EP1690011B1 - Rotor pour un compresseur - Google Patents

Rotor pour un compresseur Download PDF

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Publication number
EP1690011B1
EP1690011B1 EP04804578.5A EP04804578A EP1690011B1 EP 1690011 B1 EP1690011 B1 EP 1690011B1 EP 04804578 A EP04804578 A EP 04804578A EP 1690011 B1 EP1690011 B1 EP 1690011B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
blade
depth
groove
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.)
Not-in-force
Application number
EP04804578.5A
Other languages
German (de)
English (en)
Other versions
EP1690011A1 (fr
EP1690011B8 (fr
Inventor
René Bachofner
Pietro Grigioni
Wolfgang Kappis
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP1690011A1 publication Critical patent/EP1690011A1/fr
Publication of EP1690011B1 publication Critical patent/EP1690011B1/fr
Application granted granted Critical
Publication of EP1690011B8 publication Critical patent/EP1690011B8/fr
Not-in-force 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
    • F01D5/30—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a rotor for a compressor according to the preamble of claim 1.
  • Rotors of high-pressure compressors as they are used in particular in gas turbines, generally have a multi-stage blading, which comprises in the axial direction successively arranged blade rings.
  • Each vane ring contains a variety of blades, which are on the circumference of the rotor are arranged and fixed.
  • Each of the blades sits with a blade root in a circumferential groove which is formed as a recess in the rotor.
  • Such a rotor is for example from the document DE-A1-196 15 549 known.
  • the attachment of a single blade in a rotor according to the prior art is also in Fig. 1
  • the blade 15 comprises a radially outwardly projecting blade 21 and a Schaufelfuss16, which are separated by a platform 18 from each other.
  • the blade 15 is attached to the blade root 16 in the rotor 10.
  • a circumferential groove in the form of a recess 11 is provided, which has a Eindusiefe T.
  • shoulders 14 are formed with a shoulder depth A on the side walls.
  • the blade root 16 has a widening lower part 17 with a cross-sectional contour in the form of an inverted "T", with which it engages behind the shoulders 14 of the recess 11.
  • the force acting on the blade 15 during rotation of the rotor 10 centrifugal force is transmitted via contact surfaces 13 on the shoulders 14 of the recess 11.
  • This minimum insertion depth T min allows a shoulder depth A of the shoulder 14 which is just sufficient under the prevailing extreme operating conditions (high speeds, temperatures up to 500 ° C) and the properties of the selected rotor material sufficient initial strength of the rotor 10 in the Shoulders 14 to allow.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is to provide a Eindusung Eindusung which is substantially greater than the minimum insertion depth, and adjust the blade root accordingly.
  • the insertion depth is more than 40% greater than the minimum insertion depth.
  • recesses are provided for weight reduction in the blade root. As a result, can be compensated for increases in weight of the blade due to the extended blade root and reduce the forces occurring during operation.
  • a recess in the form of a hole passing through the blade root in the circumferential direction is provided in the blade root above the lower part, wherein the hole is designed in particular as a slot extending in the radial direction.
  • lateral shoulders 24 are again formed here, behind which the blade root 26 engages with its widened lower part 27 and is supported on the contact surfaces 23 when centrifugal forces occur.
  • the recess 21 is now performed with a Eindusiefe T, which is substantially, in particular more than 10%, greater than that in the prior art used minimum insertion depth T min .
  • This makes it possible to bring the shoulder depth of the shoulders 24 to a value B, which is substantially greater than the shoulder depth A in the prior art attachment according to Fig. 1 ,
  • the insertion depth T is about 40% greater than the minimum insertion depth T min , which has proven itself in practice.
  • the height of the blade root 26 also increases.
  • the lengthening of the blade root 26 inevitably increases the blade weight, which would lead to increased centrifugal forces and thus to increased mechanical stress on the rotor 20. It is therefore particularly advantageous if at least part of the increase in weight caused by the extension is removed again by suitable measures.
  • the measures consist in saving material on the rotor blade 25 in the region of the blade root 26 at points which are not critical for the mechanical strength by providing recesses.
  • a first preferred type of recess is a slot 19 that passes in the circumferential direction through the blade root 26 and extends in the radial direction.
  • the slot 19 is arranged in the slender section of the blade root 26 and is located in the middle between the two shoulders 24.
  • a second preferred type of recess are edge-side, rounded depressions 29 on the underside of the lower part 27 of the blade root 26. Both types of recesses 19th , 29 can be combined either individually or together to achieve the desired weight reduction through material savings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (3)

  1. Rotor (20) pour un compresseur, plus particulièrement une turbine à gaz, ce rotor (20) comprenant une pluralité d'aubes (25), qui sont disposées autour de l'axe de rotation du rotor (20) sous la forme d'une couronne et sont maintenues chacune avec une embase d'aube (26) dans une gorge circulaire (21) sur le rotor (20), l'embase de l'aube (26) s'emboîtant avec une partie inférieure (27) qui s'élargit derrière deux épaulements (24), réalisés au niveau des parois latérales de la gorge (21), avec une profondeur d'épaulement (A), et la gorge (21) est définie par une profondeur de gorge minimale (Tmin), spécifique au compresseur, qui permet d'obtenir, grâce aux propriétés des matériaux du rotor (20) et aux conditions de fonctionnement prédéterminées du compresseur, une solidité suffisante pour le début, du rotor (20) au niveau de la fixation des aubes, caractérisé en ce que la gorge (21) du rotor (20) présente une profondeur de gorge (T) qui est 40 % supérieure à la profondeur de gorge minimale (Tmin), en ce que la profondeur d'épaulement (B) est agrandie en fonction de la profondeur de gorge (T) avec (A<B), et en ce que les aubes (25) comprennent une embase d'aube (26) adaptée à la profondeur de gorge (T) et en ce que, pour la réduction du poids, dans l'embase de l'aube (26), sont prévus des évidements (19, 29), moyennant quoi, dans l'embase de l'aube (26), au-dessus de la partie inférieure (27), est prévu un évidement sous la forme d'un trou (19) traversant l'embase de l'aube (26) dans la direction circonférentielle.
  2. Rotor selon la revendication 1, caractérisé en ce que le trou est conçu comme un trou oblong (19) s'étendant dans la direction radiale.
  3. Rotor selon la revendication 1 ou 2, caractérisé en ce que, sur l'envers de la partie inférieure (27) de l'embase de l'aube (26), sont prévus des évidements sous la forme de renfoncements (29).
EP04804578.5A 2003-12-06 2004-11-26 Rotor pour un compresseur Not-in-force EP1690011B8 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10357134A DE10357134A1 (de) 2003-12-06 2003-12-06 Rotor für einen Verdichter
PCT/EP2004/053114 WO2005054682A1 (fr) 2003-12-06 2004-11-26 Rotor pour un compresseur

Publications (3)

Publication Number Publication Date
EP1690011A1 EP1690011A1 (fr) 2006-08-16
EP1690011B1 true EP1690011B1 (fr) 2017-04-26
EP1690011B8 EP1690011B8 (fr) 2017-08-02

Family

ID=34625613

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04804578.5A Not-in-force EP1690011B8 (fr) 2003-12-06 2004-11-26 Rotor pour un compresseur

Country Status (5)

Country Link
US (1) US7513747B2 (fr)
EP (1) EP1690011B8 (fr)
CA (1) CA2548642C (fr)
DE (1) DE10357134A1 (fr)
WO (1) WO2005054682A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702203A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.
EP2320030B1 (fr) * 2009-11-10 2012-12-19 Alstom Technology Ltd Rotor et aube de rotor pour une turbomachine axiale
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
US9109456B2 (en) * 2011-10-26 2015-08-18 General Electric Company System for coupling a segment to a rotor of a turbomachine
EP2956626B1 (fr) * 2013-02-12 2019-11-20 United Technologies Corporation Aube de soufflante comprenant des cavités extérieures
EP2860361B1 (fr) 2013-10-08 2017-03-01 MTU Aero Engines GmbH Support d'élément et turbomachine
US9739159B2 (en) 2013-10-09 2017-08-22 General Electric Company Method and system for relieving turbine rotor blade dovetail stress
KR101920070B1 (ko) * 2016-12-23 2018-11-19 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
FR3100835B1 (fr) * 2019-09-17 2022-10-07 Safran Aircraft Engines Aube de rotor pour une turbomachine
DE102022200592A1 (de) * 2022-01-20 2023-07-20 Siemens Energy Global GmbH & Co. KG Turbinenschaufel und Rotor
DE102022202368A1 (de) 2022-03-10 2023-09-14 Siemens Energy Global GmbH & Co. KG Nutdesign einer Scheibe für eine Turbinenschaufel, Rotor und ein Verfahren
US12055069B2 (en) * 2022-09-20 2024-08-06 Siemens Energy, Inc. System and method for reducing blade hook stress in a turbine blade

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896520A (fr) * 1942-08-13 1945-02-23 Sulzer Ag Turbo-machine axiale
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
JPH08121106A (ja) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd タービン動翼
DE19615549A1 (de) * 1996-04-19 1997-10-23 Asea Brown Boveri Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
US1638648A (en) * 1923-08-13 1927-08-09 Westinghouser Electric And Mfg Turbine-blade fastening
US2010022A (en) * 1931-06-27 1935-08-06 Holzwarth Gas Turbine Co Cooling of gas turbine blades
US2414278A (en) * 1943-07-23 1947-01-14 United Aircraft Corp Turbine blade mounting
GB723813A (en) * 1952-05-30 1955-02-09 Power Jets Res & Dev Ltd Improvements in or relating to bladed rotors for compressors, turbines and like fluid flow machines
GB751740A (en) * 1953-10-02 1956-07-04 English Electric Co Ltd Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors
US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
US3584971A (en) * 1969-05-28 1971-06-15 Westinghouse Electric Corp Bladed rotor structure for a turbine or a compressor
SU418618A1 (fr) * 1972-01-25 1974-03-05
US4875830A (en) 1985-07-18 1989-10-24 United Technologies Corporation Flanged ladder seal
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
DE59705094D1 (de) * 1996-06-21 2001-11-29 Siemens Ag Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor
FR2758364B1 (fr) * 1997-01-16 1999-02-12 Snecma Disque aubage a aubes tripodes
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
DE10120532A1 (de) * 2001-04-26 2002-10-31 Alstom Switzerland Ltd Vorrichtung und Verfahren zur Befestigung einer Laufschaufel längs einer innerhalb eines Rotors einer axial durchströmten Turbomaschine verlaufenden Umfangsnut
US6832892B2 (en) * 2002-12-11 2004-12-21 General Electric Company Sealing of steam turbine bucket hook leakages using a braided rope seal

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896520A (fr) * 1942-08-13 1945-02-23 Sulzer Ag Turbo-machine axiale
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
JPH08121106A (ja) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd タービン動翼
DE19615549A1 (de) * 1996-04-19 1997-10-23 Asea Brown Boveri Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters

Also Published As

Publication number Publication date
US20060228216A1 (en) 2006-10-12
US7513747B2 (en) 2009-04-07
WO2005054682A1 (fr) 2005-06-16
CA2548642A1 (fr) 2005-06-16
DE10357134A1 (de) 2005-06-30
CA2548642C (fr) 2011-04-19
EP1690011A1 (fr) 2006-08-16
EP1690011B8 (fr) 2017-08-02

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