EP0893576A2 - Connexion d' éléments rotatifs - Google Patents

Connexion d' éléments rotatifs Download PDF

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Publication number
EP0893576A2
EP0893576A2 EP98810441A EP98810441A EP0893576A2 EP 0893576 A2 EP0893576 A2 EP 0893576A2 EP 98810441 A EP98810441 A EP 98810441A EP 98810441 A EP98810441 A EP 98810441A EP 0893576 A2 EP0893576 A2 EP 0893576A2
Authority
EP
European Patent Office
Prior art keywords
positive
insert ring
centering
connection
connection according
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
EP98810441A
Other languages
German (de)
English (en)
Other versions
EP0893576B1 (fr
EP0893576A3 (fr
Inventor
Harry Alkelin
Mikael Fryklund
Roland Nilsson
Per Thörnblad
Hans Dr. Wettstein
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.)
GE Vernova GmbH
Original Assignee
ABB Alstom Power Switzerland Ltd
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Alstom Power Switzerland Ltd, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Alstom Power Switzerland Ltd
Publication of EP0893576A2 publication Critical patent/EP0893576A2/fr
Publication of EP0893576A3 publication Critical patent/EP0893576A3/fr
Application granted granted Critical
Publication of EP0893576B1 publication Critical patent/EP0893576B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/026—Shaft to 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.
    • Y10T403/217—Members having different coefficients of expansion
    • 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
    • Y10T403/00—Joints and connections
    • Y10T403/48—Shrunk fit

Definitions

  • the invention relates to a force-locking connection of rotating components according to the preamble of claim 1.
  • Such connections are found, for example, when assembling rotor disks of thermally highly loaded gas turbines.
  • the rotor of a turbomachine generally consists of several rotor disks, which are lined up axially and aligned concentrically. These rotor disks are clamped together by one or more tie rods and thus form a compact unit.
  • the rotors have a very high axial rigidity and centering Exhibit [concentricity], i.e. that in the different operating states no unstable conditions, vibrations or eccentric running through Changes in the center of gravity can result. This despite the inevitable different coefficients of thermal expansion of the applied different materials. About such displacements of the rotor parts against each other Hirth serrations can be avoided on the end faces of the rotor disks be arranged.
  • Other measures, such as short cones etc. could in practice offset rotor parts against each other and thus non-circular running, which can lead to the destruction of the rotor and stator prevent.
  • the invention tries to avoid these disadvantages. It is her job based on a non-positive and positive connection of rotating components create which is designed or can be retrofitted so that a operational misalignment [rotation or displacement] of components to each other is avoided.
  • the rotating components 1 and 2 as rotor disks 1 and 2nd designated.
  • the individual rotor disks are 1, 2 axially strung together and by at least one (not in the figures illustrated) tie rods clamped together concentrically.
  • the through the Tension forces caused by tie rods result in a non-positive connection of the Rotor disks.
  • these of the frictional forces resulting from the clamping forces are not sufficient to cause a misalignment to prevent the rotor disks against each other.
  • this can be the case when the rotor disks are different during rotation Have stretching behavior, partly because they are made of different materials consist.
  • This positive and non-positive connection is formed as a centering seat 3, which lies between two adjacent to each other Rotor disks are provided and biased by an insert ring 7.
  • the centering seat has the shape of a on the two adjacent rotor disks orbiting, concentric level with a positive, protruding Centering offset 4 on the rotor part 1 and a negative, drawn centering offset 5 on the rotor part 2.
  • the insert ring 7 is on the inner rotor disk relative to the centering seat 1 arranged, namely in a cavity 6. It is biased, which is the occasion assembly by thermal shrinking. On the occasion of the rotation Due to the centrifugal force due to mass, he presses the relative to the centering seat 3 internal rotor disc 1 against the external rotor disc 2 and creates a positive and non-positive connection.
  • the positive and negative Centering offsets 4, 5 of this centering seat have essentially one cylindrical contact surface 8, which is concentric with the rotor axis. Of course, there is also a slightly conical alignment of the contact surface 8 possible.
  • the centering seat prevents radial displacement and through that The contact pressure also increases the resistance to axial displacement of the rotor disks against each other. Such shifts can be caused by the thermal expansions and thermal stresses at the high operating temperatures of the gas turbines are caused.
  • the centering seat 3 is both in front of and behind the contact surface 8 provided with concave undercuts 10. Their facing the contact surface Fillets end within the contact area.
  • the internal mechanical stress curve can be changed so that the Zones of greatest mechanical stress, i.e. of the greatest voltage gradient be moved from the area of the contact surface 8.
  • both rotor parts achieved that among those mentioned certain Operating conditions in the contact area only crack-closing and thus Crack growth-preventing surface-parallel compressive stresses arise.
  • the mutual centering of the rotor disks via two conical seats via two conical seats.
  • a double conical is then useful Training of the centering seat 3 with a corresponding double conical extending contact surface 9.
  • the rotor part 2 which the has positive centering offset 4, while the rotor part 1 with the negative Centering offset 5 is provided.
  • the tolerances are chosen so that one of these conical surfaces is fully loaded during operation, while the offsets of the other conical surface are only partially in contact.
  • the insert ring 7 not all over, but only with part of its outer surface on the Rotor disc 1 is present. This can be achieved by using the ring a collar 11 is provided.
  • the federal government is in its diameter and its axial extent so that it is a small on both sides of the collar Gap 12 generated between ring 7 and rotor disk 1. The smaller one now The contact surface causes a favorable, reduced heat transfer from the rotor disc on the insert ring.
  • the rotor disk 1 - in the cavity 6 of the Insert ring 7 is housed - made of a ferritic steel with lower Expansion coefficient and the rotor disk 2 consists of an austenitic Steel with higher expansion coefficients is used as a material for the Insert ring 7 preferably also a material with higher coefficients of expansion chosen. In the case of gas turbines with high thermal loads are these material combinations for rotor disks 1 and 2 common.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
EP98810441A 1997-07-03 1998-05-14 Connexion d' éléments rotatifs Expired - Lifetime EP0893576B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19728345A DE19728345A1 (de) 1997-07-03 1997-07-03 Kraft- und formschlüssige Verbindung von rotierenden Bauteilen
DE19728345 1997-07-03

Publications (3)

Publication Number Publication Date
EP0893576A2 true EP0893576A2 (fr) 1999-01-27
EP0893576A3 EP0893576A3 (fr) 1999-12-08
EP0893576B1 EP0893576B1 (fr) 2003-12-03

Family

ID=7834469

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810441A Expired - Lifetime EP0893576B1 (fr) 1997-07-03 1998-05-14 Connexion d' éléments rotatifs

Country Status (4)

Country Link
US (2) US6126357A (fr)
EP (1) EP0893576B1 (fr)
JP (1) JPH1172002A (fr)
DE (2) DE19728345A1 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19728345A1 (de) * 1997-07-03 1999-01-07 Asea Brown Boveri Kraft- und formschlüssige Verbindung von rotierenden Bauteilen
DE10134611A1 (de) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine
GB0116479D0 (en) * 2001-07-06 2001-08-29 Rolls Royce Plc Coupling arrangement
DE10319629A1 (de) * 2003-05-02 2004-11-18 Zf Friedrichshafen Ag Welle-Nabe-Verbindung
FR2867223B1 (fr) * 2004-03-03 2006-07-28 Snecma Moteurs Turbomachine comme par exemple un turboreacteur pour avion
US20140064976A1 (en) * 2012-08-14 2014-03-06 Kevin L. Corcoran Rotor keyhole fillet for a gas turbine engine
GB2512016A (en) * 2012-09-24 2014-09-24 Arterius Ltd Methods
US20170226861A1 (en) * 2014-10-15 2017-08-10 Safran Aircraft Engines Rotary assembly for a turbine engine comprising a self-supported rotor collar
CN105570189B (zh) 2014-10-31 2020-08-18 特灵国际有限公司 将叶轮固定至压缩机轴的系统和方法
US9909595B2 (en) * 2015-07-21 2018-03-06 General Electric Company Patch ring for a compressor
US10125785B2 (en) 2015-10-16 2018-11-13 Pratt & Whitney Reduced stress rotor interface
US10190598B2 (en) * 2016-02-18 2019-01-29 Pratt & Whitney Canada Corp. Intermittent spigot joint for gas turbine engine casing connection

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3088758A (en) * 1958-02-12 1963-05-07 Atomic Energy Authority Uk Thermocompensating joint
US3713676A (en) * 1971-05-07 1973-01-30 Gen Electric Predeformed rabbit joint
CH590414A5 (fr) * 1975-07-04 1977-08-15 Bbc Brown Boveri & Cie
DE2643886C2 (de) * 1976-09-29 1978-02-09 Kraftwerk Union AG, 4330 Mülheim Gasturbinentäufer in Scheibenbauart
DE2851507C2 (de) * 1978-11-29 1982-05-19 Aktiengesellschaft Kühnle, Kopp & Kausch, 6710 Frankenthal Isolations-Federkörper und dessen Verwendung
AT378575B (de) * 1979-10-25 1985-08-26 Elin Union Ag Rotor fuer eine thermische turbomaschine
DE3625996A1 (de) * 1986-07-31 1988-02-04 Kuehnle Kopp Kausch Ag Laufzeug fuer einen abgasturbolader
US4859143A (en) * 1987-07-08 1989-08-22 United Technologies Corporation Stiffening ring for a stator assembly of an axial flow rotary machine
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
KR0154105B1 (ko) * 1989-10-30 1998-11-16 제랄드 피. 루니 보어리스 허브 컴프레스 휠을 가진 터보차저 컴프레서 휠 조립체
US5056950A (en) * 1990-08-31 1991-10-15 Allied-Signal Inc Thermally activated joint
US5163816A (en) * 1991-07-12 1992-11-17 General Motors Corporation Wheel lock, centering and drive means and turbocharger impeller combination
DE4141427A1 (de) * 1991-12-16 1993-06-17 Stroemungsmaschinen Gmbh Gasturbine mit einem radialverdichter aus aluminium
US5503490A (en) * 1994-05-13 1996-04-02 United Technologies Corporation Thermal load relief ring for engine case
DE19540745A1 (de) * 1995-11-02 1997-05-07 Asea Brown Boveri Verdichterrad-Wellenverbindung
DE19728085A1 (de) * 1997-07-02 1999-01-07 Asea Brown Boveri Fügeverbindung zwischen zwei Fügepartnern sowie deren Verwendung
DE19728345A1 (de) * 1997-07-03 1999-01-07 Asea Brown Boveri Kraft- und formschlüssige Verbindung von rotierenden Bauteilen

Also Published As

Publication number Publication date
EP0893576B1 (fr) 2003-12-03
EP0893576A3 (fr) 1999-12-08
JPH1172002A (ja) 1999-03-16
US6276863B1 (en) 2001-08-21
DE19728345A1 (de) 1999-01-07
DE59810313D1 (de) 2004-01-15
US6126357A (en) 2000-10-03

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