EP2295724B1 - Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques - Google Patents

Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques Download PDF

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Publication number
EP2295724B1
EP2295724B1 EP09011070A EP09011070A EP2295724B1 EP 2295724 B1 EP2295724 B1 EP 2295724B1 EP 09011070 A EP09011070 A EP 09011070A EP 09011070 A EP09011070 A EP 09011070A EP 2295724 B1 EP2295724 B1 EP 2295724B1
Authority
EP
European Patent Office
Prior art keywords
blade
stator blade
circumferential groove
vane
stator
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.)
Not-in-force
Application number
EP09011070A
Other languages
German (de)
English (en)
Other versions
EP2295724A1 (fr
Inventor
Bernhard Küsters
Marc Mittelbach
Uwe Sieber
Dirk Wistuba
Ulrich Waltke
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 AT09011070T priority Critical patent/ATE547591T1/de
Priority to EP09011070A priority patent/EP2295724B1/fr
Priority to US12/868,946 priority patent/US8622708B2/en
Priority to JP2010190834A priority patent/JP5073027B2/ja
Priority to CN201010268815XA priority patent/CN102003219B/zh
Publication of EP2295724A1 publication Critical patent/EP2295724A1/fr
Application granted granted Critical
Publication of EP2295724B1 publication Critical patent/EP2295724B1/fr
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
    • F01D5/3023—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
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • the invention relates to a guide vane for an axially flow-through turbomachine, comprising a two opposing sides having blade root with a platform and at least one arranged thereon blade. Furthermore, the invention relates to a stator blade assembly having a support structure, on the inner circumferential surface of which a circumferential groove is provided in which guide vanes held in a form-locking manner are arranged in a row.
  • Such a guide vane and guide vane assembly for a compressor are, for example, from US 2005/0191177 A1 known.
  • a circumferential groove is provided for each vane ring of a compressor stage.
  • the sidewalls of the circumferential groove have undercuts to hold guide vanes inserted therein with correspondingly shaped, hammer-shaped blade roots in this form-fitting manner.
  • Two adjacent vanes in the circumferential groove each have a bore in their opposite side surfaces.
  • a clamping sleeve for mechanical coupling of the two immediately adjacent blade feet is used.
  • a strained seat of blades known in a hammer-shaped circumferential groove For applying a force acting on the blades in the radial direction clamping force a circumferential groove is formed in the groove bottom of the circumferential groove, in which a force acting on the blade spring ring is used.
  • the spring ring is formed in the form of a curved clamping sleeve, which in addition to the usual longitudinal slot also has a plurality of slots extending in its circumferential direction, whereby interposed freely ending spring arms are formed, by means of which the blades inserted in the circumferential groove are fixed braced in the radial direction.
  • the object of the invention is the specification of an alternative vane arrangement and the provision of a suitable vane.
  • a vane for an axially flow-through turbomachine comprising a two opposing sides blade root with a platform and at least one arranged thereon blade, the blade root having on one of the two sides at least one protruding molding, in which at least one threaded hole is provided for radially clamping the guide vane in a circumferential groove of a supporting structure of a turbomachine by means of a clamping screw screwed into the threaded hole, supported on the groove base of the circumferential groove and wherein the blade root on the other of the two sides has at least one recess for receiving at least one Having molded piece of an adjacent vane including a screwed therein screw.
  • the guide vane arrangement according to the invention makes it possible to achieve a radially fixed clamping of the guide vane in the support structure of an axial-flow turbomachine. Since the clamping force is generated only when screwing and tightening the clamping screw, the guide vane and in particular the blade root can be manufactured with comparatively large tolerances and with comparatively low accuracy of fit with respect to the contour of the circumferential groove. On the one hand this facilitates the positioning, i. Insertion and displacement of the vane in the circumferential groove. On the other hand, the gaps required for thermal expansion can thereby be kept at a sufficient size, which renders the vane arrangement less susceptible to thermal influences.
  • the tensioning of the guide blade on the support structure blocks relative movements of the guide vanes and thereby reduces possible wear.
  • the guide vanes due to their play-free attachment to a defined radial position, whereby the radial gaps between the free-standing blade tips of the vanes and the rotor opposite these blades tips can be set and manufactured closer than before. This reduces the radial gap losses occurring in the flow medium at the blade tips of freestanding vanes during operation of the turbomachine, which increases the efficiency of the turbomachine.
  • the clamping screw required for clamping In order for the clamping screw required for clamping the guide vane does not protrude into the flow channel of the turbomachine is at one of the two opposite Side of the blade root arranged therefrom a shaped piece.
  • the fitting is arranged substantially closer to the underside of the blade root than at the surface of the platform.
  • a threaded hole is provided in which the clamping screw can be screwed. Since the fitting protrudes laterally, the threaded hole and the clamping screw for assembly work are particularly accessible.
  • the platform of that guide vane which is arranged directly adjacent to a respective vane, covers the shaped piece including the clamping screw of the relevant vane.
  • at least one recess in a size is provided on the other of the two opposite sides of the blade root, which corresponds at least to the installation space of the shaped piece including the clamping screw screwed therein.
  • the Leitschaufelfuß is hammer-shaped.
  • the guide vane on one side comprises two fittings, each with a threaded hole.
  • a tension of the guide blade take place, in which the clamping force is generated in each case close to the side walls of the circumferential groove and not like a vane with only one fitting, centered in between. This increases the security of the tension.
  • two threaded holes are provided with a comparable distance in a correspondingly large fitting.
  • the vane may also be formed as a vane segment, which has two or more blades.
  • the turbomachine is an axially flow-through compressor, so that the guide vane is formed as a compressor vane or as a compressor vane segment.
  • At least one of the guide vanes has a fuse for receiving blade root reaction forces in the circumferential direction.
  • each vane has been secured in this way so far. Due to the now reliable and strained with relatively large force vane, the number of previously used fuses can be reduced to accommodate blade root reaction forces, so that, for example, only every fourth or every third vane to accommodate such forces must be secured.
  • the support structure is designed as a guide blade carrier or as a turbomachine housing, which is split in half along its axial extension. This facilitates the insertion of vanes in the circumferential groove. Also, the provision of a vane lock is avoided, which would otherwise be required for a one-piece support structure with a then endless circumferential groove.
  • FIG. 2 show in perspective from different directions a guide vane 10 according to the invention for a turbomachine.
  • the vane 10 includes a blade root 12 having two opposite sides 14, 16. Between the two opposite sides 14, 16, a platform 18 is arranged, protruding from the surface 20 of a transversely extending aerodynamically curved blade 22 freestanding.
  • a protruding molding 24 is integrally formed in the manner of a tab.
  • the molding 24 is arranged centrally near a blade root bottom 25.
  • a threaded hole 26 is present, whose threaded axis is oriented perpendicular to the plane of the surface 20 of the platform 18.
  • a recess 29 is provided at the other (14) of the two sides 14, 16 .
  • the recess 29 of the relevant vane 10 is chosen in its position and size so that when adjacent in a ring vanes 10, the or each fitting 24 - including one disposed therein, in 1 and FIG. 2 Clamping screw not shown - one to the respective vane 10 immediately adjacent vane 10 can be fully absorbed.
  • the vane 10 also has two hooks 27 which protrude at a web 23 connecting the two sides 14, 16. Between hook 27 and platform 18 is thereby a respective groove 28 for receiving projections of the circumferential groove is present, in which the guide vane 10 is to be used.
  • the web 23 and the hooks 27 have a hammer-like appearance, after which the blade root 12 is also referred to as hammer-shaped.
  • the juxtaposed in the circumferential groove vanes 10 are always in such a way that the one side 16 of a first vane 10 of the other side 14 of a second vane 10 is as far as possible opposite each other.
  • FIG. 3 shows the longitudinal section through an annular support structure 30, which is part of a stator carrier or a housing of the axially flow-through turbomachine.
  • a circumferential groove 34 extending in the circumferential direction is provided.
  • the circumferential groove 34 has two mutually opposite side walls 36, 38, on which projections 40, 42 are provided for the positive retention of the guide vane 10.
  • guide vane 10 differs from that in the 1 and FIG.
  • each have a clamping screw 44 is screwed.
  • the clamping screw 44 may be formed for example as a grub screw or as an ordinary screw with a screw head.
  • the screw end of the clamping screw 44 is supported on the groove base 35 of the circumferential groove 34 and presses the arranged on the blade root 12 hook 27 to the projections 40, 42 of the circumferential groove 34, whereby the guide vane 10 in the radial direction of the axial flow-through turbomachine firmly biased.
  • FIG. 4 shows the cross section through FIG. 3 according to the section line IV-IV, wherein also in FIG. 4 identical features are provided with identical reference numerals.
  • the fitting 24 protrudes on the side 16 and is part of the blade root bottom 25.
  • recess 29 for receiving a fitting 24 of an adjacent vane 10 of a screwed therein clamping screw 44 can be seen.
  • the recess 29 is arranged according to the shaped piece 24 also on the blade root lower side 25.
  • FIG. 5 In the following description of the figures and in this figure, the reference numerals of the features associated with a first guide vane 10a are extended by the suffix a, the reference symbols of the features associated with a second guide vane 10b by the suffix b and the reference numerals of the features associated with a third vane 10c by the suffix c.
  • the first vane 10a is already positioned at its destination and with the help of two madenartiger clamping screws 44a in the circumferential groove 34 firmly clamped.
  • two second and third vanes 10b, 10c are already threaded in the circumferential groove 34.
  • the second vane 10b immediately adjacent thereto is displaced in the circumferential direction, ie in the direction of the arrow 52, until its platforms 18a, 18b abut one another.
  • the fitting 24a of the first vane 10a is disposed in the recess 29b of the second vane 10b, so that from the flow channel view, the platform 18b of the second vane 10b completely covers the molding 24a of the first vane 10a.
  • the surface 20b of the platform 18b covers the recess 29b when projected radially.
  • the second vane 10b is fastened with the aid of further clamping screws at the corresponding position.
  • the third vane 10c can be slid over the molding 24b of the second vane 10b, so that its clamping screws are also covered by the platform 18c of the third vane 10c.
  • a complete vane ring for an axial flow turbomachine can be mounted, in which case all vanes 10 are pressed with a defined bias to the projections 40, 42 of the holding 34.
  • the vanes 10 are also for receiving blade root reaction forces according to FIG. 6 further secured.
  • a through hole is provided, into which from the rear side of the support structure 30 of a further screw 54 can be screwed with a pin which engages in a corresponding recess on the underside of the blade root 12 of the guide vane 10.
  • the invention is not limited to those in 1, 2 and 3 Of course, it is possible, on one side 16 and then two eccentric fittings 24, each with a threaded hole 26 to provide.
  • the other side 14 of such a vane 10 then has one or two recesses 29 for receiving the corresponding fittings 24.
  • the invention provides a guide vane 10 and a guide vane assembly 50 for an axially flow-through turbomachine, in particular compressors, in which each vane 10 is held in a circumferential groove 34 via a fixed restraint.
  • a protruding molding 24 is provided with a threaded hole 26 on one side 16 of the blade root 12, in which a on the groove base 35 of the circumferential groove 34 supporting clamping screw 44 can be screwed.
  • a particular advantage of the invention is that in the vane ring both the fitting 24 and the clamping screw 44 screwed therein is completely covered by the platform 18 of a neighboring vane 10, so that the intermeshing thread of threaded hole 26 and clamping screw 44 in front of the flow channel the turbo-machine working medium flowing through the surface 20 of the platform 18 is shielded.
  • the shield prevents corrosion and the setting of the clamping screw 44, which ensures the disassembly of the guide vanes 10 from the circumferential groove 34 even after a long period of operation safely.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Aube ( 10 ) directrice pour une turbomachine à flux axial, comprenant une emplanture ( 12 ) d'aube ayant deux faces ( 14, 16 ) opposées l'une à l'autre, comprenant une plateforme ( 18 ) et au moins une lame ( 22 ) d'aube qui y est disposée,
    caractérisée en ce que
    l'emplanture ( 12 ) d'aube a, sur l'une des deux faces ( 16 ), au moins une pièce ( 24 ) conformée en saillie, dans laquelle est prévu au moins un trou ( 26 ) taraudé pour le blocage radial de l'aube ( 10 ) directrice dans une rainure ( 34 ) périphérique d'une structure ( 30 ) de support d'une turbomachine au moyen d'une vis ( 44 ) de blocage, qui y est vissée et qui s'appuie sur le fond ( 35 ) de la rainure ( 34 ) périphérique et dans laquelle l'emplanture ( 12 ) d'aube a, sur l'autre des deux faces ( 14 ), au moins un évidement ( 29 ) de réception d'au moins une pièce ( 24 ) conformée d'un aube ( 10 ) directrice voisine, y compris d'une vis ( 44 ) de blocage qui y est vissée.
  2. Aube ( 10 ) directrice suivant la revendication 1,
    dont l'emplanture ( 12 ) d'aube est en forme de marteau.
  3. Aube ( 10 ) directrice suivant la revendication 1 ou 2, comprenant deux pièces ( 24 ) conformées ayant respectivement un trou ( 26 ) taraudé ou comprenant deux trous ( 26 ) taraudés dans la une pièce ( 24 ) conformée.
  4. Aube ( 10 ) directrice suivant l'une des revendications 1 à 3, dans laquelle la pièce ( 24 ) conformée est formée au moins relativement proche du côté ( 25 ) inférieur de l'emplanture d'aube.
  5. Aube ( 10 ) directrice suivant l'une des revendications 1 à 4, qui a comme segment d'aube directrice deux ou plusieurs lames ( 22 ) d'aube.
  6. Aube ( 10 ) directrice suivant l'une des revendications 1 à 5, constituée sous la forme d'une aube directrice d'un compresseur à flux axial.
  7. Agencement ( 50 ) d'aubes directrices pour une turbomachine, de préférence pour un compresseur,
    comprenant une structure ( 30 ) annulaire de support sur la surface ( 32 ) latérale intérieure de laquelle est prévue une rainure ( 34 ) périphérique, dans laquelle viennent en étant rangées l'une derrière l'autre des aubes ( 10 ) directrices suivant l'une des revendications 1 à 5 maintenues par complémentarité de forme, chaque aube ( 10 ) directrice de ce genre étant bloquée dans la rainure ( 34 ) périphérique au moyen d'une vis ( 44 ) de blocage vissée dans le trou ( 26 ) taraudé de sa pièce ( 24 ) conformée et s'appuyant sur le fond ( 35 ) de la rainure ( 34 ) périphérique et la pièce ( 24 ) conformée, y compris la vis ( 44 ) de blocage, étant recouverte complètement par la plateforme ( 18 ) de l'aube ( 10 ) directrice, qui est voisine directement de l'aube ( 10 ) directrice concernée.
  8. Agencement ( 50 ) d'aubes directrices suivant la revendication 7,
    dans lequel au moins l'une des aubes ( 10 ) directrices comporte une sécurité pour l'absorption de force de réaction de l'emplanture d'aube dans la direction périphérique.
  9. Agencement ( 50 ) d'aubes directrices suivant l'une des revendications 7 ou 8,
    dans lequel la structure ( 30 ) de support peut être divisée par moitié.
EP09011070A 2009-08-28 2009-08-28 Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques Not-in-force EP2295724B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT09011070T ATE547591T1 (de) 2009-08-28 2009-08-28 Leitschaufel für eine axial durchströmbare turbomaschine und zugehörige leitschaufelanordnung
EP09011070A EP2295724B1 (fr) 2009-08-28 2009-08-28 Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques
US12/868,946 US8622708B2 (en) 2009-08-28 2010-08-26 Stator blade for a turbomachine which is exposable to axial throughflow, and also stator blade arrangement for it
JP2010190834A JP5073027B2 (ja) 2009-08-28 2010-08-27 軸方向に貫流可能なターボマシンのための静翼及び静翼構造
CN201010268815XA CN102003219B (zh) 2009-08-28 2010-08-27 可轴向通流的涡轮机的导向叶片及其导向叶片装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09011070A EP2295724B1 (fr) 2009-08-28 2009-08-28 Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques

Publications (2)

Publication Number Publication Date
EP2295724A1 EP2295724A1 (fr) 2011-03-16
EP2295724B1 true EP2295724B1 (fr) 2012-02-29

Family

ID=41395104

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09011070A Not-in-force EP2295724B1 (fr) 2009-08-28 2009-08-28 Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques

Country Status (5)

Country Link
US (1) US8622708B2 (fr)
EP (1) EP2295724B1 (fr)
JP (1) JP5073027B2 (fr)
CN (1) CN102003219B (fr)
AT (1) ATE547591T1 (fr)

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Also Published As

Publication number Publication date
US8622708B2 (en) 2014-01-07
ATE547591T1 (de) 2012-03-15
JP2011047406A (ja) 2011-03-10
US20110052397A1 (en) 2011-03-03
CN102003219B (zh) 2013-12-18
JP5073027B2 (ja) 2012-11-14
EP2295724A1 (fr) 2011-03-16
CN102003219A (zh) 2011-04-06

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