EP2304189A2 - Aube et turbomachine pourvue d'une aube - Google Patents

Aube et turbomachine pourvue d'une aube

Info

Publication number
EP2304189A2
EP2304189A2 EP09771998A EP09771998A EP2304189A2 EP 2304189 A2 EP2304189 A2 EP 2304189A2 EP 09771998 A EP09771998 A EP 09771998A EP 09771998 A EP09771998 A EP 09771998A EP 2304189 A2 EP2304189 A2 EP 2304189A2
Authority
EP
European Patent Office
Prior art keywords
axial
range
radially outer
radially
lobes
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
EP09771998A
Other languages
German (de)
English (en)
Other versions
EP2304189B1 (fr
Inventor
Günter Neumann
Jörg GATZKE
Ulrich Harbecke
Marc Andre Schwarz
Eduard GÖTZFRIED
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2304189A2 publication Critical patent/EP2304189A2/fr
Application granted granted Critical
Publication of EP2304189B1 publication Critical patent/EP2304189B1/fr
Active 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • 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
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the present invention relates to a blade for a turbomachine, in particular a steam turbine, with a plug foot having a plurality of lobes having radially outer first sections and radially inner second sections whose axial extent is less than that of the outer sections, and a turbomachine, in particular a steam turbine, with such blades.
  • Object of the present invention is to improve the attachment of blades of turbomachines by means of plug-in foot.
  • a blade according to the preamble of claim 1 is further developed by its characterizing features.
  • Claim 10 represents a turbomachine with one or more such blades. protection.
  • the subclaims relate to advantageous developments of the present invention.
  • the plug-in foot of a rotor blade according to the invention has a first lobe and two second lobes arranged in the axial direction on both sides of this first lobe.
  • the plug-in foot can in particular be formed in three-lobed form, the first tab then forming a central tab and the two second tabs forming edge tabs. However, it can also be provided on one or both axial sides of a first or second flap further tabs, which are then preferably formed in their essential geometric dimensions as the first or a second lobe.
  • the mutually facing axial sides of the first and second lobes have a shoulder which extends in the axial direction in such a way that the lobes have a radially outer first section and a radially inner second section connected thereto via the shoulder whose extension is in the axial direction Direction is less than that of the first, outer section.
  • the mutually remote axial sides of the second lobes preferably have no shoulder, but form continuous, preferably flat axial end faces.
  • the central tab therefore has a shoulder on both its axial sides, the two edge tabs only on their inner axial sides facing the central tab.
  • the present invention is based on the finding that by suitable choice of the radial heights of the first and second sections in relation to an overall axial width of the plug-in foot, the forces that such a plug foot can absorb can be significantly increased.
  • the distance between the axially outer end faces of the two second lobes is referred to as the overall axial width. If these two axial end faces are not parallel, the axial overall width can be based, in particular, on a minimum, maximum or average distance in the axial direction.
  • the directions "axial”, “radial” and “circumferential direction” refer in the present case to the directional information for rotors in turbomachines when the blade according to the invention is attached to such a rotor.
  • the ratio of the radial height of the first, radially outer portion is in the range between 0.39 and 0.45, preferably between 0.40 and 0.44, while the ratio of the radial height of the second, radially inner portion to the total axial width between 0.40 and 0.46, preferably between 0.41 and 0.45.
  • the radial height of a first, radially outer portion is in particular the radial extent between the shoulder and a web referred to, which connects a first and a second flap in the axial direction with each other.
  • the radial height of a second, radially inner portion is referred to in particular as the radial extent between the shoulder and a radially inner end face of the tab.
  • a ratio of a total radial height of the lobes to the total axial width is in the range between 0.88 and 0.94, preferably between 0.89 and 0.93.
  • the total radial height is in particular the sum of the above-defined radial heights of the first and second sections plus a radial height of the heel.
  • This shoulder may be a purely radial step, so that the axial extent of a flap between the first and second area changes abruptly or in a very short radial section, i. e. the shoulder has a radial height substantially equal to zero.
  • the total radial height may correspond to the sum of the radial heights of the first and second sections.
  • the shoulder can also have a slope so that the axial width of the flap tapers linearly between the first and second sections. Other, in particular convex or concave curved paragraphs are possible.
  • a preferred ratio results for a shoulder from radial height to overall axial width in the range between 0.00 and 0.14, preferably between 0.00 and 0.12.
  • the first, radially outer or second radially inner section of a first lobe preferably has a ratio in the range between 0.21 and 0.27, preferably between 0.22 and 0.26 or between, based on the overall axial width 0.11 and 0.17, preferably between 0.12 and 0.16.
  • the axial extensions of the first or second section of a second lobe are preferably in the ratio of 0.16 to 0.22, preferably between 0.17 and 0.21 or in a ratio between 0.11 and 0 for the total axial width, 17, preferably between 0.12 and 0.16.
  • the two axial sides of a tab are formed parallel to each other. If this is not the case, the axial extension can be based, in particular, on a minimum, maximum or average distance between the two axial sides.
  • the first and the second tabs preferably have one, preferably two or more radially spaced bores which are aligned with each other, so that in each case one, preferably conical, bolt can be driven into it , To avoid manufacturing and assembly tolerances, these bores can also be drilled and / or rubbed after the plug feet have been inserted into the groove arrangements.
  • the position of the bolt is chosen such that the centrifugal force in an upper crack cross section of the Bolzenebene causes little or no bending loads.
  • the midpoint of a radially outer bore has a radial distance from the radially outer end of the first portion, for example, the radially inner end of a first and second lobe connecting web, the ratio in the range of 0.24 and 0 with the total axial width , 30, preferably between 0.25 and 0.29, while the center of a radially inner bore has a corresponding ratio in the range between 0.60 and 0.66, preferably between 0.61 and 0.65.
  • first and second flaps are preferably connected to each other via a radially outer web in which the first portions of the flaps terminate radially.
  • First tab, second tab and / or web can thereby integrally formed, in particular ur- and / or non-cutting or machined formed, or formed in several pieces and connected to each other, for example, welded, be.
  • the radially outer web preferably has a radial height whose ratio to the total axial width is in the range between 0.12 and 0.18, preferably between 0.13 and 0.17.
  • an axial front face of a second flap is arranged parallel to the radial plane of the holes, so that the axial axial end face of the plug foot is correspondingly rotated by one blade pitch.
  • the web on which the blade profile is arranged on the side opposite the plug-in foot preferably lies in a plane which is essentially perpendicular to this radial plane through the bores.
  • a radially inner and / or outer end face of the web substantially perpendicular to the radial plane of the bores, i. e. be formed in the radial direction through the two centers of the holes extending plane.
  • a turbomachine according to the present invention has for securing each blade according to the invention a corresponding groove arrangement with a first groove for receiving the first lobe and two second grooves for receiving the second lobe, which are separated from the first groove by a respective web.
  • the grooves are formed substantially complementary to the flap to be picked up by them, so that in this regard reference is made to the above statements.
  • the axial total width between opposite axial sides of the two second grooves preferably corresponds substantially to the overall axial width between axial sides of the two second lobes facing away from one another.
  • radial heights or axial extensions can, as explained above to the lobes, accordingly maximum, minimum or average distances in the radial or axial direction between parallel or non-parallel surfaces are used.
  • the ratio of the radial height of the first, radially outer web portion or a first, radially outer groove portion to the total axial width is preferably in a range between 0.40 and 0.46, preferably between 0.41 and 0.45, while the corresponding ratio of the radial height of the second, radially inner web portion or a corresponding radially inner groove portion to the overall axial width preferably between 0.44 and 0.50, preferably between 0.45 and 0.49.
  • Fig. 1 a blade according to an embodiment of the present invention in a perspective overall view
  • FIG. 2 shows the plug-in foot of the moving blade according to FIG. 1 in a plan view in the circumferential direction
  • FIG. 3 shows a groove arrangement for receiving the plug-in foot according to FIG. 2 in FIG.
  • FIG. 4 the plug-in foot according to FIG. 2 taken up in the groove arrangement according to FIG. 3;
  • FIG. and Fig. 5 the plug-in foot of Fig. 4 in plan view in the axial direction.
  • Fig. 1 shows a blade 1 with a trilobal plug foot 2 according to an embodiment of the present invention in a perspective view.
  • FIG. 2 which shows a plan view of the plug-in foot 2 in the circumferential direction of a rotor of a steam turbine (not shown) into which the plug-in foot 2 can be inserted in the radial direction from the outside
  • the trilobal plug-in foot has a first central tab 3 and two in the axial direction a on both sides of this central lobe 3 arranged second edge tabs 4 on.
  • the mutually facing inner axial sides 3.i of the central lobe 3 and 4.i of the edge tabs 4 each have an oblique shoulder 5, while the axially outer end faces of the two edge tabs are planar and parallel to each other.
  • a first section 3.1 with an axial extent b F2 and the two edge tabs 4 each have a first section 4.1 with an axial extent b F i on.
  • These first sections have, as measured from the radially inner end face (bottom in Fig. 2) of the web 7 to paragraph 5, ie up to the point at which the axial extent decreases, a radial height h F i.
  • the web 7 has between the radially outer end of the tabs 3, 4 and an opposite radially outer end face on a radial height hp.
  • Central and peripheral tabs 3, 4 each have one, separated by the paragraph 5 from the first section, second section 3.2 and 4.2, an axial extent O F3 and a radial height Iv 2 between a radially inner end face of the tabs and Approach 5, ie the area in which the axial extent changes.
  • the groove arrangement shown in Fig. 3 is formed with a central groove 30 for receiving the central lobe 3 and two edge grooves 40 for receiving the edge tabs 4 in the rotor of the steam turbine.
  • the tabs 3, 4 and the grooves 30, 40 are formed substantially complementary to one another.
  • the grooves 30, 40 have rounded chamfers in their radially inner groove bottom, while the webs 40 have oblique chamfers on their radially outer end faces.
  • the plug-in foot 2 is fastened by two conical bolts (not shown) taken in the axial direction.
  • two, in Fig. 1, 5 recognizable holes 6.1, 6.2 are provided, which pass through the tabs 3, 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Aube (1) pour une turbomachine, en particulier pour une turbine à vapeur, qui comporte un tenon (2) composé d'une première patte (3) et de deux autres pattes (4) situées, dans la direction axiale (a), de chaque côté de la première patte. La première et les deuxièmes pattes présentent sur des faces axiales orientées les unes vers les autres (3i, 4i) un épaulement (5) dans le sens axial de manière telle que les pattes comportent une première partie radiale externe (3.1, 4.1) et une seconde partie radiale interne (3.2, 4.2) dont la dimension axiale (bF3) est inférieure à celle (bF1, bF2) de la première partie radiale externe. Ladite aube est caractérisée en ce que par rapport à une largeur axiale totale (b) séparant des faces axiales (4.a) opposées l'une à l'autre des deuxièmes pattes (4), la hauteur radiale (hF1 / b) de la première partie radiale externe se situe dans la plage allant de 0,39 à 0,45, en particulier de 0,40 à 0,44, et la hauteur radiale (hF2 / b) de la seconde partie radiale interne se situe dans la plage allant de 0,40 à 0,46, en particulier de 0,41 à 0,45.
EP09771998.3A 2008-07-04 2009-06-24 Aube et turbomachine pourvue d'une aube Active EP2304189B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200810031780 DE102008031780A1 (de) 2008-07-04 2008-07-04 Laufschaufel und Strömungsmaschine mit Laufschaufel
PCT/DE2009/000870 WO2010000228A2 (fr) 2008-07-04 2009-06-24 Aube et turbomachine pourvue d'une aube

Publications (2)

Publication Number Publication Date
EP2304189A2 true EP2304189A2 (fr) 2011-04-06
EP2304189B1 EP2304189B1 (fr) 2016-11-16

Family

ID=41396760

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09771998.3A Active EP2304189B1 (fr) 2008-07-04 2009-06-24 Aube et turbomachine pourvue d'une aube

Country Status (6)

Country Link
US (1) US8974187B2 (fr)
EP (1) EP2304189B1 (fr)
JP (1) JP2011526339A (fr)
CN (1) CN102084091B (fr)
DE (1) DE102008031780A1 (fr)
WO (1) WO2010000228A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8899933B2 (en) * 2012-01-03 2014-12-02 General Electric Company Rotor blade mounting
EP2690254B1 (fr) 2012-07-27 2017-04-26 General Electric Technology GmbH Fixations de pied de pale de rotor de turbine
FR3104197B1 (fr) * 2019-12-10 2022-07-29 Safran Aircraft Engines Roue de rotor de turbine pour une turbomachine d’aeronef

Family Cites Families (18)

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US1362074A (en) * 1919-05-03 1920-12-14 British Westinghouse Electric Turbine
BE367869A (fr) * 1929-02-19
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2790620A (en) * 1952-07-09 1957-04-30 Gen Electric Multiple finger dovetail attachment for turbine bucket
DE1114204B (de) * 1954-09-16 1961-09-28 Licentia Gmbh Laufschaufelbefestigung fuer axiale Stroemungsmaschinen
JPS5584804A (en) * 1978-12-20 1980-06-26 Hitachi Ltd Structure for fixing rotor blade
DE2951838C2 (de) * 1979-12-21 1982-12-23 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8500 Nürnberg Axialsicherung eines bundlosen Bolzens in den Bohrungen der Radscheibenkopfstege und der Laufschaufel-Steckfüsse axialer Dampfturbinen u.dgl.
JPS61294101A (ja) * 1985-06-21 1986-12-24 Toshiba Corp タ−ビン動翼と羽根車との結合構造
US5102302A (en) * 1988-06-02 1992-04-07 General Electric Company Fan blade mount
US5062769A (en) * 1989-11-22 1991-11-05 Ortolano Ralph J Connector for turbine element
DE19546008A1 (de) * 1995-12-09 1997-06-12 Abb Patent Gmbh Turbinenschaufel, die für den Einsatz im Naßdampfbereich von Vorend- und Endstufen von Turbinen vorgesehen ist
JP2001193406A (ja) * 2000-01-07 2001-07-17 Hitachi Ltd タービン羽根車
DE10014189A1 (de) * 2000-03-23 2001-09-27 Alstom Power Nv Befestigung der Beschaufelung einer Strömungsmaschine
JP2002349207A (ja) * 2001-05-22 2002-12-04 Toshiba Corp タービン動翼
DE10340773A1 (de) * 2003-09-02 2005-03-24 Man Turbomaschinen Ag Rotor einer Dampf- oder Gasturbine
JP4368725B2 (ja) * 2004-04-16 2009-11-18 株式会社日立製作所 タービン動翼及びそれを用いたタービン
US7387494B2 (en) * 2005-04-28 2008-06-17 General Electric Company Finger dovetail attachment between a turbine rotor wheel and bucket for stress reduction
ITMI20061064A1 (it) * 2006-05-31 2007-12-01 Nuovo Pignone Spa PALA ROTORICA DI UN PRIMO STADIO DI UNA TURBINA A VAèPORE CON PIEDE A FORCHETTA E NASTRO DI COPERTURA

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Title
See references of WO2010000228A3 *

Also Published As

Publication number Publication date
CN102084091A (zh) 2011-06-01
JP2011526339A (ja) 2011-10-06
US20110110786A1 (en) 2011-05-12
CN102084091B (zh) 2016-03-02
DE102008031780A1 (de) 2010-01-07
WO2010000228A2 (fr) 2010-01-07
WO2010000228A3 (fr) 2010-12-29
US8974187B2 (en) 2015-03-10
EP2304189B1 (fr) 2016-11-16

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