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EP0707135A3 - Bladed rotor - Google Patents

Bladed rotor Download PDF

Info

Publication number
EP0707135A3
EP0707135A3 EP95810614A EP95810614A EP0707135A3 EP 0707135 A3 EP0707135 A3 EP 0707135A3 EP 95810614 A EP95810614 A EP 95810614A EP 95810614 A EP95810614 A EP 95810614A EP 0707135 A3 EP0707135 A3 EP 0707135A3
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
radii
bladed rotor
rotor
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Withdrawn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
EP95810614A
Other languages
German (de)
French (fr)
Other versions
EP0707135A2 (en
Inventor
Uy-Liem Dr. Nguyen
Ueli Wieland
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.)
ABB AG Germany
Original Assignee
ABB Management AG
ABB Asea Brown Boveri Ltd
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 Management AG, ABB Asea Brown Boveri Ltd filed Critical ABB Management AG
Publication of EP0707135A2 publication Critical patent/EP0707135A2/en
Publication of EP0707135A3 publication Critical patent/EP0707135A3/en
Withdrawn legal-status Critical Current

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Bei einem beschaufelten Rotor (1) einer axial durchströmten Turbomaschine bestehen die Schaufeln, im wesentlichen aus einem Schaufelblatt (2a) und einem Schaufelfuss (2b). Sie sind mit ihren Schaufelfüssen (2b) reihenweise in umlaufenden Schaufelnuten (11) mit seitlichen Tragzacken befestigt. Zwischen Schaufelblatt (2a) und Schaufelfuss (2b) ist eine zur Montage der Schaufeln auf dem Rotor (1) dienende Schulter (6) angebracht. Die Schaufelnuten (11) sind symmetrisch zu den zugehörigen Symmetrieebenen (8b) durch mehrere Radien (R1-R4) ausgeformt, wobei der vorangehende Radius (R1) jeweils grösser als der nachfolgende Radius (R2) ist. Die durch die Radien (R1-R4) gebildeten Kreisbögen (21-24) besitzen an ihren Berührungspunkten eine gemeinsame Tangente (T).

Figure 00000001
In the case of a bladed rotor (1) of an axially flowed through turbomachine, the blades consist essentially of an airfoil (2a) and a blade root (2b). They are fastened with their blade feet (2b) in rows in circumferential blade grooves (11) with lateral support teeth. A shoulder (6), which is used to mount the blades on the rotor (1), is attached between the airfoil (2a) and the blade root (2b). The blade grooves (11) are formed symmetrically to the associated planes of symmetry (8b) by a plurality of radii (R1-R4), the preceding radius (R1) being larger than the following radius (R2). The arcs (21-24) formed by the radii (R1-R4) have a common tangent (T) at their points of contact.
Figure 00000001
EP95810614A 1994-10-14 1995-10-03 Bladed rotor Withdrawn EP0707135A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4436729A DE4436729A1 (en) 1994-10-14 1994-10-14 Bladed rotor
DE4436729 1994-10-14

Publications (2)

Publication Number Publication Date
EP0707135A2 EP0707135A2 (en) 1996-04-17
EP0707135A3 true EP0707135A3 (en) 1998-09-02

Family

ID=6530756

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810614A Withdrawn EP0707135A3 (en) 1994-10-14 1995-10-03 Bladed rotor

Country Status (4)

Country Link
US (1) US5580218A (en)
EP (1) EP0707135A3 (en)
JP (1) JPH08200005A (en)
DE (1) DE4436729A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702204A1 (en) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor for axial flow turbomachine i.e. gas turbine, in combined cycle power plant, has rotating blades inserted into groove, and blade root comprising inverted-T root with hammer head and adapted to base area of groove in radial direction
EP2320030B1 (en) * 2009-11-10 2012-12-19 Alstom Technology Ltd Rotor and rotor blade for an axial turbomachine
DE102010053141B4 (en) 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbine aggregate with possible over-rotation of the foot of a blade to the installation of a last blade
US8734112B2 (en) 2010-11-30 2014-05-27 United Technologies Corporation Asymmetrical rotor blade slot attachment
US9057278B2 (en) * 2012-08-22 2015-06-16 General Electric Company Turbine bucket including an integral rotation controlling feature
US9828865B2 (en) * 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
EP2860361B1 (en) 2013-10-08 2017-03-01 MTU Aero Engines GmbH Component support and fluid flow engine
JP2017120046A (en) * 2015-12-28 2017-07-06 株式会社東芝 Dovetail joint

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (en) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Method for fastening the blades of axial turbo machines, in particular blades manufactured with coarser root tolerances
US3881844A (en) * 1974-05-28 1975-05-06 Gen Electric Blade platform vibration dampers
GB2097480A (en) * 1981-04-29 1982-11-03 Rolls Royce Rotor blade fixing in circumferential slot
EP0081436A1 (en) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Compressor or turbine rotor, the wheel of which supports the hammer-type foot blades and method of assembling such a rotor
EP0210940A1 (en) * 1985-07-18 1987-02-04 United Technologies Corporation Flanged ladder seal
EP0305223A1 (en) * 1987-06-10 1989-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Blade locking device and (de)mounting thereof
FR2664944A1 (en) * 1990-07-18 1992-01-24 Snecma Compressor formed particularly of diffusers in the shape of a ring and method for mounting this compressor
GB2265671A (en) * 1992-03-24 1993-10-06 Rolls Royce Plc Bladed rotor for a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2414278A (en) * 1943-07-23 1947-01-14 United Aircraft Corp Turbine blade mounting
JPS61212603A (en) * 1985-03-16 1986-09-20 Hitachi Zosen Corp Turbine vane wheel
US5141401A (en) * 1990-09-27 1992-08-25 General Electric Company Stress-relieved rotor blade attachment slot
US5474423A (en) * 1994-10-12 1995-12-12 General Electric Co. Bucket and wheel dovetail design for turbine rotors

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (en) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Method for fastening the blades of axial turbo machines, in particular blades manufactured with coarser root tolerances
US3881844A (en) * 1974-05-28 1975-05-06 Gen Electric Blade platform vibration dampers
GB2097480A (en) * 1981-04-29 1982-11-03 Rolls Royce Rotor blade fixing in circumferential slot
EP0081436A1 (en) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Compressor or turbine rotor, the wheel of which supports the hammer-type foot blades and method of assembling such a rotor
EP0210940A1 (en) * 1985-07-18 1987-02-04 United Technologies Corporation Flanged ladder seal
EP0305223A1 (en) * 1987-06-10 1989-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Blade locking device and (de)mounting thereof
FR2664944A1 (en) * 1990-07-18 1992-01-24 Snecma Compressor formed particularly of diffusers in the shape of a ring and method for mounting this compressor
GB2265671A (en) * 1992-03-24 1993-10-06 Rolls Royce Plc Bladed rotor for a gas turbine engine

Also Published As

Publication number Publication date
JPH08200005A (en) 1996-08-06
US5580218A (en) 1996-12-03
DE4436729A1 (en) 1996-04-18
EP0707135A2 (en) 1996-04-17

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