

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008037661A1 (de) * 2006-09-27 2008-04-03 Siemens Aktiengesellschaft Sicherungsvorrichtung einer turbinenschaufel
CN105525950A (zh) * 2011-06-09 2016-04-27 通用电气公司 涡轮机叶片锁定系统
CN105525950B (zh) * 2011-06-09 2017-08-29 通用电气公司 涡轮机叶片锁定系统
EP2808490A1 (de) * 2013-05-29 2014-12-03 Alstom Technology Ltd Turbinenschaufel mit Verriegelungsstift
KR20140140497A (ko) * 2013-05-29 2014-12-09 알스톰 테크놀러지 리미티드 터빈의 블레이드
JP2014231839A (ja) * 2013-05-29 2014-12-11 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ タービンのブレード
CN110836130A (zh) * 2018-08-17 2020-02-25 斗山重工业建设有限公司 涡轮机、燃气涡轮机及涡轮叶片分离方法
CN110836130B (zh) * 2018-08-17 2022-04-05 斗山重工业建设有限公司 涡轮机、燃气涡轮机及涡轮叶片分离方法

Also Published As

Publication number Publication date
EP1752611B1 (de) 2008-04-09
DE602005005988D1 (de) 2008-05-21
DE602005005988T2 (de) 2009-05-20

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