EP2569514A1 - Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement - Google Patents

Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement

Info

Publication number
EP2569514A1
EP2569514A1 EP11723334A EP11723334A EP2569514A1 EP 2569514 A1 EP2569514 A1 EP 2569514A1 EP 11723334 A EP11723334 A EP 11723334A EP 11723334 A EP11723334 A EP 11723334A EP 2569514 A1 EP2569514 A1 EP 2569514A1
Authority
EP
European Patent Office
Prior art keywords
groove
blade
retaining
fastening arrangement
grooves
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.)
Granted
Application number
EP11723334A
Other languages
German (de)
English (en)
Other versions
EP2569514B1 (fr
Inventor
Patrick Bullinger
Marco Link
Nicolas Savilius
Uwe Sieber
Hubertus Michael Wigger
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 EP11723334.6A priority Critical patent/EP2569514B1/fr
Publication of EP2569514A1 publication Critical patent/EP2569514A1/fr
Application granted granted Critical
Publication of EP2569514B1 publication Critical patent/EP2569514B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/94—Mounting on supporting structures or systems on a movable wheeled structure
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a fastening arrangement according to the preamble of claim 1. Furthermore, the invention relates to a method for producing such a Befest Trentsanord- tion.
  • the present invention relates to the mechanical connection of stationary or rotating blades of the flow path of an axial-flow turbomachine. These are vanes which are fastened to the housing or to a corresponding guide blade carrier or to rotor blades which are arranged on the rotor of the turbomachine.
  • vanes of a blade ring are mounted in a circumferentially extending groove.
  • rotor blades are inserted into a respectively associated ⁇ impaired, axially extending groove.
  • a resilient Be ⁇ fastening of moving blades in a circumferential groove of the turbine rotor is known from US 6,761,538 B2, which are pressed by means of a both lekssgeschlitz ⁇ th and quergeschlitzten tubular spring element on the known hammer-shaped interlocking.
  • US Pat. No. 2,753,149 discloses a further type of fastening of compressor rotor blades to a rotor disk.
  • a double-headed bolt connection is provided between the groove base of the axial groove and the blade root underside. Nevertheless, a slight movement of the
  • the object relating to the fastening arrangement object is achieved by one which is designed according to the features of the on ⁇ claim 1.
  • the manufacturing method of the ge ⁇ addressed object is solved both by a method according to claim 11 and by a method according to claim. 13
  • the mounting arrangement according to the invention for blades of axial throughflow turbomachine comprises a blade carrier having a central axis and a concentric jacket surface, in which along the circumference distributed holding grooves with an axial extension are provided and blades whose blade roots are inserted in these retaining slots where ⁇ at each Holding groove has a groove bottom, which is opposite to a lower ⁇ side of the respective blade root, and depending Weil ⁇ a resilient, arranged between each groove base and the underside of this opposite clamping element, wel ⁇ Ches is biased on the respective bottom and the respective groove base, wherein in the undersides of the blades are each provided with a groove, in which the relevant clamping element surface, that is applied along its longitudinal ⁇ extension.
  • a suitable groove for guiding the clamping element is arranged in the groove base.
  • the invention is based on the finding that an improved contact pressure of the blade in the retaining groove can be achieved if at least on the blade root underside a channel is provided, in which the clamping element rests positively over its entire length. For a over the length of the undercut Verhakungs Kunststoffs gleichmä ⁇ ssige contact pressure of the blade is achieved, which is not the case with the closest prior art. At the same time an increased process quality is achieved during assembly of the blade in the retaining, since an individual adjustment of blades for pressing and fixing is not required.
  • gutters are provided both in the blade root underside and in the groove bottom, these gutters can be produced particularly easily with the aid of the following methods.
  • the blades and the blade carrier are made including all retaining grooves. Then the insertion of a blade takes place in the associated retaining groove. At ⁇ closing the blade is temporarily xed fi in the holding. This is followed by the pairs, ie simultaneous Her provide ⁇ of the two opposite grooves by a single drilling operation.
  • the bore extends along the underside-groove bottom plane and cuts in half in the Schau ⁇ felfuß and in the blade carrier. Subsequently, the insertion of the clamping element takes place in the bore. It is preferably provided that the temporary fixation is released again before or after insertion of the tensioning element.
  • both channels are produced in only one drilling operation, it can be assumed that their position is very high in accuracy with respect to both channels, which results in a particularly reliable seating of the spring element in FIG causes the corresponding grooves. This has the consequence that with predetermined clamping forces the blade can be pressed in its retaining groove to the undercuts, in particular over the entire length of the undercuts.
  • a second method according to the invention comprises the following steps: first, the blade carrier is produced, but without the associated retaining grooves. Subsequently, a drilling of the blade carrier, wherein the holes are each placed in such a way that later in the manufacture of one of the
  • This production process has the advantage that the arranged in the shop ⁇ felabo channel can be preliminarily prepared relatively easily and without any special effort, in particular if the longitudinal directions of the channel and hold ⁇ are nut different.
  • both grooves extend parallel to the longitudinal extension of the retaining groove.
  • the grooves extend obliquely to the longitudinal extension of the retaining groove.
  • the last-mentioned variant has the particular advantage that due to the mutually inclined displacement direction of blades (along the retaining groove) and clamping element (along the channel) a positive connection between the blade root and groove by means of Clamping element is brought about, which also serves as axial securing against displacement of the blades along the retaining groove.
  • the clamping element is at the same time the Axialverschiebungs Anlagensfunktion.
  • the shearing forces acting on the clamping elements by the blades prevent the latter from being released from the channels.
  • the Lekserstre- ckung of the retaining grooves relative to the central axis is inclined and the grooves extend parallel to the central axis.
  • the groove-side channel opens into at least one of the two end faces of the
  • Blade carrier which adjoin the lateral surface.
  • each blade is designed as a blade with axial feet and the blade carrier as a rotor element, wherein at least a portion of the radially outer shell ⁇ surface of the rotor element forms the respective lateral surface of the blade carrier with the corresponding retaining grooves.
  • each blade is formed as a vane with axial feet and the blade carrier as an annular vane support member, wherein at least a portion of the radially inner surface of the vane support forms the respective lateral surface of the blade carrier.
  • FIG. 2 shows a perspective view of a portion of the fastening arrangement according to the invention with a holding groove and a blade seated therein
  • FIG. 4 shows a blade according to a second embodiment
  • FIG. 5 shows a blade carrier according to a second embodiment, suitable for receiving the blade shown in FIG.
  • FIG. 1 shows, in a perspective view, a blade 10 designed as a compressor blade.
  • the compressor blade comprises an airfoil 12 which is only partially shown, to which a blade root 14 adjoins.
  • the blade ⁇ foot 14 has an outer contour which swallowtail mig is adapted to be held in a blade carrier in FIG 1, not shown, form-fitting manner.
  • the Schaufeififuß 14 has an underside 16, in which a
  • the channel 18 is arranged.
  • the channel 18 will also be referred to below as the bottom channel 18.
  • the lower side groove 18 extends over the entire longitudinal extent of the Blade root 14, so that it ends at the front side, dovetail-shaped contoured end surfaces of the blade root 14.
  • the channel 18 is configured in a U-shape, that is to say in the shape of a groove with a semicircular basic contour, and is formed so deep that it can almost, but not completely, receive a clamping element, not shown, in the form of a tensioning pin. This makes it possible, the blade 10 by means of the clamping pin biased in a holding groove to tes ⁇ term, which has no groove-side groove.
  • FIG. 2 shows a perspective representation of a blade carrier 20 of a fastening arrangement 8.
  • a retaining groove 22 is provided, which has a contour corresponding to the blade root 14 of the blade 10.
  • the contour of the retaining groove 22 is not blade-footed but modified.
  • Nut ⁇ reason 24 of the retaining groove 22 is a groove-side groove 26 is provided.
  • the blade 10 shown in FIG 2 under failed ⁇ det thereby from the position shown in FIG 1 the blade 10 is that the channel 18 is not U-shaped, but merely configured semi-circular.
  • the openings of both channels 18, 26 face each other. Viewed in cross section, form both channels 18, 26 an approximately circular Kon ⁇ structure . They are also along their longitudinal extent always opposite each other and are thus suitable for receiving a clamping ⁇ element 28, which is usually designed as a dowel pin.
  • FIG 3 It should be noted that the clamping element 28 is shown only schematically in FIG 3, by the cross section is shown rotated in 90 °. According to an alternative fastening arrangement 8, whose
  • Shovel carrier 20 in FIG 5 and the blade root 14 are shown schematically in Figure 4, the grooves 18, 26 extend transversely, ie obliquely to the longitudinal extent of the holding 22. This has the consequence that the bottom channel 18 now not frontally opens in the blade root 14 but on the wing side (FIG. 4). Further, the groove-side groove 26 opens now not in the contour of the retaining groove 22, but outside of which as a bore opening. This is Darge provides ⁇ in FIG. 5 There, the mouth 34 of the nutground remedy groove 26 outside the mouth 38 of the retaining groove 22.
  • a mounting assembly 8 for blades 10 of axial throughflow turbomachines, preferably compressors is specified with the invention
  • a blade ⁇ carrier 20 are provided with a circumferential surface, in which along the environmental distributed fangs retaining grooves 22 and comprising in which Blades 10 are used, wherein between each groove bottom 24 and the opposite bottom 16 of the respective blade root 14, a resilient clamping element 28 is provided, which is biased on the respective bottom 16 and the respective groove bottom 24, where ⁇ both in the groove base 24 and in the bottom 16 each have a groove 18, 26 is provided, in which the clamping element 28 abuts.

Landscapes

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

Abstract

La présente invention concerne un agencement de fixation (8) pour des aubes (10) de turbomachines à circulation axiale, de préférence des compresseurs, comprenant un support d'aubes (20) avec une surface d'enveloppe, dans laquelle sont réalisées des rainures de retenue (22) réparties sur la circonférence et dans lesquelles sont insérées des aubes (10). Entre chaque fond de rainure (24) et le côté inférieur (16) opposé à celui-ci de la base d'aube concernée (14), est disposé un élément de montage par serrage à effet élastique (28) qui s'appuie sur le côté inférieur concerné (16) et sur le fond de rainure concerné (24) avec précontrainte, une rigole (18, 26) étant pratiquée respectivement dans le fond de rainure (24) et dans le côté inférieur (16), l'élément de serrage (28) s'appliquant à l'intérieur desdites rigoles.
EP11723334.6A 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication Not-in-force EP2569514B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11723334.6A EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10005079A EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
PCT/EP2011/057628 WO2011141514A1 (fr) 2010-05-14 2011-05-11 Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement
EP11723334.6A EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Publications (2)

Publication Number Publication Date
EP2569514A1 true EP2569514A1 (fr) 2013-03-20
EP2569514B1 EP2569514B1 (fr) 2014-04-02

Family

ID=43017149

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10005079A Withdrawn EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP11723334.6A Not-in-force EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10005079A Withdrawn EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Country Status (6)

Country Link
US (1) US20130101422A1 (fr)
EP (2) EP2386721A1 (fr)
JP (1) JP5596223B2 (fr)
CN (1) CN102906375A (fr)
RU (1) RU2012154199A (fr)
WO (1) WO2011141514A1 (fr)

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CN110397625A (zh) * 2019-08-15 2019-11-01 上海电气燃气轮机有限公司 一种新型叶片锁紧装置
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KR102355521B1 (ko) * 2020-08-19 2022-01-24 두산중공업 주식회사 압축기 블레이드의 조립구조와 이를 포함하는 가스 터빈 및 압축기 블레이드의 조립방법
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RU2012154199A (ru) 2014-06-20
EP2569514B1 (fr) 2014-04-02
JP2013526667A (ja) 2013-06-24
US20130101422A1 (en) 2013-04-25
WO2011141514A1 (fr) 2011-11-17
CN102906375A (zh) 2013-01-30
EP2386721A1 (fr) 2011-11-16
JP5596223B2 (ja) 2014-09-24

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