EP2505784B1 - Rotor für eine Turbomaschine und zugehöriges Modernisierungsverfahren - Google Patents

Rotor für eine Turbomaschine und zugehöriges Modernisierungsverfahren Download PDF

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Publication number
EP2505784B1
EP2505784B1 EP12162535.4A EP12162535A EP2505784B1 EP 2505784 B1 EP2505784 B1 EP 2505784B1 EP 12162535 A EP12162535 A EP 12162535A EP 2505784 B1 EP2505784 B1 EP 2505784B1
Authority
EP
European Patent Office
Prior art keywords
rotor
intermediate pieces
blade
end wall
circumferential direction
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.)
Active
Application number
EP12162535.4A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2505784A1 (de
Inventor
Marco Micheli
Wolfgang Kappis
Luis Federico Puerta
Gabriel Dunkel
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2505784A1 publication Critical patent/EP2505784A1/de
Application granted granted Critical
Publication of EP2505784B1 publication Critical patent/EP2505784B1/de
Priority to HRP20160587TT priority Critical patent/HRP20160587T1/hr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D5/30—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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the present invention relates to a rotor for a turbomachine, in particular a compressor rotor or a turbine rotor of a turbomachine, for example a gas turbine or a steam turbine, preferably a power plant.
  • the present invention relates to a method for modernizing a turbomachine.
  • a rotor typically includes at least one blade row having a plurality of blades that are spaced from each other with respect to a rotational axis of the rotor in the circumferential direction.
  • the rotor blades project from the rotor into a gas path.
  • a working gas flows in this gas path.
  • such a rotor typically includes a rotor shaft having a circumferentially extending receiving groove for the respective blade row into which the blades with their blade roots are inserted.
  • a plurality of intermediate pieces may be provided, which are arranged in the receiving groove in each case between two adjacent blades.
  • the rotor blades each have an airfoil which protrudes substantially radially from the rotor blade, via which the respective rotor blades are fastened to the rotor shaft, and thus projects into the gas path.
  • a stabilization of the gas flow during operation of the turbomachine can be achieved by a special contouring on an outer side of the rotor adjacent to the blade leaf, in particular for a compressor.
  • the invention is concerned with the problem of providing an improved embodiment for a rotor of the type mentioned, which is characterized in particular in that the end wall contour is easier to produce. At the same time, a comparatively inexpensive modernization of existing turbomachines is to be made possible.
  • the respective end wall contour can have exactly two turning points in an axial section according to an advantageous embodiment and, in particular, transition tangentially into the outside of the rotor shaft at their axial ends. Additionally or alternatively, the respective end wall contour may be concavely curved. Additionally or alternatively, it is possible that in the respective end wall contour, the curvature along the gas path is arranged eccentrically, and it may be displaced in particular to a compressor to the upstream side.
  • An inventive compressor or a turbine according to the invention is equipped with a rotor of the type described above and can be used in a turbomachine, for example in a stationary turbomachine of a power plant.
  • the end wall contours on the outsides of the blade roots and the intermediate pieces may be the same.
  • the production of identical Endwandkonturen both on the blade roots and on the intermediate pieces avoids complex three-dimensional transitions, which simplifies the production of Endwandkonturen.
  • the end wall contours can be designed axially symmetrical. This means that the end wall contours are rotationally symmetrical with respect to the axis of rotation.
  • the respective Endwandkontur is profiled in a cutting plane containing the axis of rotation, in the circumferential direction constant or constant. This makes it particularly easy to attach the Endwandkonturen on the outer sides of the blade roots and on the outer sides of the spacers.
  • the intermediate pieces and the blade roots may be designed asymmetrically in the axial direction, such that the intermediate pieces can be mounted properly only in a single assembly position.
  • the above proposed design avoids faulty mounting of the intermediate pieces, which would lead to a significant impairment of the flow around the respective blades in the region of the blade root.
  • the receiving groove may have axially inwardly directed groove walls radially inwardly directed support contours, wherein the intermediate pieces have complementary support contours to the support contours of the receiving groove radially outward support contours, which are supported radially in the mounted state on the support contours of the receiving groove.
  • the spacers in the receiving groove are radially outward through fixed intense positive engagement between the abutting support contours.
  • the rotor shaft may be divided in an axial plane.
  • the blade feet may have, on their inner side facing away from the gas path or facing away from their outer side, protruding shoulders in the circumferential direction, which in the assembled state are supported radially on an inner side of the respective adjacent intermediate piece facing away from the respective outer side.
  • the blade roots are thus indirectly fixed radially via the intermediate pieces on the rotor shaft.
  • the vane fins as well as the intermediate pieces may have supporting contours, which cooperate with the supporting contours of the receiving groove.
  • an embodiment in which the blades are fastened radially only indirectly via the intermediate pieces on the rotor shaft is preferred. This makes it particularly easy to extract the blades radially from the receiving groove for the maintenance case, if for this purpose at least one intermediate piece is removed from the receiving groove, so that all remaining intermediate pieces and blade roots are displaceable within the receiving groove in the circumferential direction.
  • FIG. 1 includes a turbomachine 1, which may be a gas turbine plant or a steam turbine plant of a power plant for power generation, a compressor 2 or a turbine 3 with a stator 4, in which a rotor 5 is rotatably mounted about a rotation axis 6.
  • the rotor 5 has at least one blade row 7, the plurality of blades 8, which are arranged adjacent to each other with respect to the rotation axis 6 in the circumferential direction.
  • the axis of rotation 6 representing dash-dotted line is not to scale, but only to suggest the orientation of the axis of rotation. 6
  • the rotor 5 further has a rotor shaft 9, in which for the respective blade row 7 in the circumferential direction annularly extending receiving groove 10 is incorporated.
  • the blades 8 each have an airfoil 11, which in the installed state in an in FIG. 1 projected by a dash-dotted line indicated gas path 12, and a blade root 13 which is inserted into the receiving groove 10.
  • the blade root 13 is structurally integrated into the rotor shaft 9.
  • the rotor 5 according to FIG. 2 a plurality of intermediate pieces 14, which are also inserted into the receiving groove 10 and in each case between two adjacent blades 8 and between two adjacent blade roots 13 are arranged. Within the respective blade row 7 or within the associated receiving groove 10 thus intermediate pieces 14 and blades 8 or blade feet 13 alternate.
  • the respective blade root 13 has, on a side 15 facing the gas path 12, which is located in the circumferential direction next to the blade 8, a curved end wall contour 16, which in FIG FIG. 1 is indicated and in FIG. 5 is reproduced.
  • the end wall contour 16 has a concave curvature in an axial sectional plane of the rotor 5.
  • the intermediate pieces 14 likewise have an outer side 17 facing the gas path 12, on which the intermediate pieces 14 likewise each have such a curved end wall contour 16.
  • the curvature of the end wall contour 16 extends along the gas path 12, that is, substantially along the axial direction, which is defined by the rotation axis 6.
  • at least the intermediate pieces 14 may also be curved in the circumferential direction, namely corresponding to a radius 34 of the rotor 5.
  • the end wall contours 16 of the outer sides 15 of the blade roots 13 on the one hand and the outer sides 17 of the intermediate pieces 14 on the other hand have the same geometric shape.
  • flush transitions on the adjoining outer sides 15, 17 of the blade roots 13 and the intermediate pieces 14 can thereby be realized.
  • the outer sides 15 of the blade roots 13 and the outer sides 17 of the intermediate pieces 14 as in FIG. 2 recognizable radially adjacent to each other in the circumferential direction.
  • the end wall contours 16 of the outer sides 15 of the blade roots 13 and the end wall contours 16 of the outer sides 17 of the intermediate pieces 14 are configured axially symmetrical.
  • the respective profile results as in the FIGS. 1 and 5 by a longitudinal section containing the axis of rotation 6.
  • the end wall contours 16 are thus designed rotationally symmetrical. Only at the respective blade 8, a three-dimensional transition from the blade root 13 to the blade 11 may be appropriate.
  • the blade roots 13 and the intermediate pieces 14 are configured symmetrically, so that it is fundamentally possible to arrange the blade roots 13 and the intermediate pieces 14 rotated by 180 ° in the receiving groove 10.
  • the rotation by 180 ° refers to a rotation about the radial direction in the FIGS. 3 and 4 is perpendicular to the plane of the drawing.
  • the blade roots have 13 in Fig. 3 a width 18 which remains constant in the flow direction 21.
  • the intermediate pieces 14 here have a width 22 which remains constant in the flow direction 21.
  • FIG. 1 has the receiving groove 10 at its mutually axially opposite groove walls 23 radially inwardly directed support contours 24.
  • the intermediate pieces 14 have according to FIG. 2 at in the axial direction 20 facing away from each other ends 25 radially outwardly directed supporting contours 26, which are formed complementary to the support contours 24 of the receiving groove 10.
  • the support contours 26 of the intermediate pieces 14 can be supported radially on the support contours 24 of the receiving groove 10.
  • FIG. 2 have the blade roots 13 on its inner side 27, which faces away from the gas path 12 and from the outer side 15 of the blade root 13, in the circumferential direction 19 projecting paragraphs 28 on.
  • each blade root 13 expediently two such paragraphs 28 are provided, which protrude at two opposite end faces in the circumferential direction 19 of the respective end face.
  • these paragraphs 28 each engage under an inner side 29 of the adjacent intermediate piece 14, which faces away from the outer side 17 of the intermediate piece 14 or from the gas path 12.
  • the paragraphs 28 are supported in the assembled state radially on the inner sides 29 of the adjacent intermediate pieces 14 from.
  • Particularly advantageous is an embodiment in which the blades 8 are anchored exclusively indirectly via the intermediate pieces 14 on the rotor shaft 9 radially.
  • the end wall contour 16 may be configured to have exactly two inflection points 30, thereby making it possible to form a concave camber 31 oriented toward the rotation axis 6 and to realize tangential transitions at the end portions 32 of the end wall contour 16.
  • the curvature 31 is recognizable offset with respect to a geometric center 33 of the end wall contour 16 with respect to the axial direction 20 arranged, that is arranged eccentrically. In particular, the curvature 31 is thereby positioned shifted with respect to the center 33 to the inflow side.
  • the rotor 5 comprises at least one blade row 7 with a plurality of blades 8 adjacent to each other with respect to a rotation axis 6 of the rotor 5 in the circumferential direction 19 are arranged and at least one rotor shaft 9, for the respective blade row 7 a in Circumferential direction 19 extending receiving groove 10, in which the blades 8 are used with their blade roots 13, with a plurality of intermediate pieces 14, which are arranged in the receiving groove 10 between two adjacent blades 8, the blades 8 are exchanged for blades 8, the at their blade roots 13 on an outer side 15 each have a curved Endwandkontur 16 in the circumferential direction 19 adjacent to an airfoil 11 of the respective blade 8.
  • the intermediate pieces 14 are exchanged for intermediate pieces 14, which also each have on their outer side 17 a curved Endwandkontur 16, wherein the outer sides 15, 17 of the blade roots 13 and the intermediate pieces 14 radially flush adjacent in the circumferential direction 19, and wherein the Endwandkontur 16th in an axial sectional plane of the rotor 5 has a concave curvature 31.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12162535.4A 2011-03-31 2012-03-30 Rotor für eine Turbomaschine und zugehöriges Modernisierungsverfahren Active EP2505784B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
HRP20160587TT HRP20160587T1 (hr) 2011-03-31 2016-05-31 Rotor za turbostroj i odgovarajući postupak nadogradnje

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH00583/11A CH704825A1 (de) 2011-03-31 2011-03-31 Turbomaschinenrotor.

Publications (2)

Publication Number Publication Date
EP2505784A1 EP2505784A1 (de) 2012-10-03
EP2505784B1 true EP2505784B1 (de) 2016-03-02

Family

ID=43857690

Family Applications (1)

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EP12162535.4A Active EP2505784B1 (de) 2011-03-31 2012-03-30 Rotor für eine Turbomaschine und zugehöriges Modernisierungsverfahren

Country Status (9)

Country Link
US (1) US8915716B2 (ja)
EP (1) EP2505784B1 (ja)
JP (1) JP5875439B2 (ja)
CN (1) CN102733858B (ja)
AU (1) AU2012201556B2 (ja)
CH (1) CH704825A1 (ja)
HR (1) HRP20160587T1 (ja)
MY (1) MY165413A (ja)
RU (1) RU2544019C2 (ja)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704617A1 (de) * 2011-03-07 2012-09-14 Alstom Technology Ltd Laufschaufelanordnung einer Strömungsmaschine.
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2885506B8 (en) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Contoured flowpath surface
FR3014942B1 (fr) * 2013-12-18 2016-01-08 Snecma Aube, roue a aubes et turbomachine ; procede de fabrication de l'aube
RU2682217C1 (ru) * 2018-03-30 2019-03-15 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Рабочее колесо ротора компрессора газотурбинного двигателя
JP7162514B2 (ja) * 2018-12-07 2022-10-28 三菱重工業株式会社 軸流式ターボ機械及びその翼

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Publication number Priority date Publication date Assignee Title
FR996967A (fr) 1949-09-06 1951-12-31 Rateau Soc Perfectionnement aux aubages de turbomachines
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
BE540433A (ja) 1954-08-12
US4878811A (en) 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor
US5397215A (en) * 1993-06-14 1995-03-14 United Technologies Corporation Flow directing assembly for the compression section of a rotary machine
DE19650656C1 (de) * 1996-12-06 1998-06-10 Mtu Muenchen Gmbh Turbomaschine mit transsonischer Verdichterstufe
RU2136973C1 (ru) * 1998-03-26 1999-09-10 Акционерное общество "Турбомоторный завод" Устройство отборов воздуха из осевого компрессора
GB9823840D0 (en) * 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery
EP1124038A1 (de) 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbinenschaufelanordnung
US6561761B1 (en) * 2000-02-18 2003-05-13 General Electric Company Fluted compressor flowpath
US6669445B2 (en) 2002-03-07 2003-12-30 United Technologies Corporation Endwall shape for use in turbomachinery
US7300253B2 (en) 2005-07-25 2007-11-27 Siemens Aktiengesellschaft Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
EP2045444B1 (de) 2007-10-01 2015-11-18 Alstom Technology Ltd Laufschaufel, Verfahren zur Herstellung einer Laufschaufel, sowie Verdichter mit einer solchen Laufschaufel
US8459956B2 (en) 2008-12-24 2013-06-11 General Electric Company Curved platform turbine blade

Also Published As

Publication number Publication date
US20120251325A1 (en) 2012-10-04
US8915716B2 (en) 2014-12-23
MY165413A (en) 2018-03-21
CN102733858A (zh) 2012-10-17
HRP20160587T1 (hr) 2016-07-01
AU2012201556A1 (en) 2012-10-18
CN102733858B (zh) 2015-09-09
RU2544019C2 (ru) 2015-03-10
JP5875439B2 (ja) 2016-03-02
EP2505784A1 (de) 2012-10-03
JP2012215175A (ja) 2012-11-08
CH704825A1 (de) 2012-10-15
RU2012112418A (ru) 2013-10-10
AU2012201556B2 (en) 2015-07-23

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