EP1690011A1 - Rotor pour un compresseur - Google Patents

Rotor pour un compresseur

Info

Publication number
EP1690011A1
EP1690011A1 EP04804578A EP04804578A EP1690011A1 EP 1690011 A1 EP1690011 A1 EP 1690011A1 EP 04804578 A EP04804578 A EP 04804578A EP 04804578 A EP04804578 A EP 04804578A EP 1690011 A1 EP1690011 A1 EP 1690011A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
depth
blade
recess
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
EP04804578A
Other languages
German (de)
English (en)
Other versions
EP1690011B1 (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
Alstom Technology AG
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 Alstom Technology AG filed Critical Alstom Technology AG
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

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
    • 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 such as are used in particular in gas turbines, generally have a multi-stage blading which comprises blade rings arranged one behind the other in the axial direction. Each blade ring contains a large number of rotor blades that run around the circumference of the rotor are arranged and attached. Each of the rotor blades sits with a blade root in a circumferential groove, which is designed as a recess in the rotor.
  • a rotor is known for example from the document DE-A1-196 15 549.
  • the rotor blade 15 comprises an airfoil 21 projecting radially outwards and a blade root 16, which are separated from one another by a platform 18.
  • the rotor blade 15 is fastened to the blade root 16 in the rotor 10.
  • a circumferential groove in the form of a recess 11 is provided for fastening the blades, which has a depth of insertion T.
  • Shoulders 14 with a shoulder depth A are formed on the side walls within the recess 11.
  • the blade root 16 has a widening lower part 17 with a cross-sectional contour in the form of an upside-down "T" with which it engages behind the shoulders 14 of the recess 11.
  • the centrifugal force acting on the rotor blade 15 when the rotor 10 rotates becomes thereby transferred to the shoulders 14 of the recess 11 via contact surfaces 13.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is to provide an insertion depth of the insertion that is significantly greater than the minimum insertion depth.
  • the insertion depth should preferably be more than 10% greater than the minimum insertion depth. It has proven particularly useful when the screwing depth is about 40% greater than the minimum screwing depth.
  • a preferred embodiment of the invention is characterized in that the moving blades have a blade root that is adapted to the screwing depth, and that recesses are provided in the blade root to reduce weight. As a result, the increase in weight of the moving blade due to the extended blade root can be compensated and the forces occurring during operation can be reduced.
  • a recess is provided in the blade root above the lower part in the form of a hole passing through the blade root in the circumferential direction, the hole being designed in particular as an elongated hole extending in the radial direction.
  • FIG. 1 in a fragmentary longitudinal section, the attachment of a rotor blade in the rotor of a high-pressure compressor according to the prior art
  • Fig. 2 in a representation comparable to Fig. 1 shows an embodiment for a blade attachment according to the invention.
  • the rotor blade 25 is fastened in the rotor 20 with the airfoil 22, the platform 28 and the blade root 26 by means of a recess 21.
  • 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.
  • Screw-in depth T executed, which is significantly, in particular more than 10%, greater than the minimum screw-in depth Tmi n used in the prior art. 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 known attachment according to FIG. 1.
  • the screwing depth T is approximately 40% greater than that minimum insertion depth Tm in , which has proven itself in practice.
  • the height of the blade root 26 With the increase in the screw-in depth T and the shoulder depth B, the height of the blade root 26 also increases. By lengthening the blade root 26, the blade weight inevitably also increases, which would lead to increased centrifugal forces and thus to increased mechanical stress on the rotor 20.
  • a first preferred type of recess is an elongated hole 19 that passes through the blade root 26 in the circumferential direction and extends in the radial direction.
  • the elongated hole 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 is rounded-sided recesses 29 on the underside of the lower part 27 of the blade root 26. Both types of recesses 19, 29 can be combined individually or with each other in order to achieve the desired weight reduction by saving material.

Landscapes

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

Abstract

L'invention concerne un rotor (20) pour un compresseur, en particulier une turbine à gaz, comprenant une pluralité d'aubes mobiles (25), agencées en couronne autour de l'axe de rotation du rotor (20) et maintenues chacune dans une gorge tournée périphérique (21) sur le rotor (20) au moyen d'une emplanture (26) d'aubes, une partie inférieure élargie (27) de ladite emplanture (26) s'engageant derrière deux épaulements (24) formés sur les parois latérales de la gorge tournée (21). L'objectif de cette invention est d'allonger la durée de vie d'un rotor de ce type. A cet effet, la profondeur (T) de la gorge tournée (21) est sensiblement supérieure à une profondeur minimale (Tmin) de gorge, ce qui permet d'obtenir une résistance du rotor (20) suffisante pour le démarrage, au niveau de la fixation des aubes, selon les caractéristiques prédéfinies du matériau constituant le rotor (20) et dans les conditions de fonctionnement prescrites du compresseur.
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 true EP1690011A1 (fr) 2006-08-16
EP1690011B1 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
EP2320030B1 (fr) * 2009-11-10 2012-12-19 Alstom Technology Ltd Rotor et aube de rotor pour une turbomachine axiale
CH702203A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.
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

Family Cites Families (19)

* Cited by examiner, † Cited by third party
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
FR896520A (fr) * 1942-08-13 1945-02-23 Sulzer Ag Turbo-machine axiale
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
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
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
JPH08121106A (ja) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd タービン動翼
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005054682A1 *

Also Published As

Publication number Publication date
EP1690011B1 (fr) 2017-04-26
CA2548642A1 (fr) 2005-06-16
WO2005054682A1 (fr) 2005-06-16
DE10357134A1 (de) 2005-06-30
US20060228216A1 (en) 2006-10-12
CA2548642C (fr) 2011-04-19
EP1690011B8 (fr) 2017-08-02
US7513747B2 (en) 2009-04-07

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