EP3115554A1 - Système d'aube avec des éléments de support élastiques pour une turbomachine thermique - Google Patents

Système d'aube avec des éléments de support élastiques pour une turbomachine thermique Download PDF

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Publication number
EP3115554A1
EP3115554A1 EP15176056.8A EP15176056A EP3115554A1 EP 3115554 A1 EP3115554 A1 EP 3115554A1 EP 15176056 A EP15176056 A EP 15176056A EP 3115554 A1 EP3115554 A1 EP 3115554A1
Authority
EP
European Patent Office
Prior art keywords
groove
blade
spacers
blade assembly
spacer
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Withdrawn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
EP15176056.8A
Other languages
German (de)
English (en)
Inventor
Dimitri Zelmer
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 EP15176056.8A priority Critical patent/EP3115554A1/fr
Priority to PCT/EP2016/065271 priority patent/WO2017005592A1/fr
Priority to CN201680040648.9A priority patent/CN107835888A/zh
Priority to EP16733558.7A priority patent/EP3289184B1/fr
Priority to US15/741,907 priority patent/US10487673B2/en
Publication of EP3115554A1 publication Critical patent/EP3115554A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a blade assembly for a turbomachine with a blade carrier, on the outer peripheral surface of which a circumferential T-groove is formed, a blade ring comprising a plurality of blades and spacers, which are alternately inserted into the T-slot, and supporting elements, the on the other hand supported between the blades and spacers on the one hand and a bottom of the T-groove on the other hand, that the blades and spacers are pressed radially outward. Furthermore, the invention relates to a method for forming a blade assembly according to the invention.
  • a turbomachine for example a steam turbine or a gas turbine, comprises a turbine housing and a turbine shaft, which passes through the turbine housing and is connected to the drive shaft of a working machine, for example a generator.
  • a working machine for example a generator.
  • On the turbine shaft one or more blade assemblies are rotatably held, on each of which blades are held in the form of a blade ring.
  • a circumferential force exerted on the blades by the working fluid for example water vapor or hot gas, causes the turbine shaft to rotate, thereby driving the work machine.
  • a blade carrier When assembling a blade assembly for a turbomachine, a blade carrier is provided with a circumferential blade ring.
  • blades and spacers are alternately inserted into a circumferential along the outer peripheral surface of the blade carrier T-groove and therein in the circumferential direction shifted.
  • the blades and spacers in the circumferential T-slot must be displaced. This is accomplished by making the blade roots and spacers with clearance relative to the circumferential T-slot, particularly with radial play.
  • the spacers and blade feet When mounting the blade ring on the blade carrier, the spacers and blade feet must be biased radially outward to minimize between the spacers, the blade roots and the T-groove forming column, even at low speeds of the turbine shaft to ensure a tight fit, especially the blades and, if necessary, the tips of the blades can be reworked with high precision even when mounted.
  • the support elements - as in the EP 2 562 356 A1 proposed - also be dimensioned and designed so that they hold each other at least in the circumferential direction in position.
  • the support elements are made with a certain excess length in the circumferential direction, so that the last to be used in the T-slot support member must be shortened accordingly to fit in the remaining gap, which is associated with additional effort.
  • a fundamental difficulty in the handling of such support elements is that the gap between the undersides of the spacers and blades on the one hand and the bottom of the T-groove, on the other hand, is hardly accessible to position the support members therein.
  • the present invention provides a blade assembly of the type mentioned, in which each spacer a separate support member assigned and releasably held on this, in particular is fixed by clamping.
  • the invention is based on the idea to releasably fix the support elements on the associated spacers by clamping. This attachment process can be done outside the T-slot. Only then the spacer provided with the support element is inserted into the T-groove and moved in the circumferential direction to its destination, so that the support element automatically reaches the desired position together with the associated spacer. As a result, the assembly is easy.
  • the support elements are designed and arranged as elastic spring plates such that the associated spacers are biased radially outward in the T-slot.
  • the spacers can be pressed inwardly against the outwardly directed elastic restoring force of the spring plates to produce the radial clearance required for the displacement.
  • At least one radially outwardly projecting projection is preferably formed on the support elements, which engages with the respective associated spacer in order to releasably secure the support elements to the associated spacers.
  • corresponding recesses may be formed, in which engage the projections of the support members in particular by clamping.
  • a clamping engagement in a recess represents a secure as well as easily releasable attachment.
  • the recesses are arranged axially in the middle of the spacers, in particular having an axial width which is at least 30% and in particular at least 50% of the axial width of the spacers.
  • the projections of the support elements in particular have an axial width which corresponds to the axial width of the recesses.
  • the width of the projections may be selected such that the support elements are axially positioned in the recesses via the projections.
  • two spaced apart in the circumferential direction of the T-groove projections are formed on the support elements. Two projections allow a particularly stable connection between a support element and the associated spacer.
  • the two projections are each arranged on the support elements such that the associated spacers are clamped between the projections. This type of engagement is particularly easy to handle when mounting the blade assembly.
  • the two corresponding recesses are formed on opposite in the circumferential direction of the T-slot end faces of the spacer.
  • the two recesses are open in the circumferential direction of the T-slot.
  • Such open recesses are easy to manufacture.
  • such recesses arranged have a maximum distance, which ensures a high resistance to rotation of the support member relative to the spacer.
  • In the circumferential direction of the T-groove open recesses may also facilitate the handling of the support elements when connecting to the respective associated spacers.
  • the projections of the support elements may be received in the corresponding recesses of the associated spacers such that the end faces of the spacers come into contact with adjacent blades.
  • the recesses are formed such that the projections are completely received in the corresponding recesses so that they do not protrude in the circumferential direction of the T-groove from the end faces. In this way, the blades and spacers can form a gap-free blade ring.
  • a particular wave-shaped spring area is formed between the projections such that the spring area comes adjacent to the projections with the bottom of the T-slot and in a central region with the associated spacer in abutment.
  • a wave-shaped spring portion can apply the outward elastic force required for the radial bias of the spacers, and is easy to manufacture and handle.
  • the support elements are spaced from each other in the circumferential direction of the T-groove. This ensures that occurring in the production of the support elements Manufacturing inaccuracies do not require manual post-processing during assembly.
  • opposite end regions of the support elements project from the assigned spacers in such a way that they engage beneath adjacent blades.
  • Such end regions may for example be formed as tongues which project into the intermediate space between an adjacent blade and the bottom of the T-slot.
  • the protruding end portions are formed so as to bias the adjacent blades radially outward, each coming into abutment with the adjacent blade and the bottom of the T-slot. As a result, the adjacent blade is pressed outward and fixed in the radial direction.
  • At least one bead is formed at each end region, which comes into contact with the bottom of the T-slot and is positioned in particular in an axially central region of the end region.
  • the bead may have an axial width which is at least 30% and in particular at least 50% of the axial width of the end region. Beading can be easily and inexpensively introduced, for example, by embossing in the end regions of the support elements.
  • the central arrangement of the beads ensures that the underrun blades are pressed evenly radially outward with respect to the axial direction. In this case, wider beads on a greater elasticity, which facilitates the handling.
  • the arrangement of the support elements takes place relative to the spacers outside the T-slot, which is associated with easy handling, in particular without special tools.
  • the blade assembly according to the invention can be used in particular in thermal turbomachinery, which are axially flowed through.
  • thermal turbomachines can be understood both as compressors and in turbines.
  • the turbine can be configured as a steam turbine or as a turbine unit of a gas turbine.
  • FIGS. 1 to 4 show a rotor blade assembly 1 for a turbomachine according to an embodiment of the present invention.
  • the blade assembly 1 comprises a blade carrier 2, on whose outer peripheral surface 3 a circumferential T-groove 4 is formed, and a blade ring 5.
  • the blade ring 5 has a plurality of blades 6 and spacers 8, wherein blade roots 7 of the blades 6 alternately with the Spacers 8 are inserted into the T-groove 4.
  • the blade assembly 1 comprises support members 9 which are supported between the blades 6 and the spacers 8 on the one hand and a bottom 10 of the T-groove 4 on the other hand so that the blades 6 and the spacers 8 are pressed radially outward against shoulder surfaces of the T-slot ,
  • the support members 9 are formed as elastic spring plates and arranged in the circumferential direction of the T-groove 4 spaced from each other.
  • Each spacer 8 is a separate Assigned supporting element 9 and held releasably on this, namely fixed by clamping.
  • each case two radially outwardly projecting projections 11 are formed on the support elements 9, which engage with the respective associated spacer 8 in order to secure the support elements 9 to the associated spacers 8.
  • the spacers 2 to the projections 11 of the associated support elements 9 corresponding recesses, which are formed as open recesses in the circumferential side faces of the spacers 9.
  • the recesses have a depth in the circumferential direction such that the projections 11 are completely received in the recesses 12 and the spacer 8 is clamped between the projections 11.
  • the recesses 12 are arranged axially centrally on the spacers 8 and have an axial width which is about 50% of the axial width of the spacers 8.
  • the projections 11 of the support elements 9 have an axial width corresponding to the axial width of the recesses 12, so that it is ensured that the support elements 9 engage the spacers 2 approximately axially centrally and are positioned.
  • a wave-shaped spring portion 13 is formed adjacent to the two projections 11 each troughs 13 a, which come into contact with the bottom 10 of the T-groove 4, and between the troughs 13 a a wave crest 13 b, with the associated Spacer 8 comes into contact, has.
  • the support elements 9 also have in the circumferential direction of the T-groove 4 opposite present tongue-shaped end portions 14 which protrude from the associated spacers 8 in the circumferential direction of the T-groove 4 such that they engage under the adjacent blades 6.
  • Each projecting end portion is formed to radially outwardly bias the adjacent blade 6 and press against shoulder surfaces of the T-groove 4, engaging the adjacent blade 6 and the bottom 10 of the T-groove 4.
  • a bead 15 formed at each protruding end portion 14 projecting radially inwardly from the end portion 14 abuts against the bottom 10 of the T-groove 4, while the free end of the protruding end portion abuts against the adjacent blade 6.
  • the bead 15 is positioned in an axially central region of the end portion 14 and has an axial width that is about 50% of the axial width of the end portion 14.
  • a blade 6 is inserted into the T-groove 4 and moved in the circumferential direction of the T-groove 4 to its destination. Then, a support member 9 is fixed by clamping on a spacer 8. For this purpose, the support member 9 is attached from below onto the spacer 8, so that the two projections 11 of the support member 9 come into clamping engagement with the corresponding recesses 12 of the spacer 8.
  • the spacer 8 with the supporting element 9 arranged thereon is then inserted into the T-slot 4 and displaced in the circumferential direction of the T-slot 4 such that one end face of the spacer 8 comes into abutment with the blade 6 inserted into the T-slot 4 and an end portion 14 of the support member 9 engages under the inserted blade 6.
  • the spacer 8 inserted into the T-groove 4 is biased radially outwardly by the elastic spring force of the spring portion 13. To move therefore a radially inwardly directed force is exerted on the spacer 8 against the outwardly directed elastic restoring force.
  • a further blade 6 is inserted into the T-groove 4 and in the circumferential direction the T-slot 4 is displaced such that the further blade 6 comes into abutment with the opposite end face of the spacer 8 and the opposite end region 14 of the support element 9 engages under the further blade 6.
  • Both adjacent blades 6 are pressed radially outwardly against shoulder surfaces of the T-slot 4 by the beads 15 provided in the T-slot at the respectively under-engaging end portion 14 and radially fixed.
  • a significant advantage of the rotor blade assembly 1 according to the invention is that the support elements 9 are fastened outside the T-slot 4 in a simple manner to the spacers 8 and are handled in the sequence exclusively together with the associated spacers 8. In this way, when forming a blade assembly 1 according to the invention, no special process steps and / or tools are required in order to correctly place the support elements 9 in the T-slot 4, which is accompanied by a simple assembly of the blade ring 5.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15176056.8A 2015-07-09 2015-07-09 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique Withdrawn EP3115554A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP15176056.8A EP3115554A1 (fr) 2015-07-09 2015-07-09 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique
PCT/EP2016/065271 WO2017005592A1 (fr) 2015-07-09 2016-06-30 Ensemble d'aubes mobiles avec éléments supports élastiques pour une turbomachine thermique
CN201680040648.9A CN107835888A (zh) 2015-07-09 2016-06-30 具有用于热涡轮机的弹性支撑元件的转子叶片装置
EP16733558.7A EP3289184B1 (fr) 2015-07-09 2016-06-30 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique
US15/741,907 US10487673B2 (en) 2015-07-09 2016-06-30 Rotor blade arrangement having elastic support elements for a thermal turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15176056.8A EP3115554A1 (fr) 2015-07-09 2015-07-09 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique

Publications (1)

Publication Number Publication Date
EP3115554A1 true EP3115554A1 (fr) 2017-01-11

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EP15176056.8A Withdrawn EP3115554A1 (fr) 2015-07-09 2015-07-09 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique
EP16733558.7A Active EP3289184B1 (fr) 2015-07-09 2016-06-30 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique

Family Applications After (1)

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EP16733558.7A Active EP3289184B1 (fr) 2015-07-09 2016-06-30 Système d'aube avec des éléments de support élastiques pour une turbomachine thermique

Country Status (4)

Country Link
US (1) US10487673B2 (fr)
EP (2) EP3115554A1 (fr)
CN (1) CN107835888A (fr)
WO (1) WO2017005592A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114458391A (zh) * 2022-02-22 2022-05-10 中国联合重型燃气轮机技术有限公司 一种透平叶片锁紧组件
FR3139159B1 (fr) * 2022-08-31 2024-07-19 Safran Aircraft Engines Roue de turbine comprenant un dispositif de maintien radial de pieds d’aube dans les alveoles d’un disque de rotor

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
DE2362758A1 (de) * 1973-12-17 1975-06-26 Willi Seeber Kardaun Fa Schaufelrad fuer luefter
JPS6043102A (ja) * 1983-08-18 1985-03-07 Toshiba Corp タ−ビンロ−タ
US20020127105A1 (en) * 2000-12-16 2002-09-12 Rene Bachofner Fixation device for blading of a turbo-machine
US20110255983A1 (en) * 2008-12-23 2011-10-20 Snecma Device for attaching hammer clamp blades, associated compressor hub, compressor and turbine engine
US20120063907A1 (en) * 2010-09-13 2012-03-15 Snecma Circumferential blocking device of clamp vanes for turbine engine, with improved radial deployment
EP2562356A1 (fr) 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
FR2997722A1 (fr) * 2012-11-06 2014-05-09 Snecma Dispositif de blocage circonferentiel d'aubes marteau pour turbomachine, comprenant une piece d'actionnement de forme filaire

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
DE2362758A1 (de) * 1973-12-17 1975-06-26 Willi Seeber Kardaun Fa Schaufelrad fuer luefter
JPS6043102A (ja) * 1983-08-18 1985-03-07 Toshiba Corp タ−ビンロ−タ
US20020127105A1 (en) * 2000-12-16 2002-09-12 Rene Bachofner Fixation device for blading of a turbo-machine
US20110255983A1 (en) * 2008-12-23 2011-10-20 Snecma Device for attaching hammer clamp blades, associated compressor hub, compressor and turbine engine
US20120063907A1 (en) * 2010-09-13 2012-03-15 Snecma Circumferential blocking device of clamp vanes for turbine engine, with improved radial deployment
EP2562356A1 (fr) 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
FR2997722A1 (fr) * 2012-11-06 2014-05-09 Snecma Dispositif de blocage circonferentiel d'aubes marteau pour turbomachine, comprenant une piece d'actionnement de forme filaire

Also Published As

Publication number Publication date
EP3289184B1 (fr) 2023-11-29
US20180195399A1 (en) 2018-07-12
US10487673B2 (en) 2019-11-26
EP3289184A1 (fr) 2018-03-07
CN107835888A (zh) 2018-03-23
WO2017005592A1 (fr) 2017-01-12

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