EP2304189A2 - Rotor blade and flow engine comprising a rotor blade - Google Patents
Rotor blade and flow engine comprising a rotor bladeInfo
- 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
Links
- 230000000295 complement effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 241000191291 Abies alba Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000011089 mechanical engineering Methods 0.000 description 1
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
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200810031780 DE102008031780A1 (en) | 2008-07-04 | 2008-07-04 | Blade and turbomachine with blade |
PCT/DE2009/000870 WO2010000228A2 (en) | 2008-07-04 | 2009-06-24 | Rotor blade and flow engine comprising a rotor blade |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2304189A2 true EP2304189A2 (en) | 2011-04-06 |
EP2304189B1 EP2304189B1 (en) | 2016-11-16 |
Family
ID=41396760
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09771998.3A Active EP2304189B1 (en) | 2008-07-04 | 2009-06-24 | Rotor blade and turbomachine comprising a rotor blade |
Country Status (6)
Country | Link |
---|---|
US (1) | US8974187B2 (en) |
EP (1) | EP2304189B1 (en) |
JP (1) | JP2011526339A (en) |
CN (1) | CN102084091B (en) |
DE (1) | DE102008031780A1 (en) |
WO (1) | WO2010000228A2 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8899933B2 (en) * | 2012-01-03 | 2014-12-02 | General Electric Company | Rotor blade mounting |
EP2690254B1 (en) | 2012-07-27 | 2017-04-26 | General Electric Technology GmbH | Turbine rotor blade root attachments |
FR3104197B1 (en) | 2019-12-10 | 2022-07-29 | Safran Aircraft Engines | TURBINE ROTOR WHEEL FOR AN AIRCRAFT TURBOMACHINE |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1362074A (en) * | 1919-05-03 | 1920-12-14 | British Westinghouse Electric | Turbine |
BE367869A (en) * | 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 (en) * | 1954-09-16 | 1961-09-28 | Licentia Gmbh | Blade attachment for axial flow machines |
JPS5584804A (en) * | 1978-12-20 | 1980-06-26 | Hitachi Ltd | Structure for fixing rotor blade |
DE2951838C2 (en) * | 1979-12-21 | 1982-12-23 | M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8500 Nürnberg | Axial securing of a collarless bolt in the bores of the wheel disk head webs and the blade plug-in feet of axial steam turbines and the like. |
JPS61294101A (en) * | 1985-06-21 | 1986-12-24 | Toshiba Corp | Structure of coupling turbine moving vane and impeller |
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 (en) | 1995-12-09 | 1997-06-12 | Abb Patent Gmbh | Turbine blade, which is intended for use in the wet steam area of pre-output and output stages of turbines |
JP2001193406A (en) * | 2000-01-07 | 2001-07-17 | Hitachi Ltd | Turbine impeller |
DE10014189A1 (en) * | 2000-03-23 | 2001-09-27 | Alstom Power Nv | Blade fastening for rotating machinery has blades fitted in slots without play or with pretensioning so that torsional moments acting on inner platform or blade roots oppose torsional moments acting upon outer platform or support wing |
JP2002349207A (en) * | 2001-05-22 | 2002-12-04 | Toshiba Corp | Turbine rotor blade |
DE10340773A1 (en) * | 2003-09-02 | 2005-03-24 | Man Turbomaschinen Ag | Rotor of a steam or gas turbine |
JP4368725B2 (en) * | 2004-04-16 | 2009-11-18 | 株式会社日立製作所 | Turbine blade and turbine using the same |
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 (en) * | 2006-05-31 | 2007-12-01 | Nuovo Pignone Spa | ROTORIC SHOVEL OF A FIRST STAGE OF A VAèPORE TURBINE WITH FORK FOOT AND COVERING TAPE |
-
2008
- 2008-07-04 DE DE200810031780 patent/DE102008031780A1/en not_active Ceased
-
2009
- 2009-06-24 EP EP09771998.3A patent/EP2304189B1/en active Active
- 2009-06-24 WO PCT/DE2009/000870 patent/WO2010000228A2/en active Application Filing
- 2009-06-24 CN CN200980127003.9A patent/CN102084091B/en active Active
- 2009-06-24 JP JP2011515092A patent/JP2011526339A/en active Pending
- 2009-06-24 US US13/002,616 patent/US8974187B2/en active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2010000228A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2010000228A3 (en) | 2010-12-29 |
US20110110786A1 (en) | 2011-05-12 |
WO2010000228A2 (en) | 2010-01-07 |
DE102008031780A1 (en) | 2010-01-07 |
CN102084091B (en) | 2016-03-02 |
US8974187B2 (en) | 2015-03-10 |
JP2011526339A (en) | 2011-10-06 |
CN102084091A (en) | 2011-06-01 |
EP2304189B1 (en) | 2016-11-16 |
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