EP2282010A1 - Aube de rotor pour une turbomachine à flux axial - Google Patents

Aube de rotor pour une turbomachine à flux axial Download PDF

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Publication number
EP2282010A1
EP2282010A1 EP09008226A EP09008226A EP2282010A1 EP 2282010 A1 EP2282010 A1 EP 2282010A1 EP 09008226 A EP09008226 A EP 09008226A EP 09008226 A EP09008226 A EP 09008226A EP 2282010 A1 EP2282010 A1 EP 2282010A1
Authority
EP
European Patent Office
Prior art keywords
blade
blade root
rotor
platform
side walls
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Withdrawn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
EP09008226A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Günther Dr. Walz
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP09008226A priority Critical patent/EP2282010A1/fr
Priority to PCT/EP2010/058508 priority patent/WO2010149555A1/fr
Priority to US13/378,453 priority patent/US8951016B2/en
Priority to JP2012516650A priority patent/JP5443601B2/ja
Priority to EP10725691.9A priority patent/EP2446118B1/fr
Priority to CN201080028162.6A priority patent/CN102459819B/zh
Publication of EP2282010A1 publication Critical patent/EP2282010A1/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Withdrawn legal-status Critical Current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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a blade for an axially flow-through turbomachine, comprising in succession a curved blade, a platform and a blade root having two opposite side walls which diverge from the platform to a blade root lower side.
  • Turbomachinery blades such as turbines and compressors, are well known in the art.
  • blades have a substantially dovetail-shaped foot area, wherein the two opposite side walls of the blade root from the platform in the direction of a blade root underside widen in a straight line.
  • a rotor carrying these blades usually has a shaft collar or a correspondingly shaped rotor disk, on the outer surface of which retaining grooves with a contour corresponding to the blade root extend in the axial direction.
  • the blades are inserted with their dovetailed blade root in the corresponding retaining grooves and kept safe against loosening due to the dovetail connection thus produced in rotation of the rotor in the radial direction.
  • both the blade root of a blade and the retaining groove corresponding thereto have contours whose appearance corresponds to a fir tree.
  • the existing and interlocking undercuts and projections can at high centrifugal force due to the high speed rotating rotor stresses in the material of the rotor disk or Cause blade roots, which can lead to fatigue.
  • the object of the invention is therefore to provide an alternative, reliable attachment of blades on the rotor of a turbomachine.
  • the object of the invention is achieved with a blade according to the features of claim 1.
  • the blade according to the invention comprises a curved blade blade, a platform and a blade root with two opposite side walls which diverge from the platform to a Schaufelfußunterseite, wherein both side walls along its extension between the platform and the blade root underside are largely curved in the same direction.
  • the invention is based on the knowledge that a higher loadable connection between the blade and the rotor can be brought about by a blade root that continuously bulges from the platform to the bottom of the blade root.
  • manufacturing costs can be reduced because, in particular, when the blade is used in a turbine, the otherwise usual Christmas tree connections can also be achieved by a curved dovetail connection according to the invention.
  • the cost savings is achieved in particular by the smaller number of projections and undercuts both for the blade root and for the correspondingly shaped axial retaining groove on the rotor.
  • an improved frequency attenuation can be achieved.
  • the center of gravity of such a blade can also be displaced closer to the axis of rotation of the rotor by virtue of the blade root diverging from the platform to a blade root lower side, as a result of which the load, in particular the centrifugal force load of the rotor caused by the blade weight, is reduced.
  • Both side walls are largely curved in the same direction, d. H. one of the two side walls is largely concave, while the opposite other side wall is at least largely convex. At the same time, the two side walls diverge from the platform to a bottom of the blade root.
  • the blade root essentially has a dovetail contour.
  • the curvature of that side wall of the blade root which is leading in the direction of rotation of one equipped with such a blade rotor of a turbomachine over the other side wall, largely convex.
  • the flow forces acting on the airfoil in the blade root connection are circumferentially effective such that the blade is moved toward the groove bottom of the retaining groove.
  • the claws formed between the retaining grooves of the rotor experience a low mechanical tensile stress than in the case of a buckle in the opposite direction.
  • the trailing side wall of the blade root is largely concave.
  • the lower mechanical stress can extend the life of the rotor disc as well as the blade.
  • the blade root can also be arched in the axial direction.
  • a rotor blade 10 relating to the invention is shown in a perspective view FIG. 1 ,
  • the blade 10 sequentially includes a curved airfoil 12, a platform 14, and a blade root 16.
  • the blade root 16 extends from the platform 14 to a blade root bottom 18.
  • the blade root 16 includes two opposing side walls 20, 22, the distance of which increases with increasing distance becomes larger from the platform 14. The two side walls 20, 22 thus diverge from the platform 14 to the blade root bottom 18, wherein the rounded transition of the side walls 20, 22 to the blade root bottom 18 is left out here altogether disregarded.
  • a between the two side walls 20, 22 extending center line 24 is shown in dashed line style. Both the side wall 20 and the side wall 22 are always curved along their entire extent from platform 14 to blade root bottom 18. As a result, the side wall 20 has a largely convex shape and the side wall 22 has a largely concave shape. This results in that the center line 24 is also curved.
  • FIG. 2 shows the side view of a section of a rotor disk 25, which is part of a rotor of a turbomachine.
  • the rotor disk 25 has on its outer circumference 26 on its circumference uniformly distributed retaining grooves 28, of which in FIG. 2 only two are shown.
  • the contour of the side walls 30, 32 of the retaining grooves 28 corresponds substantially to the predetermined by the two side walls 20, 22 of the blade root 16 contour. As a result, the blade is positively inserted with its blade root 16 in the retaining groove 28.
  • the side walls 30, 32 of the retaining grooves 28 are correspondingly arched as the side walls 20, 22 of the blade root 16.
  • the direction of the curvature in the circumferential direction is chosen so that a substantially convex side wall 30 of the retaining groove 28 in the direction of rotation R of the rotor or the rotor disk 25 with respect to the opposite side wall 32 of the corresponding retaining groove 28 is trailing.
  • a rotor blade 25 inserted in the rotor blade 10 is in rotation of the rotor substantially in the A, A 'and B, B' marked surface areas and is thus secured against radial movements. Due to the coordinated arrangement of the curvature of the blade root 16 and the direction of rotation R of the rotor can be avoided in the areas A, A ', B, B' an increase in the voltage stress.
  • FIG. 3 shows one too FIG. 2 analog rotor disk 25, in which the retaining grooves 28 extend obliquely with respect to the axial direction.
  • the retaining grooves 28 have a curved along the axial direction contour. Accordingly, the blade root of a corresponding blade is then additionally arched in the axial direction.
  • Each of the blades described herein may be formed, for example, as a turbine blade or as a compressor blade.
  • a blade 10 for an axially flow-through turbomachine preferably turbine specified in the reduction of mechanical stress in the blade root 16 and the holding walls 30, 32 of a rotor, the two opposite side walls 20, 22 of the blade root 16 along their extent between platform 14 and blade root bottom 18 are continuously curved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09008226A 2009-06-23 2009-06-23 Aube de rotor pour une turbomachine à flux axial Withdrawn EP2282010A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP09008226A EP2282010A1 (fr) 2009-06-23 2009-06-23 Aube de rotor pour une turbomachine à flux axial
PCT/EP2010/058508 WO2010149555A1 (fr) 2009-06-23 2010-06-17 Aube mobile pour une turbomachine à écoulement axial et fixation pour une aube mobile de ce type
US13/378,453 US8951016B2 (en) 2009-06-23 2010-06-17 Rotor blade for an axial flow turbomachine and mounting for such a rotor blade
JP2012516650A JP5443601B2 (ja) 2009-06-23 2010-06-17 軸流ターボ機械のためのロータブレードおよびそのようなロータブレードのための組み付け部
EP10725691.9A EP2446118B1 (fr) 2009-06-23 2010-06-17 Aube mobile pour une turbomachine à écoulement axial, fixation pour une aube mobile de ce type et rotor associé
CN201080028162.6A CN102459819B (zh) 2009-06-23 2010-06-17 用于轴流式涡轮机的动叶片和用于动叶片的装配装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09008226A EP2282010A1 (fr) 2009-06-23 2009-06-23 Aube de rotor pour une turbomachine à flux axial

Publications (1)

Publication Number Publication Date
EP2282010A1 true EP2282010A1 (fr) 2011-02-09

Family

ID=41131732

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09008226A Withdrawn EP2282010A1 (fr) 2009-06-23 2009-06-23 Aube de rotor pour une turbomachine à flux axial
EP10725691.9A Not-in-force EP2446118B1 (fr) 2009-06-23 2010-06-17 Aube mobile pour une turbomachine à écoulement axial, fixation pour une aube mobile de ce type et rotor associé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10725691.9A Not-in-force EP2446118B1 (fr) 2009-06-23 2010-06-17 Aube mobile pour une turbomachine à écoulement axial, fixation pour une aube mobile de ce type et rotor associé

Country Status (5)

Country Link
US (1) US8951016B2 (fr)
EP (2) EP2282010A1 (fr)
JP (1) JP5443601B2 (fr)
CN (1) CN102459819B (fr)
WO (1) WO2010149555A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016219171A1 (de) 2016-10-04 2018-04-05 Siemens Aktiengesellschaft Verfahren zur zerstörungsfreien Materialprüfung
WO2018188878A1 (fr) 2017-04-13 2018-10-18 Siemens Aktiengesellschaft Corps de base de bobine pour fabriquer un capteur à courants de foucault, capteur à courants de foucault et dispositif d'enroulement d'un fil de bobinage sur le corps de base de bobine pour fabriquer un tel capteur à courants de foucault
WO2019206004A1 (fr) * 2018-04-24 2019-10-31 东方电气集团东方电机有限公司 Bague de siège de turbine à eau de réaction

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9353629B2 (en) 2012-11-30 2016-05-31 Solar Turbines Incorporated Turbine blade apparatus
US9822647B2 (en) 2014-01-29 2017-11-21 General Electric Company High chord bucket with dual part span shrouds and curved dovetail
US10577951B2 (en) * 2016-11-30 2020-03-03 Rolls-Royce North American Technologies Inc. Gas turbine engine with dovetail connection having contoured root

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB316070A (en) * 1928-11-13 1929-07-25 Arthur Offen Improvements in and relating to turbine blades and the like and methods of fastening the same
US1890581A (en) * 1928-12-29 1932-12-13 Siemens Ag Blades for turbine rotors
US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
GB813144A (en) * 1955-12-06 1959-05-13 Bbc Brown Boveri & Cie Improvements in or relating to turbines or compressors
DE4108930A1 (de) * 1990-03-29 1991-10-02 Gen Electric Laufschaufel und beschaufelte scheibenvorrichtung fuer ein gasturbinentriebwerk
EP0502660A1 (fr) * 1991-03-04 1992-09-09 General Electric Company Assemblage de platformes pour la fixation d'aubes sur un disque de rotor
WO1997049921A1 (fr) * 1996-06-21 1997-12-31 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor
WO1999042703A1 (fr) * 1998-02-23 1999-08-26 Alliedsignal Inc. Protuberances annulaires d'attenuation de contraintes pour aubes de turbine
GB2372784A (en) * 2000-11-24 2002-09-04 Eclectic Energy Ltd Air Turbine Interlocking Blade Root and Hub Assembly
EP1489266A1 (fr) * 2003-06-16 2004-12-22 Snecma Moteurs Rétention d'une aube avec attache à pied de marteau dissymétrique à l'aide des raidisseurs de plates-formes

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE33954E (en) * 1982-02-22 1992-06-09 United Technologies Corporation Rotor blade assembly
JPS59110214A (ja) 1982-12-15 1984-06-26 Sanyo Electric Co Ltd グラフイツクイコライザ
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
JPS6125506U (ja) * 1984-07-23 1986-02-15 株式会社東芝 タ−ビン動翼の固定装置
JPS62129168A (ja) 1985-12-02 1987-06-11 Tokushu Aerosol Kk クリ−ム状流動物の分与装置
US5222865A (en) 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
EP0520259B1 (fr) * 1991-06-28 1994-09-21 Asea Brown Boveri Ag Fixation d'aubes de rotor
JPH061939A (ja) 1992-06-19 1994-01-11 Toyo Ink Mfg Co Ltd 水性印刷インキ
CN100355102C (zh) 1997-07-31 2007-12-12 夏普公司 薄膜二端元件、其制造方法和液晶显示装置
US6902376B2 (en) * 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
DE102004015301A1 (de) * 2004-03-29 2005-10-13 Mtu Aero Engines Gmbh Laufschaufel insbesondere für eine Gasturbine
JP5071305B2 (ja) 2008-08-25 2012-11-14 ダイキン工業株式会社 空気調和機

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB316070A (en) * 1928-11-13 1929-07-25 Arthur Offen Improvements in and relating to turbine blades and the like and methods of fastening the same
US1890581A (en) * 1928-12-29 1932-12-13 Siemens Ag Blades for turbine rotors
US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
GB813144A (en) * 1955-12-06 1959-05-13 Bbc Brown Boveri & Cie Improvements in or relating to turbines or compressors
DE4108930A1 (de) * 1990-03-29 1991-10-02 Gen Electric Laufschaufel und beschaufelte scheibenvorrichtung fuer ein gasturbinentriebwerk
EP0502660A1 (fr) * 1991-03-04 1992-09-09 General Electric Company Assemblage de platformes pour la fixation d'aubes sur un disque de rotor
WO1997049921A1 (fr) * 1996-06-21 1997-12-31 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor
WO1999042703A1 (fr) * 1998-02-23 1999-08-26 Alliedsignal Inc. Protuberances annulaires d'attenuation de contraintes pour aubes de turbine
GB2372784A (en) * 2000-11-24 2002-09-04 Eclectic Energy Ltd Air Turbine Interlocking Blade Root and Hub Assembly
EP1489266A1 (fr) * 2003-06-16 2004-12-22 Snecma Moteurs Rétention d'une aube avec attache à pied de marteau dissymétrique à l'aide des raidisseurs de plates-formes

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"STIFFER CIRCUMFERENTIAL DOVETAIL MOUNT FOR TURBINE BLADES", NTIS TECH NOTES, US DEPARTMENT OF COMMERCE. SPRINGFIELD, VA, US, 1 August 1992 (1992-08-01), pages 585, XP000325273, ISSN: 0889-8464 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016219171A1 (de) 2016-10-04 2018-04-05 Siemens Aktiengesellschaft Verfahren zur zerstörungsfreien Materialprüfung
WO2018188878A1 (fr) 2017-04-13 2018-10-18 Siemens Aktiengesellschaft Corps de base de bobine pour fabriquer un capteur à courants de foucault, capteur à courants de foucault et dispositif d'enroulement d'un fil de bobinage sur le corps de base de bobine pour fabriquer un tel capteur à courants de foucault
DE102017206368A1 (de) 2017-04-13 2018-10-18 Siemens Aktiengesellschaft Spulengrundkörper zur Herstellung eines Wirbelstromsensors, einen Wirbelstromsensor sowie eine Vorrichtung, um einen Spulendraht auf den Spulengrundkörper zur Herstellung eines solchen Wirbelstromsensors zu wickeln
WO2019206004A1 (fr) * 2018-04-24 2019-10-31 东方电气集团东方电机有限公司 Bague de siège de turbine à eau de réaction

Also Published As

Publication number Publication date
US8951016B2 (en) 2015-02-10
CN102459819B (zh) 2014-10-22
WO2010149555A1 (fr) 2010-12-29
US20120093654A1 (en) 2012-04-19
CN102459819A (zh) 2012-05-16
JP5443601B2 (ja) 2014-03-19
EP2446118A1 (fr) 2012-05-02
JP2012530871A (ja) 2012-12-06
EP2446118B1 (fr) 2013-05-01

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