EP0520260A1 - Rotor à tambour pour turbine axiale - Google Patents

Rotor à tambour pour turbine axiale Download PDF

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Publication number
EP0520260A1
EP0520260A1 EP92109960A EP92109960A EP0520260A1 EP 0520260 A1 EP0520260 A1 EP 0520260A1 EP 92109960 A EP92109960 A EP 92109960A EP 92109960 A EP92109960 A EP 92109960A EP 0520260 A1 EP0520260 A1 EP 0520260A1
Authority
EP
European Patent Office
Prior art keywords
groove
blade
blades
drum rotor
preliminary
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
EP92109960A
Other languages
German (de)
English (en)
Other versions
EP0520260B1 (fr
Inventor
Hermann Baer
Hans Meyer
Ui-Liem Dr. Nguyen
Peter Novacek
Paul Slepcevic
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 Asea Brown Boveri Ltd
ABB AB
Original Assignee
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 Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0520260A1 publication Critical patent/EP0520260A1/fr
Application granted granted Critical
Publication of EP0520260B1 publication Critical patent/EP0520260B1/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
    • F01D5/10—Anti- vibration means
    • 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

Definitions

  • the invention relates to a drum rotor for an axially flow-through turbomachine, in which the blades are fastened in rows with their feet in circumferential blade grooves with lateral support teeth.
  • Such blade attachments are usually found in compressor and turbine rotors. With every rotor revolution, the rotating blade grooves change their axial dimension due to the rotor deflection. The dimensional change takes place with an amplitude, which depends on the respective construction. If the amplitude exceeds a certain level, damage to the blade roots or rotor rotations can result from frictional fatigue.
  • the corresponding parts of the first turbomachine stage in multi-stage machines are particularly at risk since the mutual relief provided by adjacent blade grooves is not given here. As a result, significantly greater relative displacement amplitudes occur in this first vane groove than in the subsequent vane grooves. This fact is explained in FIGS. 2 and 3 to be described later.
  • the invention tries to avoid all these disadvantages. It is based on the task of taking a measure in the case of rotors of the type mentioned at the beginning in which the axial displacement and the asymmetrical deformation of the first bladed groove are reduced at least approximately to the corresponding dimension of the second blade groove.
  • the preliminary groove is equipped with axially divided locking segments.
  • the actual closing of the preliminary groove prevents the supply of heat, which would lead to asymmetrical deformations.
  • the axial division of the closure segments has the advantage that their two halves can freely follow the relative movements of the support shoulders.
  • the high-pressure rotor 20 is provided with thirteen rows of runners.
  • the individual blades, consisting of blade 21 and blade root 22, are inserted in circumferential blade grooves, which are numbered from 1 to 13 on the steam inlet side and on the steam outlet side. Dash-dotted is the flow-limiting contour 23 of the cylinder, not shown, which also carries the 13 rows of guide vanes.
  • the blade feet 22 have a hammer head shape. The centrifugal forces and bending moments acting on the blade during operation are guided into the rotor by means of shoulders via appropriately configured support teeth of the blade groove.
  • the deformation of the blade groove is shown in FIG. 2 using a rotor cutout.
  • the masses Ao and Au are taken at the transition between the vertical and horizontal side wall of the recess. This transition lies opposite the most stressed point of the hammer head, which is why As a rule, the vertical and horizontal bars of the blade root are rounded.
  • the preliminary groove 0 has essentially the same axial distance from the first vane groove 1 as that between the two first vane grooves 1 and 2. Moreover, it has the same radial depth as the immediately adjacent vane groove 1. These two measures ensure that the between the pre-groove 1 and the blade groove 1 lying on the rotor-side material accumulation corresponds to the material volume that is present in the area of the rotor surface between the first and second blade groove and exerts a significant influence on the flank movements of the blade grooves.
  • the same groove depth and the same groove spacing are thus the optimal values for achieving the lowest possible axial displacement for a given construction, as is basically determined by the blade grooves 1-13.
  • the preliminary groove 0 also has the same geometry as the immediately adjacent blade groove 1, which has a favorable effect on the production costs.
  • the preliminary groove 0 is filled according to FIG. 4 with axially divided closure segments 24. These so-called blind segments are flush with the rotor surface. The two halves can follow these relative movements of the support shoulders on the occasion of the unavoidable axial movements.
  • any groove shape is suitable in terms of geometry, provided that the optimum depth dimension that is decisive for the greatest possible effect is duly observed. Filling or closing of the groove can also take place as long as the insulation criterion is taken into account.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP92109960A 1991-06-28 1992-06-13 Rotor à tambour pour turbine axiale Expired - Lifetime EP0520260B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1923/91 1991-06-28
CH192391 1991-06-28

Publications (2)

Publication Number Publication Date
EP0520260A1 true EP0520260A1 (fr) 1992-12-30
EP0520260B1 EP0520260B1 (fr) 1994-04-13

Family

ID=4221757

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92109960A Expired - Lifetime EP0520260B1 (fr) 1991-06-28 1992-06-13 Rotor à tambour pour turbine axiale

Country Status (4)

Country Link
US (1) US5232336A (fr)
EP (1) EP0520260B1 (fr)
JP (1) JPH05187201A (fr)
DE (1) DE59200115D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0707136A1 (fr) * 1994-10-14 1996-04-17 ABB Management AG Rotor à tambour pour une turbomachine à écoulement axial

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
DE10356586A1 (de) * 2003-12-04 2005-07-07 Alstom Technology Ltd Verdichterrotor

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1024983B (de) * 1954-02-16 1958-02-27 Siemens Ag Anordnung an axial beaufschlagten Turbinen, deren Schaufeln mit Formschluss in eine Ringnut des Schaufeltraegers eingesetzt sind

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US941389A (en) * 1908-05-16 1909-11-30 Westinghouse Machine Co Turbine-blading.
GB190915893A (en) * 1909-07-07 1909-09-16 Walter Wills Improvements in Roller Skates.
US3680979A (en) * 1970-10-07 1972-08-01 Carrier Corp Rotor structure for turbo machines
DE2408641A1 (de) * 1974-02-21 1975-08-28 Aeg Kanis Turbinen Beschaufelung von stroemungsmaschinen
US4872307A (en) * 1987-05-13 1989-10-10 Gibbs & Hill, Inc. Retrofit of simple cycle gas turbines for compressed air energy storage application

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1024983B (de) * 1954-02-16 1958-02-27 Siemens Ag Anordnung an axial beaufschlagten Turbinen, deren Schaufeln mit Formschluss in eine Ringnut des Schaufeltraegers eingesetzt sind

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0707136A1 (fr) * 1994-10-14 1996-04-17 ABB Management AG Rotor à tambour pour une turbomachine à écoulement axial

Also Published As

Publication number Publication date
JPH05187201A (ja) 1993-07-27
DE59200115D1 (de) 1994-05-19
EP0520260B1 (fr) 1994-04-13
US5232336A (en) 1993-08-03

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