EP0520260B1 - Rotor à tambour pour turbine axiale - Google Patents
Rotor à tambour pour turbine axiale Download PDFInfo
- Publication number
- EP0520260B1 EP0520260B1 EP92109960A EP92109960A EP0520260B1 EP 0520260 B1 EP0520260 B1 EP 0520260B1 EP 92109960 A EP92109960 A EP 92109960A EP 92109960 A EP92109960 A EP 92109960A EP 0520260 B1 EP0520260 B1 EP 0520260B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- groove
- blade
- drum rotor
- blades
- 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.)
- Expired - Lifetime
Links
Images
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 flowed through turbomachine, in which the blades are fastened in rows with their feet in circumferential blade grooves with lateral support teeth.
- Blade attachments of this type are generally found in compressor and turbine rotors. With each 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 there is no mutual relief from adjacent blade grooves. 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.
- this is achieved in that a circumferential pre-groove not equipped with blades is arranged upstream of the blade groove provided for the first row of blades.
- 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 blade groove 1 as that between the two first blade grooves 1 and 2. In addition, it has the same radial depth as the immediately adjacent blade groove 1.
- 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 be done 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)
Claims (5)
- Rotor cylindrique pour une turbomachine à écoulement axial, dans laquelle les aubes sont fixées en rangées par leurs emplantures (22) dans des rainures d'aubes circulaires par des dents porteuses latérales, caractérisé en ce qu'en amont de l'écoulement de la rainure d'aubes (1) prévue pour la première rangée d'aubes, on dispose une rainure préliminaire circulaire (0) non munie d'aubes.
- Rotor cylindrique selon la revendication 1, caractérisé en ce que la rainure préliminaire (0) a essentiellement la même profondeur radiale que la rainure d'aubes (1) prévue pour la première rangée d'aubes.
- Rotor cylindrique selon la revendication 2, caractérisé en ce que la rainure préliminaire (0) a essentiellement la même géométrie que la rainure d'aubes (1) prévue pour la première rangée d'aubes.
- Rotor cylindrique selon la revendication 1, caractérisé en ce que l'écart axial de la rainure préliminaire (0) à la première rainure d'aubes (1) à aubage est essentiellement le même que l'écart axial de la première rainure d'aubes (1) à la deuxième rainure d'aubes (2).
- Rotor cylindrique selon la revendication 1, caractérisé en ce que la rainure préliminaire (0) est munie de segments de fermeture (24) séparés axialement.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH192391 | 1991-06-28 | ||
CH1923/91 | 1991-06-28 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0520260A1 EP0520260A1 (fr) | 1992-12-30 |
EP0520260B1 true 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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5575623A (en) * | 1994-10-14 | 1996-11-19 | Abb Management Ag | Drum rotor for an axial-flow turbomachine |
Families Citing this family (2)
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 |
Family Cites Families (6)
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. |
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 |
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 |
-
1992
- 1992-06-13 EP EP92109960A patent/EP0520260B1/fr not_active Expired - Lifetime
- 1992-06-13 DE DE59200115T patent/DE59200115D1/de not_active Expired - Fee Related
- 1992-06-26 JP JP4169420A patent/JPH05187201A/ja active Pending
- 1992-06-26 US US07/904,668 patent/US5232336A/en not_active Expired - Fee Related
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5575623A (en) * | 1994-10-14 | 1996-11-19 | Abb Management Ag | Drum rotor for an axial-flow turbomachine |
Also Published As
Publication number | Publication date |
---|---|
EP0520260A1 (fr) | 1992-12-30 |
JPH05187201A (ja) | 1993-07-27 |
DE59200115D1 (de) | 1994-05-19 |
US5232336A (en) | 1993-08-03 |
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