EP1614857A1 - Turbomachine ayant un rotor composé d'au moins un disque percé - Google Patents

Turbomachine ayant un rotor composé d'au moins un disque percé Download PDF

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Publication number
EP1614857A1
EP1614857A1 EP04015806A EP04015806A EP1614857A1 EP 1614857 A1 EP1614857 A1 EP 1614857A1 EP 04015806 A EP04015806 A EP 04015806A EP 04015806 A EP04015806 A EP 04015806A EP 1614857 A1 EP1614857 A1 EP 1614857A1
Authority
EP
European Patent Office
Prior art keywords
rotor
bore
turbomachine
rotor disk
disk
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Withdrawn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
EP04015806A
Other languages
German (de)
English (en)
Inventor
Harald Hoell
Reimar Dr. Schaal
Werner Dr. Setz
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP04015806A priority Critical patent/EP1614857A1/fr
Priority to PCT/EP2005/052698 priority patent/WO2006003074A1/fr
Priority to EP05760921A priority patent/EP1763622A1/fr
Priority to JP2007518576A priority patent/JP2008505270A/ja
Priority to US11/631,768 priority patent/US7819632B2/en
Priority to CNA200580029209XA priority patent/CN101040101A/zh
Publication of EP1614857A1 publication Critical patent/EP1614857A1/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Withdrawn legal-status Critical Current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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-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
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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 invention relates to a turbomachine having a rotor rotatably mounted about a rotation axis, which rotor has at least one rotor disk, in which at least one axially extending bore is arranged. Furthermore, the invention relates to a rotor for a turbomachine and a rotor disk having at least one axially extending bore through the rotor disk.
  • Stationary gas turbines and aircraft turbines with rotors composed of a plurality of rotor disks are generally known.
  • One central or several decentralized tie rods clamp the rotor disks together.
  • the rotor disks have at least one cylindrical bore, through which the tie rods extend.
  • Each rotor disk carries on its outer periphery in a ring arranged blades, which are flowed around for compressing a flow medium or for receiving rotational energy from a flow medium thereof.
  • the blades attached to the rotor disc cause enormous centrifugal forces during operation, so that each rotor disk is exposed to great loads.
  • the rotor disks must be faultless.
  • suitable test methods are known, by means of which the rotor disk are examined before their first use as well as in repeat tests for cracks and defects in order to ensure a minimum service life and thus safe operation of the turbomachine.
  • the object of the invention is therefore to provide a rotor disk for the rotor of a turbomachine, a rotor for a turbomachine and a turbomachine whose life is extended by design measures.
  • the bore of the rotor disk extends in the axial direction at least partially crowned with a larger diameter in the middle region.
  • the solution is based on the inventive idea that increase the Mises's comparative stresses in the bore region by the bore in the axial direction at least partially spherical.
  • the increase in the comparative stress is due to the influence of the axial and tangential stress component by the spherical geometry of the bore, i. their convex cross-sectional shape. Due to the increased reference stresses, centrifuging in the hub area leads to greater plasticization, as a result of which the amount of residual compressive stress increases due to geometry, without an increase in the spin speed. Higher compressive residual stresses mean a delay in crack propagation and reduced risk of brittle fracture in later operation.
  • the turbomachine can be designed as a turbine, as a compressor, as a gas turbine or as a steam turbine. It is independent whether they are single-stage or multi-stage formed or flowed through axially or axially.
  • the bore is central, ie in the center of the rotor disk, and / or decentralized, ie spaced from the center of the rotor disk arranged.
  • the effects achieved by the crowned embodiment are independent of whether the hole is provided centrally or decentrally.
  • the maximum inner diameter of the spherical bore is arranged in the axial direction between the end faces of the rotor disk.
  • Gas turbines and their operations are generally known.
  • 1 shows a turbomachine 1 designed as a turbomachine 1 with a rotatably mounted about a rotation axis rotor 5.
  • a turbomachine 1 designed as a turbomachine 1 with a rotatably mounted about a rotation axis rotor 5.
  • a compressor 7 a combustion chamber 9 with burners 11.
  • the combustion chamber 9, the turbine unit 13 is connected downstream.
  • the rotor 5 has a plurality of adjoining rotor disks 20, in each of which a central bore 16 is provided, through which a tie rod 21 extends.
  • Fig. 2 shows the side view of a rotor disk 14 according to the invention with a centrally disposed bore 15, which extends in the axial direction partially spherical, that is curved outwardly.
  • FIG. 3 shows a section through the rotor disk 14 according to the invention as shown in FIG. 2.
  • the bore 15 initially extends in the axial direction of the rotor 5 in a circular cylindrical manner, then merges into a crowned section and ends with a circular cylindrical section.
  • the diameter 17 of the bore 15 is maximum in the spherical portion in the middle between the two end faces 19 of the rotor disk 14 and decreases in the direction of the end faces 19 and the circular cylindrical sections on both sides evenly.
  • the rotor disk 14 has a convex recess.
  • the material of the rotor disc, which surrounds the recess, thus has a concave contour.
  • FIG. 4 shows a cylindrical bore 16 known from the prior art through a rotor disk 20.
  • FIG. 5 shows the profile of stresses ⁇ of a rotor disk 20 of the prior art in a radius-voltage diagram.
  • the characteristic curve 22 shown in a circle-dash line type shows the course of the tangential stresses at a distance x from the surface of the bore 16 in the radial direction.
  • the curve 24 shown in full line shows the Mises comparison voltages. Both stresses decrease with increasing distance x from the surface of the cylindrical bore 16 of the rotor disk 20. After spinning the rotor disk 20, this pressure compressive stresses, whose course is shown in dashed line type by the characteristic curve 26. The amount of compressive residual stresses decreases with increasing distance x.
  • Fig. 6 shows the rotor disk 14 according to the invention with a along the axial direction completely convex bore 15, the shape is also referred to as spherical.
  • FIG. 7 shows the profile of stresses ⁇ of a rotor disk 14 according to the invention in a radius-voltage diagram.
  • the tangential stresses 28 of the rotor disk 14 according to the invention are shown in a circle-dash line type and the Mises comparison voltages 30 in solid line. Both stresses decrease with increasing distance x from the surface of the spherical bore 15 of the rotor disk 14. After spinning the rotor disk 14, this has a compressive residual stress 32 shown in solid line, the amount of which decreases with increasing distance x.
  • FIG. 8 shows the characteristic curves 22, 24, 26, 28, 30, 32 of the two diagrams FIG. 5 and FIG. 7 in comparison.
EP04015806A 2004-07-05 2004-07-05 Turbomachine ayant un rotor composé d'au moins un disque percé Withdrawn EP1614857A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04015806A EP1614857A1 (fr) 2004-07-05 2004-07-05 Turbomachine ayant un rotor composé d'au moins un disque percé
PCT/EP2005/052698 WO2006003074A1 (fr) 2004-07-05 2005-06-10 Turbomachine a rotor comportant au moins un disque de rotor alese
EP05760921A EP1763622A1 (fr) 2004-07-05 2005-06-10 Turbomachine ayant un rotor composé d'au moins un disque percé
JP2007518576A JP2008505270A (ja) 2004-07-05 2005-06-10 流体機械におけるロータの回転円板
US11/631,768 US7819632B2 (en) 2004-07-05 2005-06-10 Turbo machine with a rotor which has at least one rotor disk with a bore
CNA200580029209XA CN101040101A (zh) 2004-07-05 2005-06-10 具有带有至少一个钻孔转子盘的转子的涡轮机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04015806A EP1614857A1 (fr) 2004-07-05 2004-07-05 Turbomachine ayant un rotor composé d'au moins un disque percé

Publications (1)

Publication Number Publication Date
EP1614857A1 true EP1614857A1 (fr) 2006-01-11

Family

ID=34925627

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04015806A Withdrawn EP1614857A1 (fr) 2004-07-05 2004-07-05 Turbomachine ayant un rotor composé d'au moins un disque percé
EP05760921A Withdrawn EP1763622A1 (fr) 2004-07-05 2005-06-10 Turbomachine ayant un rotor composé d'au moins un disque percé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05760921A Withdrawn EP1763622A1 (fr) 2004-07-05 2005-06-10 Turbomachine ayant un rotor composé d'au moins un disque percé

Country Status (5)

Country Link
US (1) US7819632B2 (fr)
EP (2) EP1614857A1 (fr)
JP (1) JP2008505270A (fr)
CN (1) CN101040101A (fr)
WO (1) WO2006003074A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1801349A1 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de roue de turbine haute pression avec une contrainte axiale réduite et procédé

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070264989A1 (en) * 2005-10-03 2007-11-15 Rajesh Palakkal Rendezvous calling systems and methods therefor
US20080140767A1 (en) * 2006-06-14 2008-06-12 Prasad Rao Divitas description protocol and methods therefor
GB0614972D0 (en) * 2006-07-28 2006-09-06 Rolls Royce Plc A mounting disc
EP2428642A1 (fr) * 2010-09-08 2012-03-14 Siemens Aktiengesellschaft Rotor pour une turbine à vapeur avec des exclusions de matière sur sa circonférence inclinées par rapport à l'axe du rotor
US10119400B2 (en) 2012-09-28 2018-11-06 United Technologies Corporation High pressure rotor disk
US8959767B2 (en) * 2012-11-21 2015-02-24 United Technologies Corporation Method of extending life of rotating parts
WO2016015222A1 (fr) * 2014-07-29 2016-02-04 华为技术有限公司 Procédé et dispositif de chiffrement et de transmission de données

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB219655A (en) * 1923-07-28 1924-10-09 Escher Wyss Maschf Ag A rotor for high-speed engines and machines, more particularly for steam and gas turbines
US2579745A (en) * 1947-02-17 1951-12-25 Rolls Royce Axial-flow compressor or turbine
US4497612A (en) * 1983-11-25 1985-02-05 General Electric Company Steam turbine wheel antirotation means
JPS62251403A (ja) * 1986-04-25 1987-11-02 Hitachi Ltd 中心孔を有するロ−タ
US4844694A (en) * 1986-12-03 1989-07-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Fastening spindle and method of assembly for attaching rotor elements of a gas-turbine engine
EP1013893A2 (fr) * 1998-12-22 2000-06-28 General Electric Company Evitement de la dilatation thermique différentielle des éléments d'un rotor de turbine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3400835A1 (de) * 1984-01-12 1985-07-18 Klöckner-Humboldt-Deutz AG, 5000 Köln Laufrad fuer turbomaschinen
FR2712029B1 (fr) * 1993-11-03 1995-12-08 Snecma Turbomachine pourvue d'un moyen de réchauffage des disques de turbines aux montées en régime.
JP3149774B2 (ja) * 1996-03-19 2001-03-26 株式会社日立製作所 ガスタービンロータ
JP2001003702A (ja) * 1999-06-16 2001-01-09 Mitsubishi Heavy Ind Ltd ガスタービンロータ
US7241111B2 (en) * 2003-07-28 2007-07-10 United Technologies Corporation Contoured disk bore

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB219655A (en) * 1923-07-28 1924-10-09 Escher Wyss Maschf Ag A rotor for high-speed engines and machines, more particularly for steam and gas turbines
US2579745A (en) * 1947-02-17 1951-12-25 Rolls Royce Axial-flow compressor or turbine
US4497612A (en) * 1983-11-25 1985-02-05 General Electric Company Steam turbine wheel antirotation means
JPS62251403A (ja) * 1986-04-25 1987-11-02 Hitachi Ltd 中心孔を有するロ−タ
US4844694A (en) * 1986-12-03 1989-07-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Fastening spindle and method of assembly for attaching rotor elements of a gas-turbine engine
EP1013893A2 (fr) * 1998-12-22 2000-06-28 General Electric Company Evitement de la dilatation thermique différentielle des éléments d'un rotor de turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 0121, no. 26 (M - 687) 19 April 1988 (1988-04-19) *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1801349A1 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de roue de turbine haute pression avec une contrainte axiale réduite et procédé

Also Published As

Publication number Publication date
US20080031724A1 (en) 2008-02-07
CN101040101A (zh) 2007-09-19
EP1763622A1 (fr) 2007-03-21
JP2008505270A (ja) 2008-02-21
WO2006003074A1 (fr) 2006-01-12
US7819632B2 (en) 2010-10-26

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