EP2112328A1 - Rotor pour une turbomachine - Google Patents

Rotor pour une turbomachine Download PDF

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Publication number
EP2112328A1
EP2112328A1 EP08007702A EP08007702A EP2112328A1 EP 2112328 A1 EP2112328 A1 EP 2112328A1 EP 08007702 A EP08007702 A EP 08007702A EP 08007702 A EP08007702 A EP 08007702A EP 2112328 A1 EP2112328 A1 EP 2112328A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
damping element
groove
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Withdrawn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
EP08007702A
Other languages
German (de)
English (en)
Inventor
Markus Kupetz
Heinrich Dr. Stüer
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 EP08007702A priority Critical patent/EP2112328A1/fr
Publication of EP2112328A1 publication Critical patent/EP2112328A1/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Withdrawn legal-status Critical Current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
    • F01D5/26—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
    • 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

Definitions

  • the invention relates to a rotor for a turbomachine, wherein the rotor has circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a groove in the rotor.
  • a steam turbine as an embodiment of a turbomachine, essentially two components are responsible for the conversion of the thermal energy of the steam into rotational energy.
  • this would be the rotatably mounted rotor and a housing arranged around the rotor.
  • the rotor has so-called. Blades, wherein guide vanes are arranged on the housing.
  • the operating frequencies are 50Hz and 60Hz, respectively, for steam turbines used in the municipal power supply sector.
  • the rotational frequencies occurring during operation lead in connection with the thermodynamic conditions of the steam to undesirable vibrations of the blades. As a rule, cracks occur in the rotor blades, in the airfoil and / or in the blade roots.
  • the blade feet can be designed as so-called double-T, hammer or pine-tree feet. All these feet have in common that they are placed in a corresponding groove in the rotor. Furthermore, turbine blade feet are known which are bent. The bend results in a distribution of the transfer area between the rotor and the turbine blades. The transmitted forces can be better distributed, resulting in an extension of the life.
  • the turbine blades are arranged adjacent to each other on the circumference.
  • the turbine blades have blade plates disposed between the blade roots and the airfoil.
  • the rotor is formed according to the prior art such that between each two blade plates, a projection of the rotor is arranged.
  • the invention starts, the object of which is to provide a rotor having blades arranged in such a way that vibrations during operation can be effectively reduced without disturbing the main flow.
  • a rotor for a turbomachine wherein the rotor has circumferentially adjacent blades, wherein the rotor is formed along an axial direction, wherein the blades have a curved blade root, wherein the blade root is arranged in a groove in the rotor, wherein a damping element is arranged between the blade root and the groove.
  • the invention thus goes the way to realize a power transmission between the groove in the rotor material and the blade root.
  • the power transmission via the damping element, which is arranged between the blade root and the groove. With a vibration of the blade, this vibration is transmitted to the blade root, wherein the damping element disposed between the groove and the blade root exerts a counter force on the blade root in such a way that a damping of the vibrations is achieved.
  • the damping element is For this purpose hammered or caulked between the groove and the blade root.
  • the blade root has a blade root underside directed toward the axis of rotation and blade root side walls, wherein the damping element is arranged between the blade root side wall and the groove.
  • the damping element is therefore arranged in an axial gap between the Schaufelfußitwand and the groove.
  • the blade root is directed along a radial direction. Furthermore, the blade root has a blade root side wall region, which is formed substantially parallel to the radial direction.
  • the damping element is in this case arranged between the groove and the Schaufelfußitwand Scheme. Since the blade root side wall portion is formed substantially parallel to the radial direction, the force transmitted from the cushioning member to the blade root acts perpendicular to the radial direction of the blade, causing the force to act substantially in the circumferential direction. The damping of the blades, which take place in the circumferential direction, thereby effectively avoided.
  • the blade root has a blade root tip with a blade root tip side wall.
  • This blade root tip side wall is formed substantially parallel to the radial direction.
  • the damping element is disposed between the blade root tip side wall and the groove.
  • the blade root tip side wall in this case has a flat, rectilinear surface.
  • this area of the blade root can be easily manufactured in terms of manufacturing technology.
  • the amplitude of a vibration of the blade root in the region of the blade root tip would be greatest. Therefore, an arrangement of the damping element in the region of the blade root tip is advantageous. Oscillations of the entire blade are minimized by the positioning of the damping element in the area of the blade root tip.
  • the damping element is made of a resilient material.
  • a resilient material for example, a blade steel such as X 20 Cr 13 can be used.
  • Another way to use a resilient material is to use a spring steel.
  • the main advantage of using resilient material is that, when the blade roots are bent against the axial direction, a cushioning member made of resilient material exerts a permanent spring force on the blade root which causes the blade root to be pressed against the groove. Due to the elastic properties of the damping element this tries to get back to its original straight shape. For this purpose, a reaction force is developed, which acts on the blade root.
  • the damping element is designed such that it has substantially the shape of a rod. As a result, the damping element can be produced relatively easily and inexpensively. In a further advantageous embodiment, the damping element a rectangular cross section. As a result, the damping element can be easily produced.
  • the damping element has a trapezoidal or conical cross section.
  • the conicity should in this case be such that a taper takes place in the radial direction to the outside. The centrifugal forces occurring during operation on the damping element would then lead to a further jamming of the damping element between the groove and the blade root. This increases the force of the damping element on the blade root, which causes the blade root is pressed even more against the groove. As a result, vibrations of the blade root and thus also vibrations of the entire blade are effectively reduced.
  • the FIG. 1 discloses a part of a rotor 1.
  • the rotor 1 is in the FIG. 1 shown in a plan view. To see several grooves 2, which are designed to receive a blade not shown.
  • the rotor 1 is formed along an axial direction 3.
  • the groove 2 is designed so bent to the axial direction 3 that a curved curve 4 is formed.
  • a likewise bent blade root 5 of a blade is arranged.
  • FIG. 2 is a cross-sectional view of the rotor 1 according to the prior art shown.
  • the blade roots 5 are arranged next to one another in a circumferential direction 6.
  • the blade root is executed here as Tannenbaumfuß.
  • the blade root could, in an alternative embodiment, have a T-shape or an L-shape.
  • the blade roots 5 are inserted laterally into the groove 2.
  • the rotor is designed for a turbomachine, such as a steam turbine.
  • the rotor 1 In the circumferential direction 6, the rotor 1 has a plurality of adjacently arranged blades. Furthermore, the rotor 1 is directed in the axial direction 3.
  • the blades are designed such that the blade root 5 is bent. The bend is carried out here against the axial direction 3, which in the FIG. 1 you can see.
  • the blade root 5 is arranged in a groove 2 in the rotor 1.
  • FIG. 3 shows how a damping element 7 between the blade root 5 and the groove 2 is arranged.
  • the blade root 5 has a blade root underside 8 and laterally arranged blade root side walls 9. The blade is directed in a radial direction 10.
  • the damping element 7 is arranged between the blade root side wall 9 and the groove 2.
  • the blade root 2 has in the lower region a blade root side wall region 11, which is formed substantially parallel to the radial direction 10.
  • the damping element 7 is arranged between the groove 2 and the Schaufelfuß saltwand Scheme 11.
  • the damping element 7 is for this purpose hammered or caulked between the groove 2 and the Schaufelfuß saltwand Scheme 11. As a result, a high voltage between the blade root 5 and the groove 2 is achieved.
  • the contact surfaces form after clamping excellent damping properties for the vibration system foot - blade.
  • the damping element 7 can be disassembled inexpensively. Another advantage is that existing rotors 1 need not be processed. It is sufficient to modify only shovel feet 5. Furthermore, the contact pressure of the blade root 5 is not applied to the groove 2 by centrifugal force, but is already present at startup of the rotor.
  • the damping element 7 is shown.
  • the damping element 7 is formed along a direction 12 and has substantially the shape of a rod.
  • a resilient material is used as a material for the damping element 7.
  • This resilient material is for example a blade steel.
  • the material X 20 Cr 13 can be used as a blade steel.
  • Another springy material suitable for this application is a spring steel.
  • the damping element 7 has a rectangular cross-section 13.
  • the damping element 7 has a trapezoidal or conical cross section 14.
  • the damping element 7 comprises two support flanks 15, wherein in the FIGS. 4 and 5 only a supporting edge 15 can be seen.
  • the support flanks 15 are in accordance with the embodiment FIG. 4 formed parallel to each other, whereas in the embodiment according to FIG. 5 the support flanks 15 are formed at an angle ⁇ against each other.
  • a centrifugal force 16 acts on the damping element 7.
  • the centrifugal force 16 causes a force in the radial direction 10. This means that the elastic bending force of the damping element 7 on the blade root by the trapezoidal design of the damping element 7 with the centrifugal force undergoes support. Damping will be reduced even further.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08007702A 2008-04-21 2008-04-21 Rotor pour une turbomachine Withdrawn EP2112328A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08007702A EP2112328A1 (fr) 2008-04-21 2008-04-21 Rotor pour une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08007702A EP2112328A1 (fr) 2008-04-21 2008-04-21 Rotor pour une turbomachine

Publications (1)

Publication Number Publication Date
EP2112328A1 true EP2112328A1 (fr) 2009-10-28

Family

ID=39739382

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08007702A Withdrawn EP2112328A1 (fr) 2008-04-21 2008-04-21 Rotor pour une turbomachine

Country Status (1)

Country Link
EP (1) EP2112328A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102689022A (zh) * 2012-06-12 2012-09-26 哈尔滨汽轮机厂有限责任公司 汽轮机低压转子末级叶轮的齿型叶根槽加工方法

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1719415A (en) * 1927-09-14 1929-07-02 Westinghouse Electric & Mfg Co Turbine-blade attachment
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
US4711007A (en) * 1986-09-29 1987-12-08 Westinghouse Electric Corp. Method and apparatus for installing free standing turbine blades
US5236309A (en) * 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
GB2287993A (en) * 1994-03-24 1995-10-04 Rolls Royce Plc Gas turbine engine fan blade retention
EP0821133A1 (fr) * 1996-07-27 1998-01-28 ROLLS-ROYCE plc Fixation des aubes de soufflante pour un turboréacteur
EP1209322A2 (fr) * 2000-11-27 2002-05-29 General Electric Company Piece d'insertion
EP1643082A1 (fr) * 2004-09-30 2006-04-05 Siemens Aktiengesellschaft Fixation d'aubes de turbine
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1719415A (en) * 1927-09-14 1929-07-02 Westinghouse Electric & Mfg Co Turbine-blade attachment
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
US4711007A (en) * 1986-09-29 1987-12-08 Westinghouse Electric Corp. Method and apparatus for installing free standing turbine blades
US5236309A (en) * 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
GB2287993A (en) * 1994-03-24 1995-10-04 Rolls Royce Plc Gas turbine engine fan blade retention
EP0821133A1 (fr) * 1996-07-27 1998-01-28 ROLLS-ROYCE plc Fixation des aubes de soufflante pour un turboréacteur
EP1209322A2 (fr) * 2000-11-27 2002-05-29 General Electric Company Piece d'insertion
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine
EP1643082A1 (fr) * 2004-09-30 2006-04-05 Siemens Aktiengesellschaft Fixation d'aubes de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102689022A (zh) * 2012-06-12 2012-09-26 哈尔滨汽轮机厂有限责任公司 汽轮机低压转子末级叶轮的齿型叶根槽加工方法

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