EP1818506A1 - Réduction de la fatigue répétitive dans un pied de sapin - Google Patents

Réduction de la fatigue répétitive dans un pied de sapin Download PDF

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Publication number
EP1818506A1
EP1818506A1 EP06002583A EP06002583A EP1818506A1 EP 1818506 A1 EP1818506 A1 EP 1818506A1 EP 06002583 A EP06002583 A EP 06002583A EP 06002583 A EP06002583 A EP 06002583A EP 1818506 A1 EP1818506 A1 EP 1818506A1
Authority
EP
European Patent Office
Prior art keywords
blade root
insert
receptacle
blade
designed
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Withdrawn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
EP06002583A
Other languages
German (de)
English (en)
Inventor
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 EP06002583A priority Critical patent/EP1818506A1/fr
Publication of EP1818506A1 publication Critical patent/EP1818506A1/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Withdrawn legal-status Critical Current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
    • F01D5/16—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
    • F01D5/26—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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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 turbomachine having at least one blade with a blade root disposed thereon, which is accommodated in a receptacle of a bearing element.
  • turbomachines are known, for example, as a compressor, steam turbine or gas turbine.
  • the turbomachine has a rotor rotatably mounted about a rotation axis, in which a blade is anchored with its blade root.
  • the turbomachine on guide vanes, which are anchored with its Leitschaufelfuß in an inner housing or a Leitschaufelani.
  • the blade root of the blade in fir shape as a so-called Tannenfuß.
  • the correspondingly designed receptacle in the bearing element or in the rotor is designed according to the design of Tannenfußes.
  • the turbomachine has not only a blade and a vane, but a plurality thereof, so that a blade grid is formed, through which a medium flows.
  • the US 2001/0038793 A1 and the reasons for this priority DE 100 22 244 disclose a vane arrangement with damping elements in the known turbomachines.
  • the vane arrangement with damping elements comprises a rotor and vanes arranged on the circumference of the rotor, wherein damping elements are arranged between the vanes and are in contact with the vanes when the rotor rotates about a rotor axis by means of a radial centrifugal force.
  • At least between two adjacent blades a plurality of damping elements in the circumferential direction of the rotor are arranged one behind the other, so that during a rotation of the rotor arranged behind one another damping elements touch over one or more touch surfaces.
  • a first one of the damping elements arranged one behind another comes into contact with a first friction surface of the one and a second of the damping elements arranged one behind the other comes into contact with a second friction surface of the other of the adjacent blades.
  • the damping elements are arranged on the undersides of the two blade platforms, so that the undersides of the two blade platforms form friction surfaces against which the two damping elements are pressed during a rotation of the rotor by the centrifugal force.
  • the US 5,226,784 discloses a rotor blade damper of a gas engine.
  • the damper is loosely mounted in a receptacle of a disc having an axis of rotation.
  • the receptacle forms a chamber between the disc and the blade platform of a blade, which extends radially outwardly from the disc.
  • the damper comprises a generally axially extending body, which damper acts against the disc and blade platform during operation of the gas engine due to centrifugal forces.
  • the US 5,368,444 deals with the problem of friction reduction between the blade root and the receptacle. These are in the US 5,368,444 Rolls between the blade root and the receptacle arranged so that the blade root is no longer movable in a radial direction during rotation, but is held. This is done by the relative movement between the receptacle and the blade root is derived via the rotational movement of the rollers.
  • blade vibration is meant, for example, that the blade or the blade are subject to high stresses due to the rotation and the flowing past medium.
  • the induced by the blade vibrations in the foot stresses lead to high alternating voltages in areas of high static medium voltage. This combination leads to increased high-cyclic material fatigue (HCF).
  • the invention is therefore based on the object with simple means to improve a turbomachine of the type mentioned so that the life of the blade root or Tannenfußes is considerably extended.
  • this is achieved in that the blade root is supported in the region of its foot plate to the bearing element within the receptacle such that a vibratory stress of the blade root is derived in the form of bending vibrations, the blade root is seen laterally supported seen in longitudinal section, and wherein the blade root is movably mounted seen in the recording in the radial direction.
  • a movable mounting in the radial direction of the blade root is to be understood in the sense of the invention as that the foot or blade root with centrifugal rotor diameter change, so on the one hand a rotor diameter enlargement and on the other a rotor diameter reduction, can move outward or inward.
  • the vibratory stress in the form of bending vibrations is derived by the support in the region of the foot plate of Tannenfußes.
  • the support thus supports mainly laterally and not radially, which would correspond to the attachment of another contemplatniers.
  • the exclusive lateral support also has the advantageous effect that natural frequencies are not scattered by unquantifiable effects in the support, systematically postponed or uncontrollable.
  • the invention is also based on the finding that torsional modes generally do not have a life-sustaining or shortening effect in the blade root or Tannenfuß, so that only bending modes are incorporated in the inventive design of the support.
  • the blade root is designed as Tannenfuß, wherein the receptacle is designed as corresponding thereto configured fir groove.
  • the blade root in the region of its base plate associated with an insert, which is on the one hand with a supporting flank of the blade root and on the other hand with the opposite edge of the receptacle in connection.
  • the base side is oriented to a central axis of the bearing element, and its support side is oriented to the blade root and the receiving side to the flank of the receptacle, wherein a truncated to the base side tip is, and wherein an angle ⁇ between the support side and the receiving side has an amount such that it is greater than a self-locking of the insert.
  • Self-locking in the context of the invention is the friction of the components to each other. According to the invention, the angle ⁇ is now selected with such an amount that the insert is designed to be self-locking. This blockages are advantageously prevented.
  • the Tannenfuß is adjusted with its base plate to the concave curvature, and lays down in this one.
  • the insert By means of the insert according to the invention a preferred embodiment of the invention is provided in which the blade root or the Tannenfuß due to its displaceability in the radial direction has only a minor stiffness in the radial direction, but not in the tangential direction.
  • the insert With increasing speed of the blade root in the recording or in the Tannennut migrated due to the rotor diameter increase on larger diameters. This can advantageously happen without hindrance, since the inserted insert migrates.
  • the insert Will the turbomachine operated at a rated speed, the insert is an inhibitor of bending stresses. In this way, the HCF stress in the blade root or in its Schaufelfußkerben is reduced.
  • the insert is now designed or designed so that this has a self-locking design, which blockages during the rotor speed reduction are advantageously prevented.
  • the blade root on a tapered base plate, wherein the receptacle has a corresponding configuration has a relatively high radial rigidity, which can be avoided by performing, for example, relatively long projecting and thin supports.
  • FIG. 1 shows a section of a turbomachine which has at least one blade (not shown) with a blade root 1 arranged thereon and which is mounted in a receptacle 2 of a bearing element 3.
  • the blade root 1 is designed as Tannenfuß, which is referred to below as Tannenfuß 1.
  • the bearing element 3 is designed as a rotor in the illustrated embodiment, wherein the receptacle 2 has a corresponding to the Tannenfuß 1 configured fir groove 4 and mating surface.
  • the Tannenfuß 1 and the Tannennut 4 and the mating surface are shown in Figure 1 only in sections.
  • the blade root 1 or Tannenfuß 1 is supported in the region of its base plate 6 to the bearing element 3 out within the receptacle 2 or 4 Tannennut or the mating surface such that vibratory stresses of the blade root or Tannenfußes are derived in the form of bending vibrations.
  • the blade root 1 or the Tannenfuß 1 is seen in longitudinal section laterally supported, wherein the blade root 1 and the Tannenfuß 1 in the receptacle 2 and in the fir groove 4 seen in the radial direction 7 is movably mounted.
  • the blade root 1 or the Tannenfuß 1 is assigned an insert 8 in the region of its base plate 6.
  • the insert 8 is on the one hand with a supporting edge 9 of the blade root 1 and the Tannenfußes and on the other hand with the opposite flank 11 of the receptacle 2 and the fir groove 4 in combination.
  • the insert 8 is seen in longitudinal section triangular executed whose base side 12 is oriented to a center axis of the bearing element 3, not shown, and the support side 13 to the blade root 1 and the Tannenfuß 1 and its receiving side 14 to the edge 11 of the receptacle 2 or 4 Tannennut oriented is.
  • a to the base side 12 opposite tip 16 is truncated, wherein an angle ⁇ between the tooth side 13 and the receiving side 14 has such an amount that the insert 8 is designed to be self-locking, to avoid blockages, for example, in a rotor speed reduction.
  • FIG. 2 shows an advantageous embodiment of the insert 8 shown in principle in Figure 1 is shown.
  • the insert 8 according to FIG. 2 is concavely curved on its support side 13, relative to a central axis X of the insert 8, the receiving side 14 opposite thereto corresponding to the embodiment according to FIG. 1, being rectilinear with respect to the central axis X of the insert 8.
  • the advantageous embodiment of Figure 2 causes the relatively straight receiving side 14 provides a defined position of the insert 8 is available, wherein the receiving side 14 is advantageously designed as a relatively short arm for bending stresses. Due to the concave configuration of the support side 13 is a pressure point 15 of the bending stress moved relatively close to the surface of Tannenfußes 1.
  • FIG. 3 shows a further advantageous embodiment for supporting the blade root 1 and the Tannenfußes in the receptacle 2 and in the Tannennut 4.
  • a tapered Schaufelfußplatte 6 is shown, which is received in a correspondingly designed Tannennut 4.
  • the blade root plate 6 extends in its first tooth region from a surface 19 obliquely downwards in the direction of the central axis of the bearing element 3, not shown, and merges into a section 21, which is configured perpendicular to the central axis (not shown).
  • the region of the first blade root tooth with the obliquely downwardly oriented portion 18 is straight.
  • a relatively long and relatively thin support 22 is provided.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06002583A 2006-02-08 2006-02-08 Réduction de la fatigue répétitive dans un pied de sapin Withdrawn EP1818506A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06002583A EP1818506A1 (fr) 2006-02-08 2006-02-08 Réduction de la fatigue répétitive dans un pied de sapin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06002583A EP1818506A1 (fr) 2006-02-08 2006-02-08 Réduction de la fatigue répétitive dans un pied de sapin

Publications (1)

Publication Number Publication Date
EP1818506A1 true EP1818506A1 (fr) 2007-08-15

Family

ID=36636925

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06002583A Withdrawn EP1818506A1 (fr) 2006-02-08 2006-02-08 Réduction de la fatigue répétitive dans un pied de sapin

Country Status (1)

Country Link
EP (1) EP1818506A1 (fr)

Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US479723A (en) 1892-07-26 George g
GB671960A (en) 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
SU418618A1 (fr) * 1972-01-25 1974-03-05
US4169694A (en) 1977-07-20 1979-10-02 Electric Power Research Institute, Inc. Ceramic rotor blade having root with double curvature
DE3133158C1 (de) 1981-08-21 1982-12-16 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Pressflaechen-Zwischenlage aus Metall und Verfahren zur Herstellung derselben
DE3825951A1 (de) 1987-08-05 1989-02-16 Gen Electric Turbinenschaufelplattformdicht- und -schwingungsdaempfungsvorrichtung
US4820126A (en) 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
DE3815977A1 (de) 1988-05-10 1989-11-30 Mtu Muenchen Gmbh Folienzwischenlage zur fuegung von reibkorrosionsgefaehrdeten maschinenbauteilen
US5087174A (en) 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5156528A (en) 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5226784A (en) 1991-02-11 1993-07-13 General Electric Company Blade damper
US5368444A (en) 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5478207A (en) 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
EP0918139A2 (fr) 1997-11-25 1999-05-26 ROLLS-ROYCE plc Amortisseur à friction
EP1048821A2 (fr) * 1999-04-30 2000-11-02 General Electric Company Pied d'aube avec une forme diminuant la tension
US20010038793A1 (en) 2000-05-08 2001-11-08 Herbert Brandl Blade arrangement with damping elements
US20020146322A1 (en) 2001-04-10 2002-10-10 Stuart Yeo Vibration damping
DE10256778A1 (de) 2001-12-11 2004-01-08 Alstom (Switzerland) Ltd. Schwingungsdämpfer

Patent Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US479723A (en) 1892-07-26 George g
GB671960A (en) 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
SU418618A1 (fr) * 1972-01-25 1974-03-05
US4169694A (en) 1977-07-20 1979-10-02 Electric Power Research Institute, Inc. Ceramic rotor blade having root with double curvature
DE3133158C1 (de) 1981-08-21 1982-12-16 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Pressflaechen-Zwischenlage aus Metall und Verfahren zur Herstellung derselben
DE3825951A1 (de) 1987-08-05 1989-02-16 Gen Electric Turbinenschaufelplattformdicht- und -schwingungsdaempfungsvorrichtung
US4820126A (en) 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
DE3815977A1 (de) 1988-05-10 1989-11-30 Mtu Muenchen Gmbh Folienzwischenlage zur fuegung von reibkorrosionsgefaehrdeten maschinenbauteilen
US5087174A (en) 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5226784A (en) 1991-02-11 1993-07-13 General Electric Company Blade damper
US5156528A (en) 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5368444A (en) 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5478207A (en) 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
EP0918139A2 (fr) 1997-11-25 1999-05-26 ROLLS-ROYCE plc Amortisseur à friction
EP1048821A2 (fr) * 1999-04-30 2000-11-02 General Electric Company Pied d'aube avec une forme diminuant la tension
US20010038793A1 (en) 2000-05-08 2001-11-08 Herbert Brandl Blade arrangement with damping elements
DE10022244A1 (de) 2000-05-08 2001-11-15 Alstom Power Nv Schaufelanordnung mit Dämpfungselementen
US20020146322A1 (en) 2001-04-10 2002-10-10 Stuart Yeo Vibration damping
US6659725B2 (en) 2001-04-10 2003-12-09 Rolls-Royce Plc Vibration damping
DE10256778A1 (de) 2001-12-11 2004-01-08 Alstom (Switzerland) Ltd. Schwingungsdämpfer

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