WO2014016431A1 - Schaufelkranz für eine turbomaschine - Google Patents

Schaufelkranz für eine turbomaschine Download PDF

Info

Publication number
WO2014016431A1
WO2014016431A1 PCT/EP2013/065885 EP2013065885W WO2014016431A1 WO 2014016431 A1 WO2014016431 A1 WO 2014016431A1 EP 2013065885 W EP2013065885 W EP 2013065885W WO 2014016431 A1 WO2014016431 A1 WO 2014016431A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
wedge
shaped clamping
groove
clamping element
Prior art date
Application number
PCT/EP2013/065885
Other languages
German (de)
English (en)
French (fr)
Inventor
Dimitri Zelmer
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US14/415,590 priority Critical patent/US20150176417A1/en
Priority to EP13745035.9A priority patent/EP2867478B1/de
Priority to RU2015106789A priority patent/RU2015106789A/ru
Priority to JP2015523574A priority patent/JP5934443B2/ja
Priority to CN201380039937.3A priority patent/CN104508248B/zh
Priority to KR20157001709A priority patent/KR20150037864A/ko
Publication of WO2014016431A1 publication Critical patent/WO2014016431A1/de

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
    • 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
    • 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
    • F01D5/32—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
    • 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
    • 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

Definitions

  • Blade ring for a turbomachine The invention relates to a blade ring for an axial
  • Turbomachine comprising a blade carrier with a number of - holding flanks - holding grooves for blades and a corresponding number of blades whose corresponding to the retaining grooves blade feet are inserted into the retaining grooves, wherein the blades on one
  • Slot bottom of the retaining groove facing the blade root underside have a recess whose bottom is at least partially inclined relative to the groove bottom of the retaining and in each of which a wedge-shaped clamping element for pressing the blade root is arranged on the support flanks.
  • a generic object is known for example from EP 1 892 380 AI.
  • two wedges are provided between a blade root bottom and the groove bottom of the retaining groove for each rotor blade.
  • the inclinations of the two wedges are opposite.
  • the front side is in each case a clamping screw screwed into the wedges, with the one hand, a radial prestressed positioning of the blade roots on corresponding support flanks of the retaining grooves is possible.
  • the screw is also used for
  • Shovel also done under a bias.
  • the assembly under bias leads to unfavorable wear and galling on the support flanks, which increases the risk of cracking.
  • assembly or disassembly proves to be difficult in the case of servicing the blade.
  • the object of the invention is therefore to provide a blade ring for a turbomachine, in which a bias-free and thus playful assembly of blades in the retaining grooves of a blade carrier is enabled and still a sufficiently large bias is present in operation, the material-damaging wear - for example also by rattling - reliably avoids.
  • the blade ring according to the invention for an axial turbomachine comprising a blade carrier with a number of holding slots for blades and having a corresponding number of blades, which are connected to the holding elements.
  • at least one of the blades preferably all blades, has or have a recess on its base end facing the groove bottom, at least partially obliquely against the groove bottom of the retaining groove, and in each of which a wedge-shaped clamping element for pressing the blade root is arranged on the support flanks, it is provided that a spring element is provided in each recess, the spring force acts along the retaining groove on the relevant wedge-shaped clamping element, wherein the recess of a first side wall and one of the first side wall opposite the second wall is limited, wherein the
  • Spring element is supported on the one hand on the first side wall and on the other hand on a blunt end of the wedge-shaped clamping element and means are provided, with which the wedge-shaped clamping element for the bias-free mounting of the blade in the holding temporarily can be moved to a position in which the blade root bias sitting in the holding groove.
  • the spring element presses the wedge-shaped clamping element in the direction of its pointed end, which acts in conjunction with the inclined bottom of the recess, a force in the radial direction (relative to the installation position in an axial turbomachine) on the blade root, the latter to the support flanks of the retaining grooves presses.
  • This is a play-free and preloaded attachment of the rotor blade in the holding effected.
  • the spring element is thus supported on the one hand on a first side wall of the recess and on the other hand on the blunt end of the wedge-shaped clamping element.
  • Clamping element is closer to the first side wall, as in the assembled state.
  • the spring element is only compressed for the duration of disassembly or assembly as it is intended in the assembled state.
  • the displacement of the clamping element to the first side wall towards relieving the strain of the rotor blade on the supporting flanks of the retaining acts.
  • the spring element is designed as a plate spring or cup spring package.
  • an opening is provided in the first side wall.
  • a cylindrical pin is arranged at the blunt end of the wedge-shaped clamping element, which extends through both the plate spring and the disc spring package and into the opening or through the opening in the side wall.
  • the cylindrical pin may for example be hammered into a hole arranged on the clamping element or glued there.
  • the cylinder pin has in conjunction with the opening arranged in the side wall the function of a guide of the spring element and at the same time a backup of the wedge-shaped clamping element, so that it can not jump out of the recess unintentionally during assembly.
  • the means comprises a threaded hole arranged in the second side wall into which a mounting screw for displacing the wedge-shaped clamping element to the first side wall can be screwed from the outside. Consequently, the spring element is first slipped over the cylindrical pin of the wedge-shaped clamping element before assembly of the blade, after which the cylindrical pin is subsequently inserted into the opening arranged in the first side wall. At the same time, the wedge-shaped clamping element is inserted into the underside of the blade arranged on the blade root.
  • a mounting screw with a correspondingly long threaded shaft is temporarily screwed in from the outside by means of the threaded hole present in the second side wall, with which the wedge-shaped tensioning element can be displaced in the direction of the first side wall.
  • the displacement must be so large that the wedge-shaped clamping element is completely sunk in the recess and so a game-afflicted assembly of the blade with clamping element is possible.
  • the assembly thus produced is inserted into the retaining groove. After the assembly and thus the blade has assumed the predetermined position in the retaining groove, the mounting screw screwed in the second side wall can be released again, whereby the wedge-shaped clamping element is pressed by the spring element in the direction of the second side wall.
  • the wedge-shaped clamping element Due to the inclined surface of the wedge-shaped clamping element and the corresponding bottom of the recess, the wedge-shaped clamping element is pressed into the narrowing space between groove bottom and bottom and comes on both surfaces - the groove bottom and the floor - to concern. This then results in the tension of the blade root on the support flanks of the retaining.
  • a bayonet connection may be provided instead of a threaded connection in the second side wall.
  • the blades are each secured by means of a between a Schaufelfußunterseite and one of the Schaufelfußunterseite opposite groove bottom of the retaining groove arranged sheet-like securing element against displacement along the retaining grooves by the ends of the sheet-like securing element rest laterally on the blade carrier.
  • a Schaufelfußunterseite and one of the Schaufelfußunterseite opposite groove bottom of the retaining groove arranged sheet-like securing element against displacement along the retaining grooves by the ends of the sheet-like securing element rest laterally on the blade carrier.
  • the wedge-shaped clamping element is at least partially hollow.
  • the blade attachment becomes more elastic in the prestressing direction and additionally enables friction damping.
  • the blade ring gear is a blade ring, so that the blade carrier is designed as a rotor disk or shaft and the blade as a rotor blade. Nevertheless, the blade ring is also suitable for mounting vanes. Particularly preferred is the use of the blade ring in a compressor of an axially flowed stationary gas turbine.
  • FIG. 2 shows the longitudinal section through a blade ring in the region of a holding groove with a blade inserted therein according to a first embodiment
  • FIG 3 shows the side view of the detail according to FIG 2,
  • FIG. 4 shows a further side view of a holding groove with a blade inserted therein
  • FIG 5 shows a longitudinal section analogous to FIG 2 for a second
  • Embodiment of a blade ring Embodiment of a blade ring.
  • FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
  • the gas turbine 10 has inside a rotatably mounted about an axis of rotation 12 rotor 14, which is also referred to as a turbine runner.
  • rotor 14 Along the rotor 14 follow one another an intake housing 16, a compressor 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrical mutually arranged burners 22, a turbine unit 24 and a turbine outlet housing 26.
  • the compressor 18 comprises an annularly shaped compressor duct with compressor stages and rotor blade rings 44 successively cascaded one after the other.
  • the rotor blades 14 are supported by rotor disks and face with their free-ending airfoil tips 29 an outer duct wall 42 of the compressor duct.
  • the compressor channel opens into a plenum 38 via a compressor outlet diffuser 36.
  • the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas channel 30 of the turbine unit 24. In the turbine unit 24 four successive turbine stages 32 are arranged.
  • a generator or a working machine (each not shown) is coupled.
  • the compressor 18 sucks ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it.
  • the compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22.
  • Fuel also passes into the combustion space 28 via the burners 22. There, the fuel is burned to a hot gas M with the addition of the compressed air.
  • the hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24.
  • the energy released during this time is absorbed by the rotor 14 and used on the one hand to drive the compressor 18 and on the other hand to drive a work machine or electric generator.
  • FIG. 2 shows a section through a rotor disk 19 of the rotor 14 of the gas turbine 10 in the region of a retaining groove 21 extending in the axial direction.
  • the rotor disk 19 thus represents a blade carrier 46 in which the retaining grooves 21 are distributed uniformly along its circumference and thereby engage in Axial direction of the gas turbine extend.
  • the retaining grooves 21 are designed in the form of a dovetail in cross-section (FIG. 3, FIG. 4) and thus each comprise two Supporting flanks 23 against which correspondingly designed contact surfaces 25 of a blade root 31 of the blades 27 abut.
  • the blades 27 are formed as blades.
  • a recess 37 is provided on a lower side 33 of the blade root 31, which faces a groove bottom 35 of the retaining groove 21, a recess 37 is provided.
  • the recess 37 is bounded by a first side wall 39 and a second side wall 41 opposite the first side wall 39.
  • the first side wall 39 is arranged on the inflow side and the second side wall 41 is arranged on the outflow side.
  • both a tab 45 both at the outside and also a tab 45 are bent inwards (FIGS. 3 and 4) at each end, whereby a displacement of the blade 27 inserted in the retaining groove 21 is blocked.
  • a wedge-shaped clamping element 47 is provided with a pointed end 49 and a blunt end 51.
  • a cylindrical pin 53 is arranged, on which in the illustrated embodiment, a total of four disc springs are threaded as a spring element 55.
  • the cylindrical pin 53 extends into an opening 57 arranged in the first side wall 39.
  • the bottom 59 of the recess 37 is inclined relative to the groove base 35 of the retaining groove 21, corresponding to the inclination of the upper surface 61 of the wedge-shaped clamping element 47 shown in FIG.
  • a threaded hole 63 is provided in the second side wall 41, which - as well as the opening 57 - extends parallel to the retaining groove 21.
  • a mounting screw 65 required for mounting the blade 27 can be screwed into the threaded hole 63, with the aid of which the wedge-shaped clamping element 47 in FIG. 2 is pushed so far to the left. can be pushed that its blunt end 51 is positioned comparatively close to the first side wall 39. This allows the wedge-shaped clamping element 47 completely sink in the recess 37.
  • the assembly of the blade 27 in the retaining groove 21 then takes place as follows: First, the prefabricated sheet-like securing element 43 is inserted into the retaining groove.
  • the sheet-like securing element 43 extends over the entire length of the retaining groove 21, wherein already two of the tabs 45 are already bent transversely to its longitudinal extent on the inflow or outflow side.
  • the outwardly bent tab 45 serves as a stop during the insertion of the blade 27 into the retaining groove 21.
  • At the other end of the sheet-like securing element 43 only one of the two tabs 45 is initially bent in the radial direction to the machine axis.
  • the spring member 55 is placed on the cylindrical pin 53 of the wedge-shaped clamping member 47 and inserted together into the opening 57 and the recess 37.
  • the cylinder pin 53 then engages in the opening 57 designed as a slot.
  • the mounting screw 65 is screwed into the threaded hole 63, so deep that the wedge-shaped clamping member 47 is pressed to the opposite side, ie in the direction of the first side wall 39 and so far, until the wedge base 67 is located within the recess.
  • a bias-free insertion of the blade 27 can be ensured.
  • the blade 27 is inserted with the prestressed wedge-shaped clamping element 47 in the retaining groove 21.
  • the mounting screw 65 is released and removed from the assembly.
  • the wedge-shaped clamping element 47 is relieved of the force of the mounting screw and can press the blade 27 in the retaining groove 21 against the support flanks 23 and thus bias by the action of the axial forces of the spring element 55.
  • the hitherto not bent tab 45 of the sheet-like securing element 43 bent in the radial direction away from the machine axis, which then secures the blade 27 against emigration from the retaining groove 21.
  • the wedge-shaped clamping element 47 may be at least partially hollow.
  • the cavity 69 causes a resilient bias and thus brings in addition a friction damping with it.
  • the invention relates to a blade ring 44 for an axial turbomachine, comprising a blade carrier 46 with a number of retaining grooves 21 and a corresponding number of blades 27, the blade roots 31 are inserted into the retaining grooves 21, wherein the blades 27 at its one groove bottom 35 of Garut 21 facing bottom 33 each have a recess 37, the bottom 59 is at least partially opposite the groove bottom 35 of the retaining groove 21 is inclined and in each of which a wedge-shaped clamping element 47 is arranged for pressing the blade root 31 to the support flanks 23.
  • a blade carrier 46 with a number of retaining grooves 21 and a corresponding number of blades 27, the blade roots 31 are inserted into the retaining grooves 21, wherein the blades 27 at its one groove bottom 35 of Garut 21 facing bottom 33 each have a recess 37, the bottom 59 is at least partially opposite the groove bottom 35 of the retaining groove 21 is inclined and in each of which a wedge-shaped clamping element 47 is arranged for pressing the blade root 31
  • Screw connection can be used in operation, it is provided that in each recess 37, a spring element 55 is provided, the spring force along the retaining groove 21 acts on the relevant wedge-shaped clamping element 47 and that means are provided with which the wedge-shaped clamping element 47 for the bias-free mounting of the blade 27 in the retaining groove 21 can be temporarily moved to a position in which the blade root 31 sits without bias in the retaining groove 21.

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)
PCT/EP2013/065885 2012-07-27 2013-07-29 Schaufelkranz für eine turbomaschine WO2014016431A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US14/415,590 US20150176417A1 (en) 2012-07-27 2013-07-29 Blade ring for a turbomachine
EP13745035.9A EP2867478B1 (de) 2012-07-27 2013-07-29 Schaufelkranz für eine turbomaschine
RU2015106789A RU2015106789A (ru) 2012-07-27 2013-07-29 Лопаточный венец для турбомашины
JP2015523574A JP5934443B2 (ja) 2012-07-27 2013-07-29 ターボ機械のための翼リング
CN201380039937.3A CN104508248B (zh) 2012-07-27 2013-07-29 用于涡轮机的叶片环和用于固定式燃气轮机的压缩机
KR20157001709A KR20150037864A (ko) 2012-07-27 2013-07-29 터보 기계용 블레이드 링

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012213227.9 2012-07-27
DE102012213227A DE102012213227B3 (de) 2012-07-27 2012-07-27 Schaufelkranz für eine Turbomaschine

Publications (1)

Publication Number Publication Date
WO2014016431A1 true WO2014016431A1 (de) 2014-01-30

Family

ID=48916028

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2013/065885 WO2014016431A1 (de) 2012-07-27 2013-07-29 Schaufelkranz für eine turbomaschine

Country Status (8)

Country Link
US (1) US20150176417A1 (zh)
EP (1) EP2867478B1 (zh)
JP (1) JP5934443B2 (zh)
KR (1) KR20150037864A (zh)
CN (1) CN104508248B (zh)
DE (1) DE102012213227B3 (zh)
RU (1) RU2015106789A (zh)
WO (1) WO2014016431A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439858A (zh) * 2019-09-09 2019-11-12 上海电气燃气轮机有限公司 一种具有减振效果的叶片锁紧结构

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2711504A1 (de) * 2012-09-19 2014-03-26 Siemens Aktiengesellschaft Vorrichtung zum Überbrücken eines Spiels
US9739160B2 (en) 2013-10-18 2017-08-22 Siemens Aktiengesellschaft Adjustable blade root spring for turbine blade fixation in turbomachinery
US11603794B2 (en) 2015-12-30 2023-03-14 Leonard Morgensen Andersen Method and apparatus for increasing useful energy/thrust of a gas turbine engine by one or more rotating fluid moving (agitator) pieces due to formation of a defined steam region
US10208709B2 (en) * 2016-04-05 2019-02-19 United Technologies Corporation Fan blade removal feature for a gas turbine engine
US10465537B2 (en) * 2016-05-27 2019-11-05 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
IT201600130088A1 (it) 2016-12-22 2018-06-22 Nuovo Pignone Tecnologie Srl Pala di turbina e set di fissaggio
FR3084162B1 (fr) * 2018-07-23 2020-10-02 Safran Aircraft Engines Montage d'essai, et machine de test en fatigue vibratoire.
CN109113798A (zh) * 2018-08-27 2019-01-01 广东惠州天然气发电有限公司 一种新型燃气轮机静叶环
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
CN111946642B (zh) * 2020-08-17 2021-06-29 江苏恒康机电有限公司 一种方便拆卸的不锈钢风机
US11834965B2 (en) 2020-08-25 2023-12-05 General Electric Company Blade dovetail and retention apparatus
CN112483464B (zh) * 2020-10-27 2023-03-14 中国船舶重工集团公司第七0三研究所 一种周向槽型燃气轮机压气机叶片锁紧装置
FR3121954B1 (fr) * 2021-04-20 2023-07-14 Safran Aircraft Engines Dispositif de calage d’un pied d’aube dans une alveole d’un disque de rotor de turbomachine
FR3140120A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Roue de turbine comprenant un dispositif de retenue axiale de pieds d’aube dans les alvéoles d’un disque
US12065948B1 (en) * 2023-06-09 2024-08-20 Rtx Corporation Blade spacer

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5236309A (en) * 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
JPH11182494A (ja) * 1997-12-22 1999-07-06 Toshiba Corp 軸流圧縮機
EP1253293A2 (de) * 2001-04-26 2002-10-30 ALSTOM (Switzerland) Ltd Befestigung einer Laufschaufel am Rotor einer Turbomaschine
EP1703078A1 (de) 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Biegevorrichtung und Verfahren zum Biegen eines Sicherungsbleches in einem Verdichter oder einer Turbine
EP1892380A1 (de) 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Schaufelbefestigung einer Turbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5738603A (en) * 1980-08-15 1982-03-03 Hitachi Ltd Fixing construction of rotary machine blade
JPS57151005A (en) * 1981-03-13 1982-09-18 Hitachi Ltd Fall-off stopper of moving blade
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
JPH0988506A (ja) * 1995-09-21 1997-03-31 Ngk Insulators Ltd ハイブリッド型ガスタービン動翼用のブレード及びタービンディスク並びにこれらからなるハイブリッド型ガスタービン動翼
EP1507958A1 (de) * 2002-05-24 2005-02-23 ABB Turbo Systems AG Axialsicherung fuer laufschaufeln
US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5236309A (en) * 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
JPH11182494A (ja) * 1997-12-22 1999-07-06 Toshiba Corp 軸流圧縮機
EP1253293A2 (de) * 2001-04-26 2002-10-30 ALSTOM (Switzerland) Ltd Befestigung einer Laufschaufel am Rotor einer Turbomaschine
EP1703078A1 (de) 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Biegevorrichtung und Verfahren zum Biegen eines Sicherungsbleches in einem Verdichter oder einer Turbine
EP1892380A1 (de) 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Schaufelbefestigung einer Turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439858A (zh) * 2019-09-09 2019-11-12 上海电气燃气轮机有限公司 一种具有减振效果的叶片锁紧结构

Also Published As

Publication number Publication date
EP2867478B1 (de) 2016-09-21
CN104508248A (zh) 2015-04-08
US20150176417A1 (en) 2015-06-25
CN104508248B (zh) 2016-08-17
KR20150037864A (ko) 2015-04-08
EP2867478A1 (de) 2015-05-06
JP2015524531A (ja) 2015-08-24
DE102012213227B3 (de) 2013-09-26
JP5934443B2 (ja) 2016-06-15
RU2015106789A (ru) 2016-09-20

Similar Documents

Publication Publication Date Title
EP2867478B1 (de) Schaufelkranz für eine turbomaschine
DE69604757T2 (de) Dichtungs- und Rückhaltesegmente für die Schaufeln einer axialen Turbomaschine
DE60220492T2 (de) Verbindungs- und Verriegelungssystem für die Laufschaufeln eines Axialverdichters
DE69206111T2 (de) Herstellungsverfahren von Turbinen- oder Verdichtershaufeln.
EP0355312B1 (de) Axialdurchströmte Turbine mit radial-axialer erster Stufe
EP2242909B1 (de) Turbomaschinenrotor, laufschaufel für einen solchen turbomaschinenrotor sowie entsprechendes montageverfahren
WO2008122492A1 (de) Anordnung zur axialsicherung an laufschaufeln in einem rotor sowie gasturbine mit einer solchen anordnung
EP1584793A2 (de) Turbinenschaufelarretiervorrichtung
EP2173972B1 (de) Rotor für eine axial durchströmbare strömungsmaschine
WO2000009861A2 (de) Stützvorrichtung für triebwerkschaufeln
EP3078808A1 (de) Laufschaufelreihe für eine strömungsmaschine
DE3601911C2 (de) Schaufelreihe
WO2010040643A1 (de) Turbolader mit befestigungselementen zum befestigen von schaufellagerringen einer variablen turbinengeometrie vtg
DE69919459T2 (de) Befestigung eines Schaufelblattes an einem Rotor
EP2149677B1 (de) Befestigungsanordnung zur Befestigung von einer Laufschaufel an einem Rotor einer Turbomaschine
EP1733124A1 (de) Strömungsmaschine und rotor für eine strömungsmaschine
DE3424925C1 (de) Turbomaschine mit wenigstens einem radial durchströmten Laufrad
DE2532554C2 (de) Verdichterstator
EP0712995A1 (de) Beschaufelter Rotor
EP3347573B1 (de) Dummy-radscheibe und verfahren zum bearbeiten von schaufeln
EP1657404A1 (de) Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
EP1697618B1 (de) Leitschaufelträger mit mehreren leitschaufeln und verfahren zum montieren von leitschaufeln an einen leitschaufelträger
EP0707150B1 (de) Verdichter
DE102008048261A1 (de) Axialturbomaschinenrotor mit einem Schaufelschloss und Verfahren zum Herstellen desselben
DE2257076A1 (de) Trommellaeufer fuer axialverdichter und verfahren zur herstellung solcher verdichter

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13745035

Country of ref document: EP

Kind code of ref document: A1

REEP Request for entry into the european phase

Ref document number: 2013745035

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2013745035

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 14415590

Country of ref document: US

ENP Entry into the national phase

Ref document number: 20157001709

Country of ref document: KR

Kind code of ref document: A

ENP Entry into the national phase

Ref document number: 2015523574

Country of ref document: JP

Kind code of ref document: A

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2015106789

Country of ref document: RU

Kind code of ref document: A