EP1905954A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1905954A1
EP1905954A1 EP06019710A EP06019710A EP1905954A1 EP 1905954 A1 EP1905954 A1 EP 1905954A1 EP 06019710 A EP06019710 A EP 06019710A EP 06019710 A EP06019710 A EP 06019710A EP 1905954 A1 EP1905954 A1 EP 1905954A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
airfoil
turbine blade
attachment member
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Withdrawn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
EP06019710A
Other languages
German (de)
English (en)
Inventor
Katharina Bergander
Georg Dr. Bostanjoglo
Tobias Dr. Buchal
Winfried Dr. Esser
Dirk Dr. Goldschmidt
Torsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Dr. Oechsner
Ursula Pickert
Volker Dr. Vosberg
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 EP06019710A priority Critical patent/EP1905954A1/fr
Publication of EP1905954A1 publication Critical patent/EP1905954A1/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Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to a turbine blade, in particular a blade for a turbine of a thermal power plant with an airfoil and a fastening member for securing the turbine blade to a holding element of the turbine. Moreover, the invention relates to a turbine with such a turbine blade.
  • the attachment member is designed as a blade root and attachable to a rotor of the turbine.
  • Turbine blades of the aforementioned type are usually produced as castings. Due to a high accumulation of material in the region of the attachment member, or the blade root in the case of a blade, it often comes to impurities or inclusions due to casting. These occur especially with turbine blades for higher turbine stages, such as turbine blades for turbine stages three and four. The impurities impair the technical usability or the optical design of the turbine blades. In general, however, it is a requirement owed to the service that the components of a turbine are optically perfect. Therefore, in prior art turbine blades faulty areas are reworked by hand after the usual mechanical processing, such as by blending or by recesses. As a rule, this reworking leads to a visual impairment or even to a non-usability of the turbine blades. This is certainly the case if permissible specification limits of the reworked areas are exceeded.
  • This object is achieved according to the invention with a generic turbine blade, wherein the blade and the fastening member are designed as two or as separate components and secured together.
  • the object is achieved according to the invention with a turbine for a thermal power plant, which is provided with such a turbine blade.
  • the object is achieved according to the invention with an airfoil for a turbine blade of a turbine of a thermal power plant comprising a fastening member for securing the turbine blade to a rotor of the turbine, wherein the airfoil is formed separately from the fastening member and is designed such that it on the blade root is fastened.
  • the object is achieved according to the invention with a fastening member for a turbine blade comprising a blade of a turbine, wherein the fastening member is formed separately from the airfoil and is designed such that it can be fastened to the airfoil.
  • the attachment member is formed as a blade root and serves to fasten the turbine blade to the holding member in the form of a rotor of the turbine.
  • the turbine blade generally has a longitudinal extent with which it is arranged in the state attached to the holding element of the turbine radially to the rotor of the turbine.
  • the airfoil and the fastening member are fastened or fastened to one another in such a way that the attachment of a relative force between the airfoil and the fastening element counteracts parallel to the longitudinal extent of the turbine blade.
  • the separate execution of the blade and the attachment member of the turbine blade allows easier and error-free production of the individual components.
  • the geometry of the individual components Compared to the integral production of the turbine blade from a single piece simplified by the separate production the components according to the invention, the geometry of the individual components.
  • different materials for the airfoil and the fastener may be used in the turbine blade according to the invention, which are each adapted to the different mechanical requirements of the components. This measure improves the mechanical properties of the turbine blade as a whole.
  • it is possible by the separate design of the blade and the attachment member to use different manufacturing processes for the corresponding components.
  • the airfoil can be cast while the attachment member is forged.
  • the fastening member can be used in the same form for turbine blades of different turbine stages.
  • the fastener in particular the blade root of a blade can be designed as a standard component, which is combined with blades for different turbine stage. This reduces the manufacturing and construction costs for turbine blades of different turbine stages.
  • Another advantage of the turbine blade according to the invention is to be able to exchange the individual components of the turbine blade separately as part of a maintenance or a refurbishment.
  • the blade and the fastener can be replaced according to their different wear intervals.
  • each of the two components is first checked for errors after its manufacture and only error-free components are then connected to each other.
  • the blade and the attachment member are fastened to each other by means of a positive connection.
  • the airfoil and the attachment member are engaged with each other. This allows a robust connection of the two components, which withstands the centrifugal forces occurring during operation of the turbine.
  • the positive connection between the blade and the attachment member is designed such that the blade and the attachment member are interlocked.
  • the toothing of the two components takes place in particular via a Christmas tree profile or a dovetail in one of the two components and a recess adapted thereto in the respective other component.
  • the airfoil is provided with a Tannenbaumprofil having male member.
  • the male element advantageously has wedge-shaped elements protruding transversely to the longitudinal extension of the turbine blade.
  • a particularly robust connection between the airfoil and the attachment member can be made when the airfoil and the attachment member are fastened together by a groove / land connection extending along the rotor axis with the turbine blade attached to a rotor of the turbine.
  • a groove / web connection is interlocked with one another in such a way that the airfoil is fixed to the fastening member in the direction of the longitudinal extent of the turbine blade.
  • Such a groove / web connection makes it possible to easily fasten the blade to the attachment member.
  • the groove / web connection extends transversely to the longitudinal extent of the turbine blade. A connection of the airfoil with the fastener can thus be done by simply telescoping the two components.
  • the turbine blade has at least one fastening bolt with which the blade is fastened to the fastening member.
  • each attachment bolt passes through the airfoil and / or attachment member in a direction transverse to the longitudinal extent of the turbine blade.
  • the attachment member has a web-like male member which is inserted into a groove of the airfoil adapted thereto.
  • Each fastening bolt is expediently used to positively connect the groove and web of the two components with each other.
  • the fastening bolts can be inserted transversely to the extent of the groove / web connection in each case a corresponding bore.
  • fastening bolts are evenly distributed along the groove / web connection.
  • the turbine blade has a blade platform for partially delimiting a flow channel of the turbine, wherein the fastening member is formed integrally with the blade platform.
  • the blade platform serves to confine the flow medium, which may include superheated steam or hot gas, in a radial direction of the turbine.
  • the one-piece design of the attachment member with the blade platform is particularly advantageous.
  • the blade platform is formed integrally with the blade root, which is fixed in the rotor of the turbine.
  • the airfoil is formed integrally with a blade platform for partially bounding a flow channel of the turbine. This prevents flow medium from the flow channel of the turbine, such as hot steam or hot gas penetrates into the attachment region between the airfoil and the fastening member. Such penetration of flow medium could lead to a loosening of the compound.
  • the blade and the attachment member on different materials.
  • the airfoil is made of a different material or a different material composition than the attachment member.
  • the blade has intermetallic phases, and thus homogeneous chemical compounds of two or more metals.
  • the attachment member, in particular the blade root is expediently produced from a casting material based on nickel.
  • the blade is designed as a casting and the attachment member or the blade root is either a casting or a forged part. By the cast execution of the airfoil good high temperature strength properties can be achieved.
  • a forged blade root has good dynamic strength properties.
  • FIG. 1 shows a first embodiment of a turbine blade 10 according to the invention in the form of a blade for a turbine of a thermal power plant, in particular for a gas turbine or a steam turbine.
  • the turbine blade 10 has a longitudinal extent extending essentially along a longitudinal axis 12 and comprises the blade 14 and a fastening element 16 in the form of a blade root.
  • the attachment member 16 is for securing the turbine blade 10 to a rotor of the turbine.
  • the fastening member 16 has a plug-in section 18 with a fir-tree-shaped profile.
  • the turbine blade 10 further comprises a paddle platform 20 which is integral with the attachment member 16.
  • the blade platform 20 serves to partially limit a flow channel of the associated turbine.
  • the airfoil 14 and the attachment member 16 are designed as separate components and fixed in a form-fitting manner to each other.
  • the airfoil 14 has a plug-in section 2.
  • the profile of the male portion 22 has a fir tree shape in a sectional plane extending in the attached state of the turbine blade transversely to an axial extent of the turbine rotor.
  • the attachment member 16 has a receiving area 24 adapted to the shape of the insertion portion 22 of the airfoil 14.
  • the insertion portion 22 and the receiving portion 24 extend perpendicular to the plane of the drawing according to FIG. 1 or parallel or obliquely to the axial extent of the rotor of the turbine, and substantially straight.
  • the blade 14 For attachment of the airfoil 14 on the Attachment member 16, the blade 14 is inserted with its insertion portion 22 along the longitudinal extension of the receiving area 24, that is perpendicular to the plane of the drawing of FIG. 1, in the receiving area 24.
  • the male portion 22 By engaging the male portion 22 with the receiving portion 24, a positive connection between the airfoil 14 and the attachment member 16 is formed.
  • the second embodiment of the turbine blade 10 according to the invention shown in FIG. 2 differs from the first embodiment shown in FIG. 1 in that the blade platform 20 is not made in one piece with the attachment member 16 but integrally with the airfoil 14.
  • FIG. 3 shows a third embodiment of the turbine blade according to the invention.
  • the blade platform 20 is integral with the attachment member 16 as in the first embodiment of FIG.
  • the positive connection between the fastening member 16 and the blade 14 is designed in this case by means of a fastening bolt 30.
  • the fastening member 16 has a plug-in section 26 in the form of a web, which runs in the rotor-mounted state of the turbine blade 10 parallel to the rotor axis.
  • the male portion 26 is inserted into a receiving portion 28 formed in the lower portion of the airfoil 14 in the form of a groove.
  • a mounting bolt 30 is inserted transversely to the longitudinal axis 12 of the turbine blade 10 in a through the receiving portion 28 of the airfoil 14 and the insertion portion 26 of the mounting member 16 extending bore 32.
  • Fig. 4 fourth embodiment of the turbine blade according to the invention differs from the third embodiment shown in Fig. 3 only in that the blade platform 20 is not integral with the Attachment member 16, but is integral with the blade 14 is executed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06019710A 2006-09-20 2006-09-20 Aube de turbine Withdrawn EP1905954A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06019710A EP1905954A1 (fr) 2006-09-20 2006-09-20 Aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06019710A EP1905954A1 (fr) 2006-09-20 2006-09-20 Aube de turbine

Publications (1)

Publication Number Publication Date
EP1905954A1 true EP1905954A1 (fr) 2008-04-02

Family

ID=37649556

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06019710A Withdrawn EP1905954A1 (fr) 2006-09-20 2006-09-20 Aube de turbine

Country Status (1)

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EP (1) EP1905954A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH700071A1 (de) * 2008-12-12 2010-06-15 Alstom Technology Ltd Laufschaufel für eine Gasturbine.
EP2226134A2 (fr) * 2009-03-04 2010-09-08 Rolls-Royce plc Procédé de fabrication d'une surface portante
EP2322764A1 (fr) * 2009-11-17 2011-05-18 Siemens Aktiengesellschaft Fixation d'aubes de turbines pour une turbomachine
EP2441917A1 (fr) * 2010-10-18 2012-04-18 Siemens Aktiengesellschaft Elément d'adaptation d'un pied d'aube de turbine et procédé de fixation d'une aube dans un arbre rotatif d'une turbine à vapeur
EP2574723A1 (fr) * 2011-09-30 2013-04-03 Alstom Technology Ltd Procédé de transformation pour turbine à vapeur et dispositif associé
EP2581559A3 (fr) * 2011-10-12 2017-11-08 General Electric Company Ensemble adaptateur pour accouplement d'aubes de turbine au disque rotor
CN110107362A (zh) * 2019-05-31 2019-08-09 南京赛达机械制造有限公司 高强度耐腐蚀汽轮机紧固型动叶片
DE102011054550B4 (de) 2010-10-20 2022-06-15 General Electric Company Rotationsmaschine mit Nuten zur Steuerung der Fluiddynamik

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1362074A (en) * 1919-05-03 1920-12-14 British Westinghouse Electric Turbine
GB740757A (en) * 1952-10-27 1955-11-16 Power Jets Res & Dev Ltd Blades for compressors, turbines and like fluid flow machines
US3635587A (en) * 1970-06-02 1972-01-18 Gen Motors Corp Blade cooling liner
JPS5710705A (en) * 1980-06-24 1982-01-20 Toshiba Corp Manufacture of turbine wheel
US4417854A (en) * 1980-03-21 1983-11-29 Rockwell International Corporation Compliant interface for ceramic turbine blades
EP0285778A1 (fr) * 1987-03-19 1988-10-12 BBC Brown Boveri AG Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé
DE3844191A1 (de) * 1988-12-29 1990-07-05 Mtu Muenchen Gmbh Schaufelfussbefestigung fuer eine fasertechnische rotorschaufel
EP1447524A2 (fr) * 2003-02-13 2004-08-18 Alstom Technology Ltd Aube hybride pour turbomachines thermiques
EP1674511A1 (fr) * 2004-12-23 2006-06-28 Siemens Aktiengesellschaft Matière plastique comprenant des nanoparticules et revêtements produits de celle

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1362074A (en) * 1919-05-03 1920-12-14 British Westinghouse Electric Turbine
GB740757A (en) * 1952-10-27 1955-11-16 Power Jets Res & Dev Ltd Blades for compressors, turbines and like fluid flow machines
US3635587A (en) * 1970-06-02 1972-01-18 Gen Motors Corp Blade cooling liner
US4417854A (en) * 1980-03-21 1983-11-29 Rockwell International Corporation Compliant interface for ceramic turbine blades
JPS5710705A (en) * 1980-06-24 1982-01-20 Toshiba Corp Manufacture of turbine wheel
EP0285778A1 (fr) * 1987-03-19 1988-10-12 BBC Brown Boveri AG Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé
DE3844191A1 (de) * 1988-12-29 1990-07-05 Mtu Muenchen Gmbh Schaufelfussbefestigung fuer eine fasertechnische rotorschaufel
EP1447524A2 (fr) * 2003-02-13 2004-08-18 Alstom Technology Ltd Aube hybride pour turbomachines thermiques
EP1674511A1 (fr) * 2004-12-23 2006-06-28 Siemens Aktiengesellschaft Matière plastique comprenant des nanoparticules et revêtements produits de celle

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8911213B2 (en) 2008-12-12 2014-12-16 Alstom Technology Ltd Rotor blade for a gas turbine
EP2196624A1 (fr) 2008-12-12 2010-06-16 Alstom Technology Ltd Aube d'une turbine à gaz
CH700071A1 (de) * 2008-12-12 2010-06-15 Alstom Technology Ltd Laufschaufel für eine Gasturbine.
EP2226134A2 (fr) * 2009-03-04 2010-09-08 Rolls-Royce plc Procédé de fabrication d'une surface portante
US8926285B2 (en) 2009-11-17 2015-01-06 Siemens Aktiengesellschaft Turbine blade fastening for a turbomachine
WO2011061193A1 (fr) * 2009-11-17 2011-05-26 Siemens Aktiengesellschaft Fixation d'ailette de turbine pour une machine d'écoulement
EP2322764A1 (fr) * 2009-11-17 2011-05-18 Siemens Aktiengesellschaft Fixation d'aubes de turbines pour une turbomachine
RU2562687C2 (ru) * 2009-11-17 2015-09-10 Сименс Акциенгезелльшафт Крепление турбинной лопатки для турбомашины
EP2441917A1 (fr) * 2010-10-18 2012-04-18 Siemens Aktiengesellschaft Elément d'adaptation d'un pied d'aube de turbine et procédé de fixation d'une aube dans un arbre rotatif d'une turbine à vapeur
WO2012052358A1 (fr) * 2010-10-18 2012-04-26 Siemens Aktiengesellschaft Dispositif adaptateur de pied pour fixer une aube dans un évidement d'un arbre rotatif d'une turbine à vapeur, et procédé de fixation d'aube
DE102011054550B4 (de) 2010-10-20 2022-06-15 General Electric Company Rotationsmaschine mit Nuten zur Steuerung der Fluiddynamik
EP2574723A1 (fr) * 2011-09-30 2013-04-03 Alstom Technology Ltd Procédé de transformation pour turbine à vapeur et dispositif associé
US9328612B2 (en) 2011-09-30 2016-05-03 Alstom Technology Ltd Retrofitting methods and devices for large steam turbines
EP2581559A3 (fr) * 2011-10-12 2017-11-08 General Electric Company Ensemble adaptateur pour accouplement d'aubes de turbine au disque rotor
CN110107362A (zh) * 2019-05-31 2019-08-09 南京赛达机械制造有限公司 高强度耐腐蚀汽轮机紧固型动叶片

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