EP2860350A1 - Turbinenschaufel sowie Gasturbine - Google Patents

Turbinenschaufel sowie Gasturbine Download PDF

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Publication number
EP2860350A1
EP2860350A1 EP20130187992 EP13187992A EP2860350A1 EP 2860350 A1 EP2860350 A1 EP 2860350A1 EP 20130187992 EP20130187992 EP 20130187992 EP 13187992 A EP13187992 A EP 13187992A EP 2860350 A1 EP2860350 A1 EP 2860350A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
turbine
platform
material recess
securing element
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Withdrawn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
EP20130187992
Other languages
German (de)
English (en)
French (fr)
Inventor
Sascha Dr. Dungs
Karsten Dr. Kolk
Peter Schröder
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 EP20130187992 priority Critical patent/EP2860350A1/de
Priority to PCT/EP2014/068828 priority patent/WO2015051957A1/de
Priority to JP2016516552A priority patent/JP6211690B2/ja
Priority to CN201480055796.9A priority patent/CN105637182B/zh
Priority to EP14758952.7A priority patent/EP3025027B1/de
Priority to US15/025,725 priority patent/US20160245107A1/en
Publication of EP2860350A1 publication Critical patent/EP2860350A1/de
Withdrawn legal-status Critical Current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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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

Definitions

  • the invention relates to a turbine blade with a turbine blade, with a turbine blade root and arranged between the turbine blade and the turbine blade root turbine blade platform having on its underside a Einstecknut for inserting a sealing plate, wherein the sealing plate can be secured by means of a supported on the turbine blade platform securing element ,
  • the invention further relates to a gas turbine having a multiplicity of turbine blades and to a turbine rotor, to which the turbine blades are respectively fastened by means of a turbine blade root.
  • the respective turbine blade has a turbine blade and a turbine blade root. With the latter, it can be fixed in a correspondingly formed on a turbine rotor Turbinenrotornut.
  • the respective turbine blade with the turbine blade root in the axial direction of insertion which is aligned with the axis of rotation of the turbine rotor, inserted and held in the corresponding turbine rotor groove.
  • the turbine bucket In a transition area between the turbine blade root and a turbine bucket blade, the turbine bucket has a turbine bucket platform for supporting the turbine bucket on the turbine rotor.
  • the turbine blade roots and the turbine rotor grooves are lined with sealing sheets to separate a turbine blade air side cooling air area from an outer hot air area, in particular, a gas turbine.
  • These sealing plates are in this case, on the one hand, at an insertion groove provided in the respective turbine blade platform and, on the other hand, at one in the turbine rotor incorporated retaining groove.
  • the sealing plates are additionally secured by means of a securing means on the turbine blade platform.
  • This securing means comprises at least one flexible locking plate element, which can engage with one of its ends in a jointly configured by two directly adjacent turbine blades gap when it is bent accordingly. This securing means then prevents inadvertent rotation of the sealing plates in the circumferential direction of the turbine rotor.
  • the object of the invention is achieved by a turbine blade with a turbine blade, with a turbine blade root and a arranged between the turbine blade and the turbine blade root turbine blade platform having on its underside a Einstecknut for inserting a sealing plate, wherein the sealing sheet by means of a on the turbine blade platform supporting safety element can be secured, and wherein the turbine blade platform has a material recess with two mutually opposing abutment edges, that the securing element can be fixed transversely to the axial extent of the turbine blade root on both sides of the turbine blade.
  • the turbine blade on the turbine blade platform has a material recess for fixing on both sides and thus for securing the securing element in the circumferential direction of a turbine rotor or a platform ring element on the underside of the turbine blade platform, in particular at least partially on a web of the turbine blade platform facing the turbine rotor , is designed that the fuse element is fixed in both directions to contact edges of the material recess.
  • Such a platform ring element is composed by a plurality of turbine blades, which are arranged side by side about a rotation axis of a turbine rotor.
  • the securing element could only be secured on one side on a lateral edge contour of the turbine blade platform, so that always two mutually corresponding turbine blades were required to secure the fuse element in the sense of the invention in the circumferential direction on both sides of the turbine blade platform. Due to tolerances caused thereby, the securing element can often be secured only imprecisely on the turbine blade platforms of the turbine blades.
  • the securing element preferably comprises a bendable sheet metal strip element, which is bent on the one hand in a known manner by introduced into the sealing plate elongated slots.
  • this bendable sheet metal strip member is bent into the material recess so that the bendable sheet metal strip member having that end is fixed to both sides of the turbine blade platform with respect to the circumferential direction.
  • a cold gap to be maintained between the securing element and the turbine blade platform can be set particularly precisely, since this cold gap is adjusted in each case only with respect to a single turbine blade and no longer with respect to two such turbine blades.
  • a correctly set cold-gap is important so that the fuse element does not support the gasket during operation of a gas turbine or the like.
  • the material recess according to the invention is integrally formed on the turbine blade platform, the securing element can be secured more precisely, as a result of which a gas turbine or the like can also be operated in a more reliable manner.
  • the object of the invention is also achieved by a gas turbine with a plurality of turbine blades and with a turbine rotor, to which the turbine blades are respectively fastened by means of a turbine blade root, wherein the gas turbine turbine blades according to one of the features described herein.
  • a preferred embodiment thus also provides that the material recess is incorporated within the turbine blade platform.
  • the accumulation of material can alternatively be generated on the turbine blade platform by providing an additional accumulation of material on the underside of the turbine blade platform within which the material recess is inserted. If such a material accumulation is additionally provided on the underside of the turbine blade platform, the structure of the turbine blade platform is advantageously not adversely affected by material weakening caused by the material recess.
  • the accumulation of material can be structurally easily attached to the turbine blade platform by being cast on.
  • the material cutout can be configured using the material accumulation when the material accumulation is arranged radially below and axially adjacent to the insertion.
  • the material recess is at least partially - seen in the radial direction - below this insertion and - seen in the axial direction - next to this insertion.
  • the radial direction extends in the sense of the invention in the direction of the longitudinal extent of the turbine blade, whereas the axial direction extends in the direction of the longitudinal extent of the turbine blade root or in alignment with a rotational axis of a turbine rotor.
  • the material recess is arranged transversely to the axial extent of the turbine blade root centrally of the turbine blade platform, the material recess can be arranged directly below the turbine blade, this area of the turbine blade platforms being particularly stable.
  • the material recess can be made structurally simpler on the turbine blade platform if the material recess has a width by means of which a reliable overlap with the securing element can be ensured.
  • the securing element can be particularly easily inflected into the material recess when the material recess is arranged above the end of the turbine blade root end furthest from the turbine blade platform.
  • the farthest end is typically the lower end of the turbine blade.
  • the material recess can be configured almost arbitrarily. It is advantageous, however, if the material recess is designed triangular. As a result, the material recess can be produced easily in terms of manufacturing technology.
  • a simplified assembly of the securing element can be achieved if the two abutment edges configure a downwardly opened exception.
  • the two abutment edges include an opening angle of less than 170 ° or less than 100 °, whereby forces acting on the turbine blade platforms from the securing element can be transferred sufficiently well.
  • the abutment edges include an opening angle of more than 30 °.
  • the material recess can be produced in terms of process technology simply on the underside of the turbine blade platform if the abutment edges are arranged in a direction towards the turbine blade blade tapered receiving space.
  • the securing element can be set very precisely on the turbine blade platform if the abutment edges are machined.
  • the reliable fixing of the securing element on the turbine blade platform can be further improved if the abutment edges are made so wide that a reliable overlap with the securing element can be ensured.
  • the width of the abutment edges extends in the axial direction of the turbine blade root.
  • the abutment edges are at least as wide as the locking plate element of the securing element is thick.
  • the securing element can be easily taken up by its end from the material recess, without it protruding axially beyond the material recess.
  • an arrangement turbine blade, sealing plate and securing element can be particularly well secured against a circumferential displacement, in particular of the seal plate.
  • FIG. 1 shows a partially illustrated turbine blade 1 with a turbine blade 2, with a turbine blade root 3 and with a turbine blade platform 4 arranged between the turbine blade 2 and the turbine blade root 3.
  • the turbine blade platform 4 has on its underside 5 an insertion groove 6 for insertion of a sealing plate 7 (see FIG. 6 ), wherein the turbine blade platform 4 according to the invention a material recess 8 with two opposing abutment edges 9 and 10, that a securing element 11 for securing the seal plate 7 transverse to the axial extension 12 of the turbine blade root 3 on both sides of the turbine blade 1 can be fixed.
  • the sealing plate 7 can be secured in the circumferential direction 13 on both sides of only a single turbine blade 1.
  • present material recess 8 can be configured in many ways.
  • the material recess 8 is introduced directly inside the turbine blade platform 3. This means that the material recess 8 lies completely behind the lower outer edge 16 of the turbine blade platform 4 or behind the lower outer edge 16 of a web 17 of the turbine blade platform 4 extending from the edge region 14 to the edge region 15 and terminates in particular with this outer edge 16.
  • the material recess 8 is at least partially at height and thus immediately - as seen in axial extension 12 - axially adjacent the Einstecknut 6, in which the sealing plate 7 is inserted with proper assembly.
  • the material recess 8 is introduced into a material accumulation 20 additionally mounted below the turbine blade platform 4.
  • the material accumulation 20 is in this embodiment radially below and axially adjacent to the insertion groove 6, so that the turbine blade platform 4 is structurally not weakened by the material recess 8A.
  • the accumulation of material 20 is a survey that partially extends below the turbine blade platform 4, which is spaced apart from the edge regions 14 and 15 by a distance 21 and thus not continuous with the underside 5 of the turbine blade platform 4 from the edge region 14 to Edge region 15, or vice versa, extending web 17 is to be confused.
  • the respective distance 21 (shown here by way of example only and numbered) between the accumulation of material 20, but also between the material recesses 8 and 8A, and one of the edge regions 14 and 15 is substantially larger, preferably twice as large as the length 22 of material accumulation 20 or the opening length 22A of the material recesses 8 or 8A transversely to the axial extent 12 of the turbine blade root 3.
  • the material recess 8A may in this case be worked into the web 17, but it does not have to, whereby in the latter variant the web 17 is not weakened by the tip of the material recess 8A.
  • Both material recesses 8 and 8A are designed triangular in the exemplary embodiments shown here by way of example.
  • the material recesses 8 and 8A are each arranged transversely to the axial extension 12 of the turbine blade root 3 centrally on the turbine blade platform 4, so that the turbine blade root 3 transverse to its axial extent 12 may continue to be designed symmetrically.
  • the material recesses 8 and 8A each have a width 23, by means of which a reliable overlap with the securing element 11 can be ensured (see, by way of example FIG. 5 ).
  • the material recesses 8 and 8A also each have the two abutment edges 9 and 10, on which the securing element 11 can be supported on both sides, which are correspondingly made so wide that a reliable overlap with the securing element 11 can be ensured.
  • the two abutment edges 9 and 10 include an opening angle 26 and formulate a downward, ie in the radial direction 27 turbine blade root 3, open and upwards, ie in the radial opposite direction 28 turbine blade platform 4, tapered receiving space 29, in which the top 30 (see FIGS. 6 or 7 ) of the fuse element 11 can be inflected.
  • the material recesses 8 and 8A are each arranged above the end 31 of the turbine blade root end 3 which is furthest away from the turbine blade platform 4, so that the sealing sheet 7 can be structurally secured with the aid of the securing element 11 to the respective material recess 8 or 8A of the turbine blade platform 4.
  • Such a sealing plate 7 is exemplary in the FIG. 6 shown. It has in its upper region 32, two spaced-apart slots 33 and 34, through which in a conventional manner, designed as a sheet metal element 35 fuse element 11 is inserted.
  • the slots 33 and 34 are arranged one above the other and extend with their respective long side (not explicitly numbered here) transversely to the axial extension 12 of the turbine blade root 3, so that the securing element 11 extends radially in alignment with the turbine blade 2.
  • the tip 30 of the securing element 11 can be easily bent into the downwardly open receiving space 29 and fixed or secured to the turbine blade platform 4.
  • a related mounting state 36 is shown according to the FIG. 7 in which the tip 30 of the securing element 11 is arranged in the material recess 8 or 8A in the final assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20130187992 2013-10-10 2013-10-10 Turbinenschaufel sowie Gasturbine Withdrawn EP2860350A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP20130187992 EP2860350A1 (de) 2013-10-10 2013-10-10 Turbinenschaufel sowie Gasturbine
PCT/EP2014/068828 WO2015051957A1 (de) 2013-10-10 2014-09-04 Turbinenschaufel sowie gasturbine
JP2016516552A JP6211690B2 (ja) 2013-10-10 2014-09-04 タービンブレードおよびガスタービン
CN201480055796.9A CN105637182B (zh) 2013-10-10 2014-09-04 涡轮叶片和燃气轮机
EP14758952.7A EP3025027B1 (de) 2013-10-10 2014-09-04 Turbinenschaufel sowie gasturbine
US15/025,725 US20160245107A1 (en) 2013-10-10 2014-09-04 Turbine blade and gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20130187992 EP2860350A1 (de) 2013-10-10 2013-10-10 Turbinenschaufel sowie Gasturbine

Publications (1)

Publication Number Publication Date
EP2860350A1 true EP2860350A1 (de) 2015-04-15

Family

ID=49378090

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20130187992 Withdrawn EP2860350A1 (de) 2013-10-10 2013-10-10 Turbinenschaufel sowie Gasturbine
EP14758952.7A Not-in-force EP3025027B1 (de) 2013-10-10 2014-09-04 Turbinenschaufel sowie gasturbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14758952.7A Not-in-force EP3025027B1 (de) 2013-10-10 2014-09-04 Turbinenschaufel sowie gasturbine

Country Status (5)

Country Link
US (1) US20160245107A1 (ja)
EP (2) EP2860350A1 (ja)
JP (1) JP6211690B2 (ja)
CN (1) CN105637182B (ja)
WO (1) WO2015051957A1 (ja)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3236011A1 (de) * 2016-04-20 2017-10-25 Rolls-Royce Deutschland Ltd & Co KG Rotor mit überhang an laufschaufeln für ein sicherungselement
EP3025028B1 (de) * 2013-10-10 2018-05-09 Siemens Aktiengesellschaft Turbinenschaufel sowie gasturbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10753212B2 (en) * 2017-08-23 2020-08-25 Doosan Heavy Industries & Construction Co., Ltd Turbine blade, turbine, and gas turbine having the same
EP3611344A1 (de) * 2018-08-16 2020-02-19 Siemens Aktiengesellschaft Rotor mit umfangssicherung von dichtelementen

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FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur
US20080181767A1 (en) * 2007-01-30 2008-07-31 Siemens Power Generation, Inc. Turbine seal plate locking system
EP2662533A2 (en) * 2012-05-07 2013-11-13 General Electric Company Cover segment for blade mounting region, corresponding system and method of mounting
WO2013167346A1 (de) * 2012-05-08 2013-11-14 Siemens Aktiengesellschaft Turbinenlaufschaufel und axialer rotorabschnitt für eine gasturbine

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EP1978211A1 (de) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Anordnung zur Axialsicherung an Laufschaufeln in einem Rotor sowie Gasturbine mit einer solchen Anordnung
EP2088287A1 (de) * 2008-02-08 2009-08-12 Siemens Aktiengesellschaft Anordnung zur Axialsicherung von Laufschaufeln in einem Rotor einer Gasturbine
US8210823B2 (en) * 2008-07-08 2012-07-03 General Electric Company Method and apparatus for creating seal slots for turbine components
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Publication number Priority date Publication date Assignee Title
FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur
US20080181767A1 (en) * 2007-01-30 2008-07-31 Siemens Power Generation, Inc. Turbine seal plate locking system
EP2662533A2 (en) * 2012-05-07 2013-11-13 General Electric Company Cover segment for blade mounting region, corresponding system and method of mounting
WO2013167346A1 (de) * 2012-05-08 2013-11-14 Siemens Aktiengesellschaft Turbinenlaufschaufel und axialer rotorabschnitt für eine gasturbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3025028B1 (de) * 2013-10-10 2018-05-09 Siemens Aktiengesellschaft Turbinenschaufel sowie gasturbine
EP3236011A1 (de) * 2016-04-20 2017-10-25 Rolls-Royce Deutschland Ltd & Co KG Rotor mit überhang an laufschaufeln für ein sicherungselement
US10526904B2 (en) 2016-04-20 2020-01-07 Rolls-Royce Deutschland Ltd & Co Kg Rotor with overhang at blades for a locking element
EP3236011B1 (de) 2016-04-20 2022-08-31 Rolls-Royce Deutschland Ltd & Co KG Rotor mit überhang an laufschaufeln für ein sicherungselement

Also Published As

Publication number Publication date
EP3025027B1 (de) 2017-11-01
CN105637182B (zh) 2018-01-16
CN105637182A (zh) 2016-06-01
JP6211690B2 (ja) 2017-10-11
JP2016538448A (ja) 2016-12-08
WO2015051957A1 (de) 2015-04-16
EP3025027A1 (de) 2016-06-01
US20160245107A1 (en) 2016-08-25

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