EP1707746A1 - Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant - Google Patents

Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant Download PDF

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Publication number
EP1707746A1
EP1707746A1 EP05005989A EP05005989A EP1707746A1 EP 1707746 A1 EP1707746 A1 EP 1707746A1 EP 05005989 A EP05005989 A EP 05005989A EP 05005989 A EP05005989 A EP 05005989A EP 1707746 A1 EP1707746 A1 EP 1707746A1
Authority
EP
European Patent Office
Prior art keywords
blade
segment
machine part
groove
blade root
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Withdrawn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
EP05005989A
Other languages
German (de)
English (en)
Inventor
Frank Brumbi
Markus Kupetz
Ulrich Stanka
Heinrich Dr. Stüer
Mesut Tunc
Jörg Wagemakers
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 EP05005989A priority Critical patent/EP1707746A1/fr
Publication of EP1707746A1 publication Critical patent/EP1707746A1/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Withdrawn legal-status Critical Current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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the invention relates to a machine part of a stationary, axially flow-through turbomachine having a segment-forming number of blades, which are held in a groove of the machine part, wherein a blade has a blade root disposed in the groove.
  • the invention further relates to a method for assembling a number of blades in a machine part of a turbomachine in which a machine part is provided with a groove and a segment with a number of blades is mounted in the groove, wherein a blade with its blade root in the groove is arranged.
  • a turbomachine designed as a turbomachine is applied to generate rotational energy in a flow channel with working fluid.
  • a number of blades is arranged, which are flowed through by the working medium.
  • a blade has an airfoil projecting into the flow channel and a blade root attached to the machine part.
  • a machine part can be understood to mean a rotor and / or a housing or another part of the turbomachine designed as a gas or steam turbine or as a compressor.
  • a blade In a turbine, a blade is distinguished between a vane and a rotor or rotor blade.
  • a blade is disposed with its blade root in a groove of the rotor, and a blade blade receives kinetic energy of the working fluid such that the rotor is rotated by the blades.
  • a vane is attached to the non-rotatable machine housing, ie, the turbine housing, and held with its vane root in a groove of the turbine housing, the vane having a vane root disposed in the groove having.
  • a vane blade protrudes into the flow channel and serves to guide the flow medium in order to conduct it as effectively as possible to a rotor blade.
  • a blade ring is formed by a number of blades, wherein the blade roots are held in a groove of the machine part oriented along a ring circumference and an airfoil is oriented along a ring radius.
  • the blade With a blade, the blade is facing outward from the rotor into the flow channel.
  • the vane blade With a guide vane, the vane blade from the engine housing radially inwardly into the flow channel.
  • a bucket may also have a bucket tip.
  • a hitherto known possibility which meets the high load is to fix the blade root by means of a fitting piece which is geometrically adapted specifically to the geometry between the blade root and its surroundings.
  • the geometrically adapted fitting is z. B. specially shaped and inserted on the geometry of a gap or gap between the blade root and Nutberandung.
  • a geometrically adapted fitting piece can be shaped and inserted especially for a geometry between two blade roots. In this way, a fitting piece fills the space between a blade root and a groove and / or between two adjacent ones Shovel feet completely off and sets the blade root either against a Nutberandung or against an adjacent blade root.
  • Another possibility is to fix a blade root on the machine part in the groove, for example by a welded or soldered connection.
  • the invention begins, whose object is to provide an apparatus and a method, wherein the a tight fit of a blade is ensured and on the other hand, a mounting of a blade is facilitated.
  • a blade root of a first blade at a first edge of the segment by a mechanical clamping element with a blade root of a second blade at a second edge of the segment under tension connected is.
  • the object is achieved by an initially mentioned method for assembling a number of blades in a machine part, wherein according to the invention a first blade is arranged with its blade root in the groove to form a first edge of the segment, to form a second edge of the Segment a second blade is arranged with its blade root in the groove and a blade root of the first blade is connected by a mechanical clamping element with a blade root of the second blade under tension.
  • the new concept it is intended to clamp a number of blades forming a segment by means of a mechanical tensioning element.
  • the mechanical clamping element can be formed in particular in the form of a tensioning cable.
  • the number of blades includes at least the first and second blades forming first and second edges of the segment. Preferably, a further number of blades of the segment is clamped between the first and the second blade.
  • the method of assembly thereby envisages loosely inserting the blades into the groove, attaching the tensioning element to the blade root of the first blade and the blade root of the second blade, then pretensioning, for example by means of mechanical or hydraulic tools, and after reaching a predetermined Tighten the tension so that said blade feet are connected under tension.
  • pretensioning for example by means of mechanical or hydraulic tools, and after reaching a predetermined Tighten the tension so that said blade feet are connected under tension.
  • a number of further blades are arranged with their blade root in the groove after the first blade.
  • the invention has recognized that it is possible in this way, with considerable simplification of the assembly, the number of blades forming the segment securely attached to the machine part. In contrast to previously customary procedures, this eliminates the need to underline every single blade with a passport or Stemm collaborate explained above or have to moor precisely. Furthermore, eliminating the need to make individual passport or Stemm thoroughlye tolerance tolerances for each individual blade. A simplification of the assembly is already achieved by the greatly reduced physical force of a fitter, for which it is no longer necessary to attach each individual blade fit. Furthermore, it is ensured according to the new concept that despite the predetermined tension of the blades forming the segment there is still a sufficient degree of freedom to provide a precisely metered installation rotation for the individual blade root.
  • the new concept also permits, above all, rapid disassembly of the blades forming the segment, as may possibly be necessary during inspection work or repairs, since, in contrast to the prior art, it is no longer necessary to release any undercutting of a single blade. Rather, it is sufficient to release the mechanical clamping element and thus to release the clamped blades of the segment as a whole, so that they can be easily removed by being pushed out of the groove.
  • a blade root of a blade of the segment has an opening, in particular a bore, through which the mechanical tensioning element, in particular a tensioning cable, is guided.
  • Such a hole requires only a relatively small overhead in a production of the individual blade.
  • the opening can be attached to a convenient location of the blade root.
  • a blade root of a blade of the segment is mounted in a groove oriented along a circumference of the ring on the turbine part, with a blade having an airfoil oriented along a ring radius. In this way, a complete blade ring can be attached to a turbine part.
  • the mechanical tensioning element in the first and / or second blade is deflected from the direction of the ring circumference in the direction of the ring radius under tension.
  • the mechanical tensioning element is clamped at its ends, for example at the cable ends of a tensioning cable, preferably radially inwardly or outwardly after a first and / or second edge blade.
  • the rope ends are fixed after reaching a predetermined bias and secured against loosening. This ensures that a first and / or second blade arranged on a first and / or second edge of the segment is secured sufficiently.
  • this is achieved by a sufficient radial force, which results from the fact that the mechanical tensioning element is deflected in the direction of the ring radius under tension.
  • a comparatively small deflection of the blade is originally compared with a number of blades of the segment arranged between the first and second blade mechanical clamping element present, so that, based on a circumferentially oriented clamping force, a comparatively low clamping force in the direction of the ring radius is present.
  • This could lead to a comparatively less strong fixation of a first and / or second blade on the edge of the segment and is compensated by the said deflection of the mechanical tensioning element in the direction of the ring radius.
  • the said deflection can take place not only on a single blade arranged on the edge of the segment but, if necessary, for example on two adjacent blades on an edge of the segment.
  • one or more blades close to the edge i. H.
  • the first and / or second blade on a first and / or second edge of the segment exceptionally be supported on the blade root. That is, preferably, a blade root of at least the first and / or the second blade is supported. This also means that a blade close to the edge is provided with a sufficient clamping force in the direction of the ring radius in order to ensure sufficient fixation.
  • the segment is formed in the form of a semicircular segment.
  • the number of blades of an entire half of a blade ring can be clamped by a blade root of the first blade at a first edge of the segment by a mechanical tensioning element with a blade root of the second blade at a second edge of the segment under tension connected is.
  • only two clamping elements would be necessary for the entire blade ring and a Unterstemmen each blade is thereby completely or largely avoided.
  • contact surfaces of adjacent blade roots have centering means.
  • This has the advantage that adjacent blades of the segment center when clamping against each other and even adjust. This increases the secure fixation of each individual blade and at the same time facilitates the Nachjustier pressure, as sets a high degree of self-adjustment and self-fixing by the centering.
  • the centering means may be formed as mutually self-centering on or bulge of the contact surfaces.
  • the centering means could also be formed as a mutually centering pin or a recess on the contact surfaces. The type of centering can be conveniently selected in each case.
  • the invention also leads to a turbine, in particular a gas or steam turbine with a machine part designed as a turbine part or to a compressor with a machine part designed as a compressor part of the kind explained above.
  • FIG. 1 shows a blade 1 in the form of a guide blade, which is attached to a machine part 4 in the form of a machine housing 3 of a turbine.
  • the guide blade 1 has a blade root 5, an airfoil 7 and a blade cover sheet 9.
  • machine housing 3 is provided with a groove 11, and a detail shown in Figure 2 segment of a number of blades as the vane 1 is mounted in the groove 11, wherein each vane 1 with her blade root 5 in the Groove 11 is pushed.
  • FIG. 2 shows, in a view in the direction of the axis 17 of the machine housing 3, a segment 19 which is formed from a number of guide vanes 1, which, as shown in FIG. 1, have a blade root 5, an airfoil 7 and a blade cover leaf 9.
  • Each of the guide vanes 1 has an opening 15 shown in FIG. 1 for passing through a mechanical tensioning element 13.
  • the segment 19 is formed in the form of a semicircular segment, so that the blade ring only half shown in FIG. 2 is formed by two of the segments 19.
  • the segment 19 has a first vane 23 for forming a first edge 21 of the segment, said first vane 23 in FIG. 2 representing a first edge vane.
  • the segment 19 has a second vane 27, which in FIG. 2 represents a second edge vane.
  • the blade root 29 of the first edge blade 23 is connected by the mechanical tensioning element 13 in the form of a tension wire with the blade root 31 of the second edge blade 27 under tension.
  • the further number of blades 33 is clamped between the first edge blade 23 and the second edge blade 27.
  • the first edge blade 23 is arranged with its blade root 29 in the groove 11 of the machine housing 3. Subsequently, the number of further guide vanes 33 of the segment 19 is individually arranged in each case with its blade foot not provided with a reference number in FIG. 2 in the groove. Subsequently, the second edge blade 27 is arranged with its blade root 31 in the groove 11.
  • the respective vanes 23, 24, 27, 28 are braced along the outer annular periphery 35 of the groove 11, so that they are in comparison to the other vanes in FIG the direction of the axis 17 of the machine housing 3 along the ring radius 36 are crazy.
  • the exciting attachment of the guide blades 23, 24 , 27, 28 of the segment 19 a sufficient radial force F r in particular for the near-edge blades 23, 24, 27, 28 provided.
  • the guided through the opening 15 mechanical tensioning element 13 in the form of a tension wire is biased. This can be done for example by means of hydraulic tools. After reaching a predetermined clamping force F t , which is to ensure a sufficient blade tension, the mechanical clamping element is secured against loosening the machine housing 3 in the embodiment shown here.
  • the mechanical tensioning element 13 in the form of a wire rope at the first edge blade 23 and the second edge blade 27 is deflected from the direction of the ring circumference 35 in the direction of the ring radius 36 under tension and sufficient with the above Clamping force secured against loosening.
  • the deflection increases the blade tension, in particular in the region of the edges 21, 25, ie, in the regions X of the segment, since, in particular, the guide vanes 23, 24, 27, 28 arranged in the vicinity of the edges 21, 25 are deflected in a direction along the ring radius 36 to the axis 17 of the machine housing 3 towards the inside of the groove 11 are pressed. In this way, in particular the guide vanes 23, 24, 27, 28 are provided with a sufficient fixation.
  • the deflection of the mechanical tensioning element 13 described above could replace a caulking of the blades 23, 24, 27, 28 in the region X of the segment 19.
  • an embodiment is possible in which the deflection of the mechanical tensioning element 13 is eliminated and only a caulking of the guide vanes 23, 24, 27, 28 in the area X is made.
  • Measures such as the caulking of vanes in the area X or the deflection of a mechanical clamping element 13 may optionally in comparatively strong curved segments 19, ie segments with small ring radius 36, omitted, since at relatively small segments already due to their greater curvature, a sufficiently large clamping force F r can be available in the direction of the ring radius.
  • a blade 1 in order to ensure a simplified and secure assembly of a number of blades 1 in a machine part 4 of a turbomachine, in a machine part 4 with a segment 19 forming number of blades 1, in a groove 11 of the machine part 4 or machine housing 3, wherein a blade 1 has a blade root 5 arranged in the groove 11, provided according to the new concept that a blade root 29 of a first blade 23 at a first edge 21 of the segment 19 by a mechanical tensioning element 13 with a blade root 31 a second blade 27 is connected to a second edge 25 of the segment 19 under tension. Furthermore, a method for mounting according to the new concept is specified.
EP05005989A 2005-03-18 2005-03-18 Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant Withdrawn EP1707746A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05005989A EP1707746A1 (fr) 2005-03-18 2005-03-18 Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05005989A EP1707746A1 (fr) 2005-03-18 2005-03-18 Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant

Publications (1)

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EP1707746A1 true EP1707746A1 (fr) 2006-10-04

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EP05005989A Withdrawn EP1707746A1 (fr) 2005-03-18 2005-03-18 Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB122455A (en) * 1918-01-21 1919-01-21 Charles Algernon Parsons Turbine Blade Attachments.
DE333353C (de) * 1920-04-16 1921-03-18 Osthoff Fa Walter Gewebe-Gassengmaschine
EP1130217A1 (fr) * 2000-03-01 2001-09-05 ABB Alstom Power N.V. Fixation des aubes dans une turbomachine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB122455A (en) * 1918-01-21 1919-01-21 Charles Algernon Parsons Turbine Blade Attachments.
DE333353C (de) * 1920-04-16 1921-03-18 Osthoff Fa Walter Gewebe-Gassengmaschine
EP1130217A1 (fr) * 2000-03-01 2001-09-05 ABB Alstom Power N.V. Fixation des aubes dans une turbomachine

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